Abstract

Disclosed in the embodiments of the present description is a fault diagnosis method for a sensor of an electromechanical actuation system. The method comprises: on the basis of a reference sensor signal and an actual sensor signal of a target sensor, determining whether the target sensor has a fault, wherein the reference sensor signal is output by an electromechanical actuation system model; if the target sensor has a fault, inputting the difference between the reference sensor signal and the actual sensor signal into a first neural network, so as to determine whether the fault of the target sensor belongs to a first fault type; and if it is not determined that the fault of the target sensor belongs to the first fault type, inputting the actual sensor signal into a second neural network, so as to determine whether the fault of the target sensor belongs to a second fault type.

IPC Classes  ?

• G01D 18/00 - Testing or calibrating apparatus or arrangements provided for in groups
• G06F 18/241 - Classification techniques relating to the classification model, e.g. parametric or non-parametric approaches
• G06N 3/045 - Combinations of networks
• G06N 3/126 - Evolutionary algorithms, e.g. genetic algorithms or genetic programming

Abstract

A virtual synthesis and anomaly monitoring method for a glide slope deviation signal in an instrument landing system (ILS), comprising: generating a Gs glide slope deviation signal by means of the ILS (120); converting longitude/latitude/altitude data outputted by an INS and a satellite positioning system into longitude/latitude/altitude data fused by a Kalman filter (112); on the basis of the position of an aircraft and longitude and latitude coordinates of an airport Gs station and the altitude of the aircraft, calculating distance information between the aircraft and the airport Gs station (114); on the basis of the distance information, using a trigonometric function to calculate a virtually synthesized glide slope deviation signal (116); comparing the virtually synthesized glide slope deviation signal with the Gs glide slope deviation signal to determine whether the difference between the two exceeds a preset threshold (132): if not, determining that the Gs glide slope deviation signal is normal and selecting the Gs glide slope deviation signal for landing guidance (134); and if yes, determining that the Gs glide slope deviation signal is anomalous and selecting the virtually synthesized glide slope deviation signal for landing guidance (136).

IPC Classes  ?

• G01C 3/22 - Measuring distances in line of sightOptical rangefinders using a parallactic triangle with variable angles and a base of fixed length at, near, or formed by, the object
• G01S 19/00 - Satellite radio beacon positioning systemsDetermining position, velocity or attitude using signals transmitted by such systems

Abstract

A method and system for regulating and controlling the damping of a magnetorheological fluid landing gear of an aircraft. The method comprises: acquiring parameters required for regulating and controlling the current of an excitation coil of a magnetorheological fluid landing gear; on the basis of the acquired parameters, generating a change curve, which changes with time starting from the present moment and is used for regulating and controlling the current; and applying the change curve for the current to control the current applied to the excitation coil, so as to regulate and control the damping of the magnetorheological fluid landing gear.

IPC Classes  ?

• B64C 25/60 - Oleo legs
• B64C 25/58 - Arrangements or adaptations of shock-absorbers or springs
• F16F 9/53 - Means for adjusting damping characteristics by varying fluid viscosity, e.g. electromagnetically

Goods & Services

Vehicles for locomotion by land, air, water or rail; airplane towing vehicles; aerial conveyors; tires for aircraft wheels; helicopters; parachutes; civilian drones; aeronautical apparatus, machines and appliances; aircraft boarding bridge; aeroplanes; luggage carriers for vehicles. Vehicle battery charging; vehicle breakdown repair services; vehicle greasing; custom installation of exterior, interior and mechanical parts of vehicles [tuning]; vehicle polishing; anti-rust treatment for vehicles; vehicle maintenance; vehicle washing; providing information relating to repair services in the aviation sector; airplane maintenance and repair.

Abstract

The present application relates to a direct-current evaporative cooling simulated electric load system, comprising: a water storage unit, which is configured to store water to be supplied; a water supply unit, which is configured to provide a water supply pressure and regulate a water supply flow rate that is provided from the water storage unit to a direct-current evaporation unit; the direct-current evaporation unit, which is configured to provide a simulated load, use heat generated by the simulated load to convert supplied water into steam, and discharge the steam to the outside; and a control unit, which is configured to control the operation of components of the direct-current evaporative cooling simulated electric load system, wherein the control unit adjusts a flow-regulating valve in the water supply unit to match the water supply flow rate with a loading power of the direct-current evaporation unit, and the temperature of the direct-current evaporation unit is also controlled within a required interval range. In addition, the present application further relates to a corresponding control method for a direct-current evaporative cooling simulated electric load system.

IPC Classes  ?

• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

A ducted fan unit (1). The ducted fan unit (1) is mounted on an aircraft wing (3); a duct (11) is formed inside the ducted fan unit (1); the duct (11) is sequentially provided with a duct air intake section (111), a duct middle section (112) and a duct exhaust section (113) in an airflow direction; a fan (12) is provided in the duct air intake section (111), and the fan (12) is connected to a power unit (13) so as to guide air from the outside into the duct (11); the air from the outside enters the duct (11) from the duct air intake section (111), passes through the duct middle section (112) and then flows out of the duct (11) via the duct exhaust section (113); and the cross sections of the duct sections of the duct (11) are shaped as a rounded rectangle or a circle. The efficiency of the fan in the ducted fan units (1) is improved, and a stable lift augmentation effect is provided.

IPC Classes  ?

• B64C 11/00 - Propellers, e.g. of ducted typeFeatures common to propellers and rotors for rotorcraft
• B64C 11/46 - Arrangements of, or constructional features peculiar to, multiple propellers
• B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings

Abstract

The present application relates to the technical field of avionics, and provides a feedforward excitation current determining method, a device, and a storage medium, which can enable current inner loops to directly and rapidly respond to load changes rather than only relying on voltage outer loops for adjustment, thereby improving the dynamic performance of aircraft variable-frequency alternating-current power generation systems. The method is applied to an aircraft three-stage electric excitation power generation system. The system comprises a main generator, a main exciter, a permanent magnet generator, a rotating rectifier, a generator controller, and a feedforward excitation current determining apparatus. The feedforward excitation current determining apparatus is used for: acquiring load power, an engine rotating speed and a given reference voltage of the main generator; calculating an excitation current required by the current load and a no-load excitation current on the basis of the load power, the engine rotating speed and the given reference voltage of the main generator, motor parameters of the main generator, and motor parameters of the main exciter; and determining a feedforward excitation current on the basis of the excitation current required by the current load and the no-load excitation current.

IPC Classes  ?

• H02P 9/14 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field
• H02P 101/30 - Special adaptation of control arrangements for generators for aircraft

Abstract

The present invention relates to an adaptive cabin door pneumatic sealing plate for a cabin door of an aircraft, comprising a fixed portion and a deformable portion, wherein the fixed portion is fixed on the cabin door, and the deformable portion extends from the fixed portion to the fuselage of the aircraft. The sealing plate comprises a temperature control unit, and the temperature control unit can be operated to control the temperature of the deformable portion, so that the deformable portion deforms between an open state and a closed state.

IPC Classes  ?

• B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens

Abstract

A super-cooled large droplet detector, which can accurately and reliably identify and distinguish super-cooled large droplet freezing weather. The super-cooled large droplet detector comprises a detector base and a detection structure, wherein the detection structure is used for detecting super-cooled droplets in airflow and for identifying freezing weather and distinguishing super-cooled large droplet freezing weather from the freezing weather; an outer layer of the detection structure is a temperature sensor layer, an intermediate layer thereof is an electric heating film layer, and an inner layer thereof is a structure substrate; the electric heating film layer provides heating energy by means of a plurality of electric heating loops, such that the surface of the detection structure maintains at a uniform temperature; the temperature sensor layer is provided with a plurality of temperature sensors; and a controller is provided in the structure substrate, and the controller infers an impact range of the super-cooled droplets by means of temperature changes, which are caused by the super-cooled large droplets impacting the detection structure, at a plurality of different positions, and determines, by means of determining whether the impact range exceeds a critical impact range obtained when the super-cooled droplets exceeding a critical size impact the detection structure, whether the previous impacting super-cooled droplets are super-cooled large droplets.

IPC Classes  ?

• B64D 15/20 - Means for detecting icing or initiating de-icing
• G01W 1/00 - Meteorology

Abstract

The present application relates to the technical field of avionics. Provided are a method and apparatus for calculating aircraft position information, and a device and a storage medium, which are used for improving the calculation accuracy of aircraft position information. The method mainly comprises: acquiring first Gaussian plane coordinates and second Gaussian plane coordinates which respectively correspond to two pieces of distance measure equipment (DME), and acquiring a first horizontal projection distance and a second horizontal projection distance between the two pieces of DME and an aircraft slant range respectively; calculating Gaussian plane projection coordinates of an aircraft on the basis of the first Gaussian plane coordinates, the second Gaussian plane coordinates, the first horizontal projection distance and the second horizontal projection distance; and performing Gaussian coordinate inverse calculation on the Gaussian plane projection coordinates of the aircraft, so as to obtain the current longitude and latitude coordinates of the aircraft.

IPC Classes  ?

• G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using radio waves

Abstract

Disclosed in the present invention is an information dynamic extraction method for an electronic checklist (ECL) table, comprising: detecting whether a table exists in an ECL program; if a table exists in the ECL program, determining whether information extraction needs to be performed on the table; in response to determining that information extraction needs to be performed on the table, determining target parameters on the basis of the content of the table; determining an extraction range on the basis of aircraft state information and the target parameters; and extracting information from the table on the basis of the extraction range so as to display the extracted information in the ECL program.

IPC Classes  ?

• G06F 40/18 - Editing, e.g. inserting or deleting of tablesEditing, e.g. inserting or deleting using ruled lines of spreadsheets

Abstract

A pressure display apparatus (100), comprising: a pressure pointer (10), the pressure pointer (10) moving within a first moving range; a bottom color band (20), the bottom color band (20) covering the first moving range in a first direction and is set to be in a first color; a temperature assembly (30), the temperature assembly (30) being disposed on the bottom color band (20) and covering the first moving range, wherein the temperature assembly (30) comprises a first section (31) and a second section (32) whose lengths change as the temperature changes, the first section (31) is set to be in a second color, and the second section (32) is set to be transparent; and a protective cover (40), the protective cover (40) enclosing the pressure pointer (10), the bottom color band (20), and the temperature assembly (30) between the protective cover (40) and a housing (101). According to the pressure display apparatus (100), only by modifying the part of the housing (101) of a pressure gauge, whether the pressure at a current temperature falls within a predetermined range can still be accurately determined when the temperature changes, thereby reducing the modification cost and achieving temperature display compensation visually.

IPC Classes  ?

• G01L 19/04 - Means for compensating for effects of changes of temperature
• G01L 19/08 - Means for indicating or recording, e.g. for remote indication

Abstract

An aircraft windshield window frame framework assembly, comprising: window frame frameworks (20), which comprise main windshield opening frames (21) surrounding main windshields (11) of an aircraft and side windshield opening frames (22) surrounding side windshields (12) of the aircraft, wherein the main windshield opening frames (21) and the side windshield opening frames (22) are mounted on and fitted with the corresponding main windshields (11) and side windshields (12) by means of tight fit to form an integral whole, the two main windshield opening frames (21) are in direct contact and are connected in a butt joint manner, and each main windshield opening frame (21) and the corresponding side windshield opening frame (22) are in direct contact and are connected in a butt joint manner. The design of butt-joint connection of the opening frames of the four integral window frame frameworks and the use of connecting belt plates at butt-joint sections of the opening frames make a force transfer route of the window frame frameworks at connection sections more direct, thereby achieving higher load transfer efficiency and structural use efficiency, and reducing the manufacturing difficulty and manufacturing cost on the premise of meeting the load-bearing design requirement.

IPC Classes  ?

• B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens

Abstract

An inerting system for an aircraft fuel tank (100), comprising: an ejection device (200), the ejection device (200) comprising: an ejection flow inlet (210), configured to introduce, as an ejection flow (300), exhaust gas discharged by an engine or an APU of an aircraft; an ejected flow inlet (220), which is in fluid communication with a gas-phase space (110) of the fuel tank (100), so as to introduce gas in the gas-phase space as an ejected flow (600); a mixing chamber, configured to mix the ejected flow (600) entering through the ejected flow inlet (220) with the ejection flow (300) entering through the ejection flow inlet (210), so as to receive energy from the ejection flow (300); and a mixed flow outlet (230), the ejected flow (600) and the ejection flow (300) being together discharged through the mixed flow outlet (230); an inerting reaction device (700), which receives the mixed flow discharged through the mixed flow outlet (230), and performs inerting processing on the mixed flow, so as to obtain an inerted substance flow; and a post-processing device, configured to introduce the inerted substance flow back to the gas-phase space (110) of the fuel tank (100). The inerting system can improve the inerting effect of fuel tanks by fully using existing conditions of aircraft.

IPC Classes  ?

• B64D 37/32 - Safety measures not otherwise provided for, e.g. preventing explosive conditions

Abstract

A vortex generator (100) and an aircraft comprising the vortex generator. The vortex generator is disposed on an aerodynamic surface (200) of an aircraft and comprises: a support shaft (10), the support shaft (10) being fixedly mounted on the aerodynamic surface (200); and a blade (20), the blade (20) being pivotally mounted on the support shaft (10). The vortex generator (100) further comprises a memory alloy spring (30), a first end (31) of the memory alloy spring (30) being attached to the support shaft (10), and a second end (32) of the memory alloy spring (30) being attached to the blade (20). The initial length of the memory alloy spring (30) changes with a change in temperature, so as to drive the blade (20) to rotate around the support shaft (10) between a first position and a second position. The vortex generator (100) can implement active adjustment of an angle of deflection following a change in the environmental temperature, effectively controlling separation between an airflow and an airfoil. Moreover, while reducing the degree of separation of the airfoil, excess resistance is not added, and the lift force of the aircraft is increased, the torque characteristics are improved, and the goal of shock absorption is achieved.

IPC Classes  ?

• B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices

Abstract

A hatch opening device capable of increasing the opening speed of a hatch, comprising a hatch (1) and a plurality of gooseneck hinges (2). Connecting plates are connected between every adjacent gooseneck hinges (2) in the direction of a mounting shaft X of the hatch (1). The hatch opening device can increase the response speed when an RAT hatch is opened, thereby avoiding interference with an RAT system.

IPC Classes  ?

• B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens

Abstract

Disclosed is a winglet (9) for an aircraft, the winglet comprising: a first control section (L1), which is located in a base region of the winglet (9); a third control section (L3), which is located in a tip region of the winglet (9); and a second control section (L2), which is located between the first control section (L1) and the third control section (L3), wherein the second control section (L2) is a flow control section, at least a portion of the second control section (L2) in a spanwise direction of the winglet (9) is provided with a winglet slit (11), and the first control section (L1) and the third control section (L3) are non-flow control sections. Owing to the aerodynamic configuration of the winglet (9) for an aircraft, winglet flow separation in a low-speed high-attack-angle state can be delayed without designing a complex structure, and flight resistance in a high-speed cruising state can be reduced.

IPC Classes  ?

• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• B64C 21/02 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like

Abstract

The present application relates to the technical field of avionics systems. Provided are an avionics data network configuration method and apparatus, and a computer device and a storage medium, which are used for improving the update and iteration efficiency of a network configuration. The method mainly comprises: acquiring link information of each virtual link, wherein the link information comprises a maximum frame length and a transmission period; setting bandwidth packets according to the link information of the virtual links in a network, and assigning the virtual links to respective bandwidth packets; calculating a total bandwidth of all the bandwidth packets, and a transmission period and duration of each bandwidth packet according to the link information of the virtual links and a total bandwidth of an avionics data network; and setting corresponding phases for the virtual links according to the link information of the virtual links.

IPC Classes  ?

• H04L 41/0803 - Configuration setting

Abstract

The present application relates to the technical field of aviation wind tunnel testing, and provides a wind tunnel test data static aero-elasticity correction method and apparatus, a device, and a storage medium, which are used to reduce computer memory occupied in a calculation process and improve data conversion efficiency. The method mainly comprises: on the basis of a three-dimensional unstructured fluid grid, obtaining aerodynamic load data of a surface of an aircraft wind tunnel test model by means of multi-process parallel fluid dynamics numerical simulation of the aircraft wind tunnel test model on the basis of a RANS equation; according to a mapping relationship between surface aerodynamic grid points of a two-dimensional unstructured grid and a beam unit in a geometric nonlinear structure finite element model, as well as a load transmission theorem, interpolating the aerodynamic load data of the surface of the aircraft wind tunnel test model into a corresponding load node of the geometric nonlinear structure finite element model; and obtaining a corrected aerodynamic force of the aircraft wind tunnel test model, according to a deformation amount of the aircraft wind tunnel test model and an aerodynamic force difference.

IPC Classes  ?

• G06F 30/23 - Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
• G06F 30/28 - Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
• G06F 111/10 - Numerical modelling
• G06F 113/08 - Fluids

Abstract

Disclosed in the present invention are a synchronous calibration system and method for an aviation digital pressure sensor. The synchronous calibration system comprises: a standard pressure generator used for generating a series of standard pressures; a multi-channel connecting tool used for installing a plurality of aviation digital pressure sensors to be calibrated, and independently communicating each sensor with standard pressure generator gas paths; a synchronous calibration assistance apparatus provided with an input end electrically connected to the sensors, a channel switch used for selectively acquiring a sensing signal generated by any one sensor electrically connected to the input end, and an output end used for synchronously transmitting the sensing signal to a standard data collector and a pressure gauge unit; and the standard data collector and the pressure gauge unit used for generating pressure values and an electrical signal characteristic curve on the basis of the received sensing signal. The present invention can realize synchronous calibration of an electrical signal characteristic curve and pressure values of an aviation digital pressure sensor, and significantly improves the calibration efficiency.

IPC Classes  ?

• G01L 27/00 - Testing or calibrating of apparatus for measuring fluid pressure

Abstract

A ram air turbine (RAT) emergency energy driving device, comprising a first-group turbine blade (10) and a second-group turbine blade (20), which are coaxially arranged in an axial direction (A), wherein relative to the first-group turbine blade (10), the second-group turbine blade (20) can rotate about the axial direction (A) from a first position to a second position, and can be maintained at the second position; and at the first position, the first-group turbine blade (10) is superposed with the second-group turbine blade (20), while at the second position, a pre-set non-zero angle is formed between the first-group turbine blade (10) and the second-group turbine blade (20). Also disclosed is an aircraft, which comprises the RAT emergency energy driving device. Insofar as it is ensured that a space in a cabin of an RAT is not affected, the number of blades is increased, such that the turbine starts rotating faster, thereby shortening the time for the RAT to access a power grid. In addition, an increase in the number of blades can also improve the efficiency of the turbine using wind energy to convert energy, thereby improving the emergency power generation efficiency.

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes
• F02K 7/16 - Composite ram-jet/turbo-jet engines

Abstract

The present invention relates to an aircraft engine bleed air liquid-cooling system and an aircraft comprising the system. The aircraft engine bleed air liquid-cooling system comprises an evaporative refrigeration unit, a secondary refrigerant distribution unit, and one or more cooling units, wherein the evaporative refrigeration unit provides the cooling capacity of a refrigerant according to an evaporation cycle principle, and conveys cold refrigerant to the secondary refrigerant distribution unit, so that the cold refrigerant exchanges heat with liquid secondary refrigerants in the secondary refrigerant distribution unit so as to cool the liquid secondary refrigerants; the secondary refrigerant distribution unit conveys the cooled liquid secondary refrigerants to the one or more cooling units, so that the cooled liquid secondary refrigerants exchange heat with bleed air in the one or more cooling units to cool the bleed air; and the bleed air, which is cooled by the one or more cooling units, is conveyed to one or more corresponding user sub-systems. According to the technical solution, the present invention can achieve the following beneficial technical effects: being capable of improving the capacity of cooling engine bleed air, and preventing the design size of a pre-cooler from being too large.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned

Abstract

A sewing device and sewing method for an expanded sheet. The sewing device comprises: a frame (10) comprising outer columns and inner columns, wherein the outer columns comprise two separate front columns (11) and two close rear columns (12), and the inner columns comprise two close central columns (13); a conveying device (20) sleeved on the corresponding outer columns and inner columns of the frame (10) for circulating operation so as to circulate an expanded sheet from the front columns (11) to the rear columns (12), wherein the conveying device (20) comprises: a first conveyor belt (21), a second conveyor belt (22), and a plurality of clamping parts; and a sewing apparatus (30), the sewing apparatus (30) being mounted on the central columns (13) of the frame (10), and used for sewing a first expanded sheet and a second expanded sheet.

IPC Classes  ?

• D05B 23/00 - Sewing apparatus or machines not otherwise provided for
• D05B 33/00 - Devices incorporated in sewing machines for supplying or removing the work
• D05B 41/00 - Work-collecting devices for sewing machines
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure

Abstract

Disclosed is a dual-mode hydraulic servo actuator. The actuator comprises: an oil intake pipeline and an oil return pipeline, wherein the oil intake pipeline is distributed to a servo valve (6) and a first-stage modal selection valve (7), and the oil return pipeline is connected to a variable damping valve (9); a second-stage modal selection valve (8) connected to the first-stage modal selection valve (7), the servo valve (6) and the variable damping valve (9); and an actuation cylinder (10) connected to the second-stage modal selection valve (8), wherein the actuation cylinder (10) carries out linear output when the hydraulic servo actuator is in a first mode. The hydraulic servo actuator further comprises a pressure relief unit. When the hydraulic servo actuator is in a second mode, the actuation cylinder (10) is connected to the variable damping valve (9)/the pressure relief unit, and the pressure relief unit provides a maintenance connection port and provides a release function of releasing a damping force, so as to realize damping-free connection between the actuation cylinder (10) and the oil return pipeline. The hydraulic servo actuator solves the problem of operation difficulty caused by a damping force during ground maintenance, thereby significantly improving the operability and convenience of maintenance inspection, and thus improving the economy of operating an aircraft.

IPC Classes  ?

• B64C 13/40 - Transmitting means with power amplification using fluid pressure
• B64C 13/42 - Transmitting means with power amplification using fluid pressure having duplication or stand-by provisions
• B64C 13/50 - Transmitting means with power amplification using electrical energy

Abstract

A thermal test apparatus (10) and test method for a hybrid connection structure (16). The thermal test apparatus (10) comprises a first connection member (11), a second connection member (12) and a temperature adjustment cabinet (13). A load is applied to the hybrid connection structure (16) by means of the first connection member (11) and the second connection member (12), so as to perform a mechanical test on the hybrid connection structure (16). The temperature adjustment cabinet (13) provides a temperature environment for the hybrid connection structure (16), and records the strain of the hybrid connection structure (16) at a preset temperature. By means of the temperature adjustment cabinet (13) providing a preset temperature for the hybrid connection structure (16), and applying a load to the hybrid connection structure (16), a static test for the hybrid connection structure (16) is implemented at a preset temperature. Temperature and load are both taken into consideration to perform a thermal test on a hybrid connection structure (16), such that the test environment is closer to a real working condition.

IPC Classes  ?

• G01N 3/18 - Performing tests at high or low temperatures
• G01N 3/04 - Chucks
• G01N 3/06 - Special adaptations of indicating or recording means

Abstract

CGCGCGCG is greater than 0, water in the rear water tank (01) being consumed by the user, and discharging wastewater in the user into the front wastewater tank (03). The described method and system are simple and reliable, and the center of gravity of an aircraft can be easily kept within an expected ideal range.

IPC Classes  ?

• B64C 17/08 - Aircraft stabilisation not otherwise provided for by ballast supply or discharge

Abstract

A fan duct nozzle of an aviation turbofan engine. A notch is formed in a rear edge of an engine nacelle on an outer side of an engine pylon, and a flow guide curved surface matching the notch in shape is arranged on a profile of the fan duct nozzle. The notch is unilaterally formed in the outer side of the engine pylon, and a transition section between the notch and the rear edge of the engine nacelle includes two transition rounded corners. The present disclosure adopts a unilateral notch-shaped nozzle in the external duct of the turbofan engine, uses high-speed flowing of venting by an engine fan to provide flowing protection for an airfoil, improves a lift coefficient, and reduces negative impact on the airfoil exerted by the engine nacelle at a high incidence, thus lowering resistance, lowering a weight of the nacelle, and improving a lift-drag ratio.

IPC Classes  ?

• F02K 1/52 - Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
• B64C 7/02 - Nacelles
• F02K 1/40 - Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
• B64C 7/00 - Structures or fairings not otherwise provided for

Abstract

A passenger cabin disinfection system (100), a passenger cabin disinfection method, and a vehicle comprising the passenger cabin disinfection system (100). The passenger cabin disinfection system (100) comprises: an integrated illumination and disinfection unit (10), which is arranged in a passenger cabin (200), and comprises: an illumination module (11), an ultraviolet disinfection module (12, 12') arranged in parallel with the illumination module (11), and a switching module (13) used for selectively turning on or turning off the illumination module (11) and the ultraviolet disinfection module (12, 12'), wherein the switching module (13) allows only one of the illumination module (11) and the ultraviolet disinfection module (12, 12') to power on; and an entrance area control unit (20), which is arranged at the entrance (201) of the passenger cabin (200) and in communication connection with the integrated illumination and disinfection unit (10) and an attendant management terminal (30) in the passenger cabin (200), wherein the entrance area control unit (20) comprises: a kinetic energy switch (21) used for controlling the illumination module (11) and the ultraviolet disinfection module (12, 12'), and a sensor (22) used for sensing a passenger passing through the entrance (201). The degree of integration and intelligence of the passenger cabin disinfection system (100) is high.

IPC Classes  ?

• A61L 9/20 - Ultraviolet radiation
• A61L 2/10 - Ultraviolet radiation
• A61L 2/24 - Apparatus using programmed or automatic operation
• A61L 2/26 - Accessories
• F21V 33/00 - Structural combinations of lighting devices with other articles, not otherwise provided for
• F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft

Abstract

An integrated electric propulsion system for electric aircrafts. A distributed electric propulsion system and a fly-by-wire flight control actuation system which are integrated on aircraft wings can be unified, thereby providing for the electric aircrafts reliable, efficient and stable flight power, and meanwhile reducing the weight and energy loss of the system. The integrated electric propulsion system for electric aircrafts is independent from an airborne electric energy system on which a plurality of electrified loads are mounted, and the integrated electric propulsion system for electric aircrafts integrates a distributed electric propulsion system and a fly-by-wire flight control actuation system which are integrated on wings of an electric aircraft, so as to connect same with a unified power supply system. In case of normal power supply, power is supplied via a first power supply path to the distributed electric propulsion system and the fly-by-wire flight control actuation system. Under a failure condition that normal power supply is partially failed or an emergency condition that the normal power supply is all failed, by means of an energy management part, the path for supplying power to the distributed electric propulsion system and the fly-by-wire flight control actuation system is switched to a power supply path different from the first power supply path.

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• H02J 1/08 - Three-wire systemsSystems having more than three wires

Abstract

The present invention relates to a wing system integrated with a power battery module. The wing system comprises: a wing box, the wing box comprising a plurality of wing support members, and the plurality of wing support members being configured to define therebetween at least one power battery cell mounting compartment, and power battery cells, the power battery cells being arranged in the at least one power battery cell mounting compartment, so as to allow the plurality of wing support members constituting the at least one power battery cell mounting compartment to be used as at least a part of battery casings of the power battery cells. In the wing system of the present invention, the wing box serves as a part of the battery casings so that battery cells or cells can be accommodated therein, thereby providing effective and safe protection and necessary functions for power battery modules, reducing the weight of power battery systems, and increasing the structure and space utilization rate. In addition, the present invention also relates to an electric aircraft.

IPC Classes  ?

• B64C 3/32 - Wings specially adapted for mounting power plant
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B60L 53/80 - Exchanging energy storage elements, e.g. removable batteries

Abstract

An aircraft wing (10) having an integrated distributed ducted fan, the aircraft wing (10) being attached to a fuselage (20) and being provided with a ducted fan power set (30), wherein the ducted fan power set (30) is provided on an inboard section (11) of the aircraft wing (10) and is arranged above the aircraft wing (10) so as to form an integral body with the aircraft wing (10), and wherein the inboard section (11) comprises an inboard flap (11a), the inboard flap (11a) being able to move between a first extended position and a first retracted position, and wherein, when in the first extended position, the inboard flap (11A) protrudes relative to the inboard section (11) and abuts against the trailing edge of the ducted fan power set (30), and when in the first retracted position, the inboard flap (11A) is retracted relative to the inboard section (11). The inboard flap (11A) is a movable component. In this way, when necessary, the inboard flap (11A) extends rearwards and deflects, and the jet of air outputted by the ducted fan, under the action of the Coanda effect, respectively produces a low-pressure area and a high-pressure area on the upper surface and the lower surface of the inboard flap (11A), achieving wing lift.

IPC Classes  ?

• B64C 3/32 - Wings specially adapted for mounting power plant
• B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• B64C 9/18 - Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps

Abstract

A flexible connecting structure (100) for an arresting wall and a fuselage. The flexible connecting structure is configured to fix an arresting wall (200) to the interior of an aircraft (300), and comprises: a first connecting joint (10), the first connecting joint (10) being pivotally connected to a second connecting joint (201) arranged on the arresting wall; a flexible transition member (20), a first end (21) of the flexible transition member being fixed to a free end (11) of the first connecting joint; and an interframe short beam (30), which is fixed to an adjacent frame (301) and stringer (302) on an aircraft panel and fixed to a second end (22) of the flexible transition member. The structure can bear, by means of the flexible transition member, a course load transmitted via the arresting wall to the fuselage of the aircraft, thereby effectively avoiding excessive constraint of a rigid arresting wall on deformation of structures such as local skin of the fuselage under a working condition of pressurization, and eliminating the influence on the fatigue performance of the structure of the fuselage.

IPC Classes  ?

• B64C 1/10 - Bulkheads

Abstract

An outer duct nozzle of an aerial turbofan engine. A notch (3) is formed in an engine nacelle rear edge (4) on the outer side of an engine pylon (2), a flow guide curved surface (7) matching the notch (3) in shape is provided on the outer duct nozzle profile, the notch (3) is unilaterally provided on the outer side of the engine pylon (2), and a transition section of the notch (3) and the engine nacelle rear edge (4) comprises two sections of transition rounded corners (5, 6). According to the present invention, the unilateral notch-shaped nozzle of the outer duct of the turbofan engine is used, flow protection is provided for wings by utilizing high-speed flow of exhaust gas of an engine fan, a lift coefficient is improved, and an adverse effect of an engine nacelle (1) on the wings under a large angle of attack is reduced, such that the resistance is reduced, the weight of the nacelle is reduced, and a lift-drag ratio is improved.

IPC Classes  ?

• B64D 29/00 - Power-plant nacelles, fairings or cowlings

Abstract

An airborne device which has a bus interface and a dedicated wireless transmission apparatus connected to the bus interface, the dedicated wireless transmission apparatus includes: an interface conversion module; and a wireless transmission module. The interface conversion module is configured to convert bus data received from the bus interface into a data packet suitable for transmission using a radio access technology, and/or to convert a data packet received from the wireless transmission module into bus data corresponding to the bus interface. The wireless transmission module is configured to use the radio access technology to transmit the converted data packet, and/or to receive the data packet transmitted using the radio access technology. In addition, a method and a system for wireless interconnection between airborne devices.

IPC Classes  ?

• H04L 12/40 - Bus networks
• H04L 69/08 - Protocols for interworkingProtocol conversion

Abstract

An equipment failure rate determining method and device, computer equipment and a storage medium, which relate to the technical field of aviation and are used for determining a failure rate of each equipment in an integrated modular avionics system. The main technical solution lies in: determining an allocation failure rate of each equipment type according to an importance value, a complexity value, a maintenance value and a test value of the equipment type in the integrated modular avionics system (S101); determining an equipment type of which the allocation failure rate is less than a corresponding pre-estimated failure rate as a target equipment type (S102); and redetermining a failure rate of the target equipment type according to the importance value, a cost value, a time value, a mass value, the allocation failure rate and the corresponding pre-estimated failure rate of the target equipment type (S103).

IPC Classes  ?

• G06Q 10/06 - Resources, workflows, human or project managementEnterprise or organisation planningEnterprise or organisation modelling

Abstract

The purpose of the present invention is to provide a cabin door driving assembly, an undercarriage cabin door assembly, and a cabin door driving assembly design method. In order to achieve the purpose, the cabin door driving assembly comprises an actuating unit and a pair of pull rods; the actuating unit comprises a rod member capable of linear displacement; one end of each pull rod and an end portion of the rod member are connected to each other in a relatively rotatable manner, and the other end of each pull rod is used for being connected to a cabin door. The cabin door driving assembly in this configuration is simple in structure, and easy to implement and assemble. In addition, compared with a mode in which a plurality of connecting points are arranged in an existing cabin door driving assembly, the number of connecting points in the cabin door driving assembly described in the present application is less, and compared with an existing solution, the later damage probability of the cabin door driving assembly is lower, so that the maintenance cost can be reduced.

IPC Classes  ?

• B64C 25/00 - Alighting gear
• B64C 25/16 - Fairings movable in conjunction with undercarriage elements

Abstract

A rudder pedal assembly used for controlling a flight vehicle, and the flight vehicle. The rudder pedal assembly comprises a first rudder pedal unit (11), a second rudder pedal unit (13), and a trimming return drive and damping module (12), wherein the trimming return drive and damping module is arranged between the first rudder pedal unit and the second rudder pedal unit, and is connected to the first rudder pedal unit and the second rudder pedal unit by means of corresponding coupling connecting rods (6); the first rudder pedal unit and the second rudder pedal unit each comprise a pair of pedals (1) and a spring (2), the spring being capable of providing corresponding force sense feedback in response to the action of the pedals; and the trimming return drive and damping module comprises a spindle (21), and a trimming return-drive electric motor (4) and a damper (10) which are connected to the spindle in parallel, the trimming return-drive electric motor and the damper being distributed to the first rudder pedal unit and the second rudder pedal unit.

IPC Classes  ?

• B64C 13/04 - Initiating means actuated personally

Abstract

A bidirectional swirl mixing device for an air source system heat exchanger of an aircraft, comprising an outer sleeve (20) and an inner sleeve (40). The inner sleeve (40) is arranged within the outer sleeve (20) and the two sleeves are spaced apart from each other. The mixing device further comprises: multiple outer ring stator blades (30) which are spaced apart and fixedly connected to the inner wall surface of the outer sleeve (20) and the outer wall surface of the inner sleeve (40); and multiple inner ring stator blades (50), which are spaced apart and fixedly connected to the inner wall surface of the inner sleeve (40). The outer ring stator blades (30) and the inner ring stator blades (50) are arranged at different angles relative to the longitudinal axis of the inner sleeve (40). When the outer ring blades and the inner ring blades incline in opposite directions relative to the longitudinal direction, the bidirectional swirl mixing device can enable airflow passing through the inner ring blades and the outer ring blades to rotate in opposite directions, so that the two strands of airflow are wound and mixed, and the temperature field is quickly and efficiently homogenized.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned

Abstract

The present invention provides a load diversion method for a ram air turbine system and a load diversion device. Acquiring data of a turbine disc surface airflow influencing a ram air turbine of an aircraft, detecting the load information of an electrical generator of the ram air turbine system, analyzing and calculating the power supply capability of the ram air turbine system on the basis of the above data, and, analyzing and calculating the power demand of an emergency load on the basis of the load information of an electrical generator, so that the storage battery connected to the main power grid of the aircraft and the ram air turbine system is matchingly charged and discharged with the power supply capability of the electric generator of the ram air turbine system and the power demand of the emergency load.

IPC Classes  ?

• H02J 9/06 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over

Abstract

A trimming-type tailplane connection structure (100), comprising: a tailplane upper mounting frame (111) and a tailplane lower mounting frame (112), the tailplane upper mounting frame (111) and the tailplane lower mounting frame (112) being mounted and connected to the body (200) of an aircraft; tailplane supporting beams (120) for connecting the tailplane upper mounting frame (111) to the tailplane lower mounting frame (112) and supporting same to form a frame plane, the tailplane supporting beams (120) serving as a part of a vertical load transfer system to transfer a vertical load component force, and also serving as a part of a heading load transfer system to transfer a heading component force; a heading linkage (130) for serving as a part of the heading load transfer system to transfer a heading component force, and also serving as a part of the vertical load transfer system to transfer a vertical load component force; and a linkage joint (140) and lateral linkages (150), the linkage joint (140) being provided at the portion where the tailplane upper mounting frame (111) is connected to the tailplane lower mounting frame (112), the two lateral linkages (150) being connected to the linkage joint (140), and the linkage joint (140) and the lateral linkages (150) serving as a part of a lateral load transfer system to transfer a lateral load component force, wherein the vertical load transfer system, the heading load transfer system and the lateral load transfer system are independently provided.

IPC Classes  ?

• B64C 5/02 - Tailplanes
• B64C 1/26 - Attaching the wing or tail units or stabilising surfaces

Abstract

An aircraft flap (10) that excludes an actuation structure providing an air jet. The aircraft flap comprises at least one side-edge opening that is connected to one or more air channels for directing an airflow in and/or out to reduce the structural strength of a vortex system of a side edge of the flap, wherein the air channel passes through a first surface and a second surface of the flap, and thus a first side-edge opening is formed in the first surface, and a second side-edge opening is formed in the second surface; and one of the first surface and the second surface is a side surface (11) of the flap, and one of the first side-edge opening and the second side-edge opening is a side-surface opening (110, 120). The aircraft flap can reduce aerodynamic loss while ensuring a noise reduction effect, and has a simple structure and good practicability.

IPC Classes  ?

• B64C 21/02 - Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
• B64C 9/14 - Adjustable control surfaces or members, e.g. rudders forming slots

Abstract

A venting device for an auxiliary tank of an aircraft. The venting device is configured to maintain the gas pressure of a fuel-free space in the auxiliary tank, and is characterized in that same comprises a vent pipe for the auxiliary tank, wherein the vent pipe for the auxiliary tank is connected between the auxiliary tank and wing tanks arranged on aircraft wings, so that the fuel-free space in the auxiliary tank is in fluid communication with fuel-free spaces in the wing tanks; and a vent valve, which is arranged midway in the vent pipe for the auxiliary tank, wherein the vent valve is opened or closed or the opening degree thereof is adjusted according to the magnitude of the pressure difference between the fuel-free space in the auxiliary tank and the environment outside an aircraft.

IPC Classes  ?

• B64D 37/02 - Tanks

Abstract

A fly-by-wire flight backup control system and method. The fly-by-wire flight backup control system may comprise a backup sensor module (120) and a backup control computer (130), which is coupled to the backup sensor module (120), wherein the backup control computer (130) receives a state signal of a main control channel (101); the main control channel (101) generates a control command on the basis of a sensor signal from a main control sensor module (112), so as to control a main control servo actuation module (114); and when the state signal of the main control channel (101) that is received by the backup control computer (130) indicates that the main control channel (101) fails, the backup control computer (130) supplies power to the backup sensor module (120) and a backup servo actuation module (140), and generates a control command on the basis of a sensor signal received from the backup sensor module (120), so as to control the backup servo actuation module (140).

IPC Classes  ?

• G05B 9/03 - Safety arrangements electric with multiple-channel loop, i.e. redundant control systems

Abstract

Provided in the present invention is a time division multiplexing circuit for cables of a starting-generation system of an aircraft, wherein the starting-generation system of the aircraft comprises a starter-generator control unit (SGCU), an auxiliary starter-generator (ASG) and a rack distribution panel (RDP). The time division multiplexing circuit comprises: a first group of cables, which connects an SGCU to an RDP, and a second group of cables, which connects the RDP to an ASG, wherein in a starting stage, an SGCU excitation line comprises the first group of cables from the SGCU to the RDP, and the second group of cables from the RDP to the ASG; and in a generation stage, a generator output feed line comprises the second group of cables from the ASG to the RDP, and a voltage detection line comprises the first group of cables from the SGCU to the RDP. In addition, further provided in the present invention is a time division multiplexing method for cables of a starting-generation system of an aircraft. By means of the present invention, the number and length of cables of a starting-generation system of an aircraft can be significantly reduced, thereby reducing the total weight of the cables of the starting-generation system.

IPC Classes  ?

• H02P 9/30 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
• H02P 9/02 - Arrangements for controlling electric generators for the purpose of obtaining a desired output Details
• H02P 101/30 - Special adaptation of control arrangements for generators for aircraft

Abstract

A lock-latch mechanism apparatus, comprising a latch mechanism (10), a lock mechanism (20), and a linkage mechanism (30). The latch mechanism (10) comprises a latch shaft (11) rotatably mounted to a cabin door body. The lock mechanism (20) comprises a lock shaft (21) rotatably mounted to the cabin door body, the lock shaft (21) being configured so that the axis of the lock shaft (21) is fixed with respect to the axis of the latch shaft (11). The linkage mechanism (30) comprises a driven member (31) fixedly connected to the latch shaft (11) and a driving member (32) fixedly connected to the lock shaft (21), the driven member (31) comprising a latched driven end part (31a) and an unlatched driven end part (31b), and the driving member (32) driving the driven member (31) to rotate. A latching and locking method using the aforementioned lock-latch mechanism apparatus, and an unlatching and unlocking method using the aforementioned lock-latch mechanism apparatus are used, which implements that a cabin door must be latched before same can be locked during a closing process, and the cabin door must be unlocked before same can be unlatched during an opening process.

IPC Classes  ?

• E05B 15/00 - Other details of locksParts for engagement by bolts of fastening devices
• E05B 65/00 - Locks for special use

Abstract

A windshield wiper device and a windshield cleaning system comprising same. The windshield wiper device (100) comprises: a wiper arm (10); an electric motor (20), wherein the electric motor (20) is used for driving the wiper arm (10) around a pivot point in a reciprocating manner; a wiper blade (30), wherein the wiper blade (30) is attached to the wiper arm (10) so as to wipe a windshield along with the reciprocating movement of the wiper arm (10), the wiper blade (30) is of a two-section structure and comprises a first-section wiper blade (31) and a second-section wiper blade (32), and the first-section wiper blade (31) and the second-section wiper blade (32) are connected to each other by means of a pivoting device (50); and a control device (40), wherein the control device (40) enables the second-section wiper blade (32) to rotate about the pivoting device (50) between a folded state in which the second-section wiper blade is attached to the first-section wiper blade (31) and an unfolded state in which an angle is formed between the second-section wiper blade and the first-section wiper blade (31). By means of the two-section windshield wiper device, the windshield wiping area is greatly increased, and the defect of a windshield wiper not being able to wipe all the visual field protection areas of pilots in the prior art is eliminated, such that the flight safety of an aircraft is ensured.

IPC Classes  ?

• B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
• B60S 1/36 - Variable-length arms
• B60S 1/38 - Wiper blades

Abstract

An aircraft leading edge assembly (10) having a leading edge end (11) facing a forward direction and a trailing edge end (12) facing away from the forward direction, the leading edge assembly comprising: a first bulkhead plate (110), a second bulkhead plate (120), a front spar (150), and a leading edge skin (130) which forms the leading edge end (11) of the leading edge assembly; and further comprising an auxiliary spar portion (200), wherein a first side (201) of the auxiliary spar portion is attached to the first bulkhead plate (110) and the leading edge skin (130), and a second side (202) of the auxiliary spar portion is attached to the second bulkhead plate (120) and the leading edge skin (130); the auxiliary spar portion (200) comprises a web (230), and the web (230) has a substantially flat web plane; and the first side (201) of the auxiliary spar portion is closer to the leading edge end than the second side (202) of the auxiliary spar portion, such that the web is inclined relative to a plane where the front spar is located. The aircraft leading edge assembly can improve the safety thereof against collisions with birds, reduce the weight of the leading edge assembly, and ensure that birds can slide away from the assembly.

IPC Classes  ?

• B64C 5/02 - Tailplanes
• B64C 5/06 - Fins
• B64C 3/28 - Leading or trailing edges attached to primary structures, e.g. forming fixed slots

Abstract

A core mold (20) for producing a hat-shaped reinforcement member. The core mold (20) can be laid in a stringer inner cavity (11) of a stringer (10), such that the stringer (10) and a skin (30) attached to an opening of the stringer inner cavity (11) can be formed into the hat-shaped reinforcement member. The core mold (20) comprises a vacuum bag layer (21) forming a core mold inner cavity (23) and an isolation layer (22) provided outside the outer surface of the vacuum bag layer (21), wherein the vacuum bag layer (21) has a thickness enabling the shape of the core mold (20) to be maintained under a normal temperature state, and the isolation layer (22) is made of an elastic material which is not adhesive to the stringer inner cavity (11). The core mold (20) can maintain the cross-sectional shape without the help of a foreign object, and has enough shape following capability in a length direction. After curing is completed, elasticity of the core mold (20) facilitates demolding thereof.

IPC Classes  ?

• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations

Abstract

An interactive retrieval method and apparatus, and a computer device and a storage medium, which belong to both the fields of computer software and avionics systems, and are used for improving the retrieval efficiency of electronic flight bags, guaranteeing flight operation safety, modernizing the flight operation of civil aircrafts, effectively ensuring flight safety, reducing the workload of pilots, improving the economic benefits of airlines, and also improving the core competitiveness of civil aircrafts. The method comprises: step S1, expanding, in combination with a knowledge graph, a query statement input by a user; step S2, selecting, from a document library, a plurality of documents that have a relatively high similarity with the expanded query statement, and returning the documents to the user; and step S3, adjusting the weight of each node in the knowledge graph according to a user behavior, so as to optimize a retrieval result.

IPC Classes  ?

• G06F 40/30 - Semantic analysis

Abstract

An aircraft propulsion system. The system comprises: a control apparatus, rotary power sets and fixed power sets, wherein the control apparatus is used for sending a target working mode to the rotary power sets and the fixed power sets according to an aircraft control instruction; the rotary power sets are used for adjusting, according to the target working mode, the directions and working states of all propellers in the rotary power sets; and the fixed power sets are used for adjusting, according to the target working mode, the working states of all propellers in the fixed power sets. By means of the aircraft propulsion system, there is no power deadweight in an aircraft control system, the weight of an aircraft is reduced, and flight control over the aircraft is optimized, thereby improving the utilization efficiency of the overall power system of the aircraft. Moreover, since the rotary power sets and the fixed power sets of the aircraft propulsion system are arranged in a distributed layout, the fault tolerance of the power system is improved, thereby ensuring the safety of the aircraft.

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
• B64C 3/32 - Wings specially adapted for mounting power plant

Abstract

The present invention relates to the technical field of composite material forming and provides a flexible carbon nanotube film self-heating platform for assisting in automated placement and a method, giving the surface of a placement tool a heating function, thereby reducing the difference between the placement tool and a placement process in temperature, and increasing the viscosity of a placement material, thus improving the placement effect. The platform comprises an automated placement mold, a carbon nanotube film, and a vacuum bag that are disposed sequentially from bottom to top; the carbon nanotube film is connected to a power source by means of wires; the vacuum bag is connected to a vacuuming device by means of a pipeline; the carbon nanotube film is of any area and covers a placement region of the automated placement mold; and the vacuum bag is bonded to the automated placement mold by a sealant and covers the region where the carbon nanotube film is located. The technical solution provided by the present invention is suitable for the process of automated fiber placement/automated tape placement.

IPC Classes  ?

• B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 65/30 - Electrical means
• H05B 3/34 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
• H05B 3/36 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs heating conductor embedded in insulating material

Abstract

Provided are an in-flight information assistance method and apparatus. The method comprises: obtaining target voice data (S102); segmenting the target voice data to obtain single voice data (S104); performing voice recognition according to the single voice data to generate text data (S106); displaying the single voice data and text data (S108). The invention solves the technical problem in the prior art that convenience and accuracy in obtaining control instructions are not adequate.

IPC Classes  ?

• G10L 15/26 - Speech to text systems
• G10L 15/04 - SegmentationWord boundary detection
• G08G 5/00 - Traffic control systems for aircraft

Abstract

A fly-by-wire flight control system and a control method. The fly-by-wire flight control system comprises: a cockpit control device used to provide a cockpit control instruction; an electronic flight control apparatus communicatively connected to the cockpit control device, receiving the cockpit control instruction from the cockpit control device, and generating a control instruction for controlling a flight control actuator assembly; and the flight control actuator assembly communicatively connected to the electronic flight control apparatus, receiving the control instruction for controlling the flight control actuator assembly, and causing a corresponding control surface of an aircraft to move. The electronic flight control apparatus comprises at least two main computers (1, 2, 3) and three secondary computers (4, 5, 6), and the secondary computers (4, 5, 6) correspond to individual control channels. The secondary computers (4, 5, 6) are configured to independently receive the cockpit control instruction from the cockpit control device and perform control rule computation on the instruction if the main computers (1, 2, 3) fail. The flight control actuator assembly is communicatively connected to each of the secondary computers (4, 5, 6), such that a minimum safety requirement of the aircraft is met when any one of the control channels is operating independently.

IPC Classes  ?

• B64C 13/50 - Transmitting means with power amplification using electrical energy
• G05B 15/02 - Systems controlled by a computer electric

Abstract

An on-board information assisting system and method, comprising: an obtaining module (10) obtains voice information, voice processing modules (21) and (22) convert the voice information into text information, and by means of an electronic flight bag (31) and an indication record system (32), the voice information and text information are displayed by means of a human-computer interaction interface (40); or a navigation system (30) receives a navigation instruction in the text information, for guiding flying. The present invention relates to the aviation field and aims at assisting a pilot to listen, replay and query air traffic control information in a flight task, improves convenience and accuracy for obtaining a traffic control instruction, reduces communication costs, and provides security guarantee for aircraft navigation.

IPC Classes  ?

• G10L 15/26 - Speech to text systems
• G08G 5/00 - Traffic control systems for aircraft
• B64D 47/00 - Equipment not otherwise provided for

Abstract

An airplane wing fuel tank access cover and a structure of a peripheral area of the access cover, relating to the technical field of aviation. The airplane wing fuel tank access cover comprises an inner access cover (7), an outer access cover (9), a sandwiched layer (73), a fixing member (77), and a fastening member (74). The inner access cover (7) is sealedly connected to an airplane wing lower wallboard (5) and the outer access cover (9) by means of the sandwiched layer (73); the fastening member (74) is provided in the inner access cover (7); the fixing member (77) passes through a fixing hole in the outer access cover (9) and is connected to the fastening member (74); and a wallboard access cover interlayer recessed area (6) of the airplane wing lower wallboard (5) provides a flat mounting area for the inner access cover (7) while ensuring that the outer access cover (9) is attached to the airplane wing lower wallboard (5). The metal outer access cover (9) ensures anti-impact and lightning protection requirements of the fuel tank access cover and plays a role in protecting the inner access cover (7) made of a composite material; moreover, the inner access cover (7) made of the composite material can effectively reduce the weight of a fuel tank access cover assembly and avoids galvanic corrosion caused by an access cover made of a single metal alloy.

IPC Classes  ?

• B64C 3/34 - Tanks constructed integrally with wings, e.g. for fuel or water
• B64D 37/04 - Arrangement thereof in or on aircraft

Abstract

A brake cooling fan device. A brake is used for aircraft wheels of an aircraft landing gear. The brake cooling fan device comprises a mechanical power device and a cooling fan assembly (2); the cooling fan assembly (2) comprises a fan rotating shaft (22) and a cooling fan (21) fixedly mounted on the fan rotating shaft (22); the mechanical power device drives the cooling fan assembly (2) to operate, so that the cooling fan (21) rotates along with the fan rotating shaft (22). The mechanical power device comprises aircraft wheels and a variable-speed transmission assembly (1); the variable-speed transmission assembly (1) is connected between the aircraft wheels and the cooling fan assembly (2); an input end of the variable-speed transmission assembly (1) is connected to the aircraft wheels in a transmission manner, and an output end of the variable-speed transmission assembly (1) is connected to the cooling fan assembly (2) in a transmission manner, so that rotating power of the aircraft wheels is delivered to the cooling fan assembly (2) by means of the variable-speed transmission assembly (1). An output rotating speed of the variable-speed transmission assembly (1) is larger than an input rotating speed of the variable-speed transmission assembly (1). By means of the brake cooling fan device, an aircraft can quickly pass through a station in the operation stage, and dispatching efficiency of the aircraft can be improved.

IPC Classes  ?

• B64C 25/42 - Arrangement or adaptation of brakes
• B60T 5/00 - Vehicle modifications to facilitate cooling of brakes

Abstract

Provided is an onboard device of an aircraft, the onboard device having a bus interface and a dedicated wireless transmission apparatus connected to the bus interface. The dedicated wireless transmission apparatus comprises an interface conversion module and a wireless transmission module, wherein the interface conversion module is configured to convert bus data received from the bus interface into a data packet that can be transmitted using radio access technology, and/or to convert a data packet received from the wireless transmission module into bus data corresponding to the bus interface; and the wireless transmission module is configured to use the radio access technology to transmit the converted data packet, and/or to receive the data packet transmitted using the radio access technology. In addition, further provided are a method and system for wireless interconnection between onboard devices. By means of the present invention, the number of cables of an airplane can be effectively reduced without affecting the structure of an original onboard device, thereby reducing the weight of the aircraft and saving the amount of space occupied by the cables.

IPC Classes  ?

• H04L 12/40 - Bus networks
• H04W 4/42 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for mass transport vehicles, e.g. buses, trains or aircraft

Abstract

A flap/slat control lever (500) for a high-lift system for an aircraft, comprising a handle (502); a pull rod (504); a light guide plate (506) with a position mark; a mechanical component (508) coupled to the pull rod; a rotating shaft (510) coupled to the mechanical component; and a first sensor unit (512_1) and a second sensor unit (512_2) coupled to the rotating shaft. The mechanical component is arranged to be coaxially linked to the first sensor unit and the second sensor unit by means of the rotating shaft. When the flap/slat control lever is moved, the first sensor unit and the second sensor unit simultaneously read the position of the flap/slat control lever, and respectively generate a first sensor unit output signal and a second sensor unit output signal on the basis of the read position of the flap/slat control lever for providing for corresponding first and second flap/slat electronic control devices (404_1, 404_2). Also disclosed are a flap/slat lever and a method for operating a flap/slat electronic control device.

IPC Classes  ?

• B64C 13/04 - Initiating means actuated personally
• B64C 13/50 - Transmitting means with power amplification using electrical energy

Abstract

Disclosed is a connecting device, the connecting device being used for connecting a panel and a guide rail, wherein the guide rail is provided with a plurality of openings in the direction of the guide rail, the connecting device comprises connecting modules (10), the connecting modules (10) are connected to the openings, the connecting modules (10) comprise a first connecting module (10S) and a second connecting module (10L), and the width of the second connecting module (10L) matches the width of the opening to limit the panel in the direction of the guide rail. According to the connecting device, flexible arrangement of a passenger service unit (PSU) on an azimuth of an airplane is facilitated, certain relative deformation between the inner side and the outer side of the guide rail of the passenger service unit (PSU) is allowed, the manufacturing and assembling process can be simplified, the manufacturing period of the passenger service unit (PSU) is shortened, tooling mold manufacturing is reduced, the production and manufacturing costs are reduced, the maintenance and use costs of the passenger service unit (PSU) are reduced, fasteners are reduced, and noise in a cabin can be reduced.

IPC Classes  ?

• B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for

Abstract

A method and a system for determining a laser tracker station, an electronic device (12), and a medium. The method for determining a laser tracker station position comprises: on the basis of a horizontal measurement point (P) of an aeroplane requiring whole-aeroplane horizontal measurement and preset laser tracker stations (STS1, STS2), determining a simulation device station of the aeroplane requiring whole-aeroplane horizontal measurement (S110); acquiring three-dimensional coordinate data of multiple reference points of the aeroplane requiring whole-aeroplane horizontal measurement (S120); and, on the basis of the simulation device station and the three-dimensional coordinate data of the multiple reference points, determining a laser tracker station of the aeroplane requiring whole-aeroplane horizontal measurement (S130).

IPC Classes  ?

• G01C 9/00 - Measuring inclination, e.g. by clinometers, by levels

Abstract

A flap slat control lever and a method for operating the lever are disclosed. The lever includes: a first displacement sensor to detect a displacement of the flap slat control lever and generate a first displacement detection signal; a second displacement sensor to detect the displacement of the flap slat control lever and generate a second displacement detection signal; a first control command module to receive the first displacement detection signal; and a second control command module to receive the second displacement detection signal, wherein the first control command module is in a standby state and the second control command module is in a working state.

IPC Classes  ?

• B64C 13/04 - Initiating means actuated personally
• B64C 13/50 - Transmitting means with power amplification using electrical energy
• G05B 9/03 - Safety arrangements electric with multiple-channel loop, i.e. redundant control systems
• G06F 7/02 - Comparing digital values

Abstract

Disclosed is a bogie landing gear (100), comprising a bogie (110), wherein the bogie (110) is connected to a bearing strut (112), at least two axles (111) are arranged on the bogie (110), and an airplane wheel (120) is installed on each of the axles (111). The bogie landing gear (100) further comprises an automatic sliding device (130). The automatic sliding device (130) comprises: a driving mechanism which is fixedly installed on the bogie (110) and comprises a first output shaft and a second output shaft that can move synchronously, wherein the first output shaft and the second output shaft are connected to a first transmission mechanism and a second transmission mechanism respectively so as to transmit output rotation to a first airplane wheel and a second airplane wheel; and a clutch mechanism (160) for enabling the first transmission mechanism and the second transmission mechanism to move between a first position and a second position, so that the first transmission mechanism and the second transmission mechanism are connected to or disconnected from the first airplane wheel and the second airplane wheel. In the structure of the bogie landing gear (100) of the structure, the improved automatic sliding device (130) structure is adopted, such that an automatic sliding operation of the bogie landing gear (100) is achieved. Further disclosed is an aircraft comprising the bogie landing gear (100).

IPC Classes  ?

• B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies

Abstract

A laser light source module (110), comprising: at least one laser light source (111); at least one optical fibre (113), arranged in the direction of transmission of the laser, the optical fibre (113) being positioned downstream of the laser light source (111), and one end of the optical fibre (113) being positioned to be aligned with the laser light source (111), such that the laser light emitted by the laser light source (111) is incident to the optical fibre (113); and a collimation system (114), arranged in the direction of transmission of the laser, the collimation system (114) being positioned downstream of the optical fibre (113), and being aligned with the other end of the optical fibre (118) to receive the laser from the optical fibre (113). The structure of the laser light source module (110) allows the number of laser light sources (111), such as laser diodes, to be increased according to requirements, and can thereby also effectively reduce the volume of the module. Also relating to a laser lamp comprising said module.

IPC Classes  ?

• F21S 8/00 - Lighting devices intended for fixed installation
• H01S 5/00 - Semiconductor lasers
• F21V 9/40 - Elements for modifying spectral properties, polarisation or intensity of the light emitted, e.g. filters with provision for controlling spectral properties, e.g. colour, or intensity
• F21W 107/30 - Use or application of lighting devices on or in particular types of vehicles for aircraft
• F21Y 115/30 - Semiconductor lasers

Abstract

An air preparation system (100), comprising an air inlet (110), an air outlet (120), a compression device (130) and a main refrigeration device (140), wherein the compression device (130) is arranged between the air inlet (110) and the air outlet (120) and is in fluid communication with the air inlet (110) and the air outlet (120), the compression device (130) pressurizes air flowing through the compression device (130), the main refrigeration device (140) is arranged between the compression device (130) and the air outlet (120) and is in fluid communication with the compression device (130) and the air outlet (120), the main refrigeration device (140) reduces the temperature of air flowing through the main refrigeration device (140), the compression device (130) is an electrically powered compression device (130), and the main refrigeration device (140) is an electrically powered heat exchange element. The air preparation system (100) can reduce a bleed air flow, the installation space and the weight of the system.

IPC Classes  ?

• B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned

Abstract

A carbon nanotube thin film/composite material forming method and a manufactured lightning protection structure. In the forming method, a low-cost liquid forming one-step method is adopted to integrally obtain an ultralight carbon nanotube thin film/composite material lightning protection structure. The lightning protection structure comprises: a carbon nanotube thin film used as a conductive layer, a composite material comprising fibers and a resin with which the fibers are filled, and an adhesive film used for electric insulation between the composite material and the carbon nanotube thin film, wherein the carbon nanotube thin film, the adhesive film, and the composite material are sequentially provided. The lightning protection structure can be integrally formed by means of the one-step method.

IPC Classes  ?

• B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
• B29C 70/36 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting
• B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced

Abstract

Disclosed is a wall plate structure for a composite-material stringer in the shape of the Chinese character "工", comprising several "C"-shaped overlays (5), an intermediate intercalation layer (6), a flange intercalation layer (8) and a skin overlay (10), wherein the "C"-shaped overlays (5) are laid side by side on the skin overlay (10), and closed portions of the "C"-shaped overlays (5) are in curing connection with the skin overlay (10); the intermediate intercalation layer (6) is provided in a gap between adjacent "C"-shaped overlays (5), and the intermediate intercalation layer (6) is in curing connection with the skin overlay (10); and the flange intercalation layer (8) is provided on the tops of the "C"-shaped overlays (5) and the intermediate intercalation layer (6) to jointly form an upper flange of a stringer in the shape of the Chinese character "工". A forming mold and forming method for the wall plate structure for a composite-material stringer in the shape of the Chinese character "工" are further disclosed. The "C"-shaped overlays and skin overlay of the wall plate structure for a composite-material stringer in the shape of the Chinese character "工" are completely attached, thus a bonding area is expanded and the bearing capacity of a stringer is increased while the amount of stringers manufactured is reduced. A detachable mold is used to support the "C"-shaped overlays, and thereby the problem of de-moulding of a composite-material stringer in the shape of the Chinese character "工" is solved, such that preparation of the stringer structure can be rapidly realized.

IPC Classes  ?

• B64C 3/18 - SparsRibsStringers
• B29C 33/42 - Moulds or coresDetails thereof or accessories therefor characterised by the shape of the moulding surface, e.g. ribs or grooves
• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core

Abstract

A mold, a fabrication method for an assembled preformed structure and a fabrication method for a wallboard structure, the mold for the preforming of a U-shaped stringer comprising a base (1), a rigid mold (2) and an elastic mold (3), wherein the rigid mold (2) is detachably arranged on the base (1); the rigid mold (2) is a U-shaped structure and is wrapped on three adjacent outer sidewalls of the base (1); the elastic mold (3) is placed on the rigid mold (2) and is a U-shaped structure; and the elastic mold (3) is wrapped on the outer sidewalls of the rigid mold (2).

IPC Classes  ?

• B29C 33/30 - Mounting, exchanging or centering
• B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
• B29B 11/06 - Making preforms by moulding the material
• B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
• B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof

Abstract

Provided are a sealing structure capable of pre-setting a gap, and a fastening method. The sealing structure capable of pre-setting a gap comprises a fixing structure (1) and an auxiliary structure (2), wherein the fixing structure (1) is used for pressing and limiting a part to be positioned, and for forming a finished hole (7) in a surface of said part; the auxiliary structure (2) is used for assisting the fixing structure (1) in carrying out auxiliary limitation on said part; and adjusting protrusions (4) for pre-setting a gap are arranged on side walls of end faces, which cooperate with each other, of the fixing structure (1) and the auxiliary structure (2). Drilling and assembly precision can be ensured by providing the adjusting protrusions of a pre-set thickness on a working face of the sealing structure according to requirements; a gap between a sealing angled sheet and a stringer web (5) can be controlled by means of the adjusting protrusions; and the sealing angled sheet is made of glass fiber material, which is structurally lighter than an aluminum alloy material, such that a design requirement for lightning protection between a composite-material stringer and a metal wing rib (6) is met.

IPC Classes  ?

• B64C 3/18 - SparsRibsStringers

Abstract

A connecting corner box for the root part of a civil aircraft wing upper panel. The connecting corner box comprises a bottom side (9), an upright side (10) and reinforcing ribs (11), wherein the bottom side (9) is provided with notches (93), one side of the upright side (10) is connected to the notches (93) by means of the reinforcing ribs (11), and the notches (93) are used for inserting T-type stringer webs of an outer wing panel. Further provided are a connecting structure for the root part of a civil aircraft wing upper panel and a wing. The present invention reduces the number of structural members, simplifies assembly and improves assembling efficiency.

IPC Classes  ?

• B64C 1/26 - Attaching the wing or tail units or stabilising surfaces

Abstract

Provided is an ice crystal detector, comprising an axially extending ice crystal collection probe and a detection device. The ice crystal collection probe comprises a windward surface on one side and a leeward surface opposite to the windward surface, and comprises a rod body, a groove positioned on the windward surface and extending in an axial direction of the rod body, and a photoelectric sensor mounted at one end or both ends of the rod body. The groove comprises an opening and a bottom. The photoelectric sensor forms an optical path in the groove which is spaced from the bottom of the groove for monitoring ice crystals on the bottom of the groove. A controller is connected to the photoelectric sensor and determines whether an ice crystal icing condition exists according to the change of an electric signal fed back by the photoelectric sensor. The rod body also comprises a plurality of airflow channels, an inlet of each airflow channel is positioned at the bottom of the groove of the ice crystal collection probe, and an outlet thereof is positioned on the leeward surface of the ice crystal collection probe. The ice crystal detector is simple in structure, high in reliability, easy to realize and low in electric power consumption, and can detect whether an ice crystal icing condition exists in the air.

IPC Classes  ?

• B64D 15/20 - Means for detecting icing or initiating de-icing
• G01V 8/10 - Detecting, e.g. by using light barriers

Abstract

A method of determining a design allowable for compression of a composite material T-bar, the method taking into account an impact on a web plate edge causing BVID, obtaining an effect on bar carrying capacity of different profile parameters, ply proportions and a hot and humid environment of the T-bar, and calculating an influence factor thereof, while also taking into account the effects of different material batches and furnace times, finally determining, by means of statistics and analysis of compression experimental data of a beam, a design allowable for compression of a composite material T-Bar.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

A test method for pin load distribution measurement for a mechanical connection structure, relating to the field of mechanical devices and mechanical tests. The method comprises: on the upper surface and the lower surface of the mechanical connection structure, respectively providing multiple strain measurement devices (6) between every two adjacent fasteners (4); providing a mounting space for the strain measurement devices (6) between two connected members (3) in contact with each other; mounting the multiple strain measurement devices (6) in the mounting space; measuring loads of section transfer between every two adjacent fasteners (4); and obtaining a pin load distribution measurement result of the mechanical connection structure. A layout space is provided for strain measurement devices (6) such as strain gauges to obtain upper and lower surface strain distributions of the connected members (3) on the sections between two fasteners (4). The magnitude of the loads of the given sections of the connected members (3) can be completely obtained by means of test measurement, thereby avoiding the uncertainty caused by introducing an analysis method.

IPC Classes  ?

• G01L 1/22 - Measuring force or stress, in general by measuring variations in ohmic resistance of solid materials or of electrically-conductive fluidsMeasuring force or stress, in general by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress using resistance strain gauges
• G01L 1/00 - Measuring force or stress, in general

Abstract

Disclosed is an upper wall end and wall plate connection integral corner box assembly, comprising an outer corner box (7) for fixing a composite-material test article, and several inner independent small corner boxes (8) for cooperating with the outer corner box (7) to fix the composite-material test article, wherein the outer corner box (7) is arranged on an outer side of a composite-material test article wall plate (9), the several inner independent small corner boxes (8) are symmetrically arranged on an inner side of the composite-material test article wall plate (9), and the outer corner box (7) and the several inner independent small corner boxes (8) are arranged symmetrically. According to the connection integral corner box assembly, based on the performance difference between a composite material and a metal material, the structural details of an upper wall end and wall plate connection corner box are improved, thereby improving the force transmission effect between a metal corner box and a composite-material wall plate, and eliminating the risk of potentially damaging the test article. Meanwhile, a notch is designed at either end of the corner box, thereby achieving the effects of reducing the weight and making the assembly of a front beam corner box and a rear beam corner box more coordinated.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems
• G01M 13/00 - Testing of machine parts

Abstract

Disclosed is a backup statically indeterminate hanging structure of an aircraft, the structure comprising a left wall plate, a right wall plate, a hanging middle connector tab, and a lateral connecting rod. A side wall plate tab and a short beam middle connector tab (2) are superimposed together back-to-back in order to jointly transmit a heading load and a vertical load. When one tab is damaged, the other tab transmits the loads to ensure that the load of a hanging middle connector remains unchanged. Meanwhile, a wing hanging middle connector has a split design, thereby avoiding the overall failure of the wing hanging connector caused by crack growth. The side wall plate tab and a hanging short beam tab of the hanging structure form a redundancy design, and the single lateral connecting rod (3) is composed of two connecting pieces and forms a backup design, thereby facilitating a reduction in a concentrated force load of a wing lower wall plate, and further reducing the weight of a wing lower wall plate assembly.

IPC Classes  ?

• B64D 47/00 - Equipment not otherwise provided for
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting

Abstract

A box section docking assembly and docking method and application therefor for different load levels. The box section docking method comprises the steps: using the docking assembly for connecting a body box section and a fake piece box section; docking a wall plate and a wing spar of the body and the fake piece in a cross-section manner, docking the wing spar in a double shear form, and connecting the docked inner side of the wall plate by a corner tab. The method is simple in assembly, and convenient in operation. In addition, a box section test is more stable and safer by adopting a double shear structure during docking, and the risk of the failure of a composite material is reduced.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems

Abstract

A connection structure for connecting a composite-material aircraft wing spar to a wing root region. The wing spar is C-shaped, and consists of a wing spar web (1), a wing spar upper edge bar (2.1), and a wing spar lower edge bar (2.2). The composite-material wing spar is fabricated by means of manual laying, automated tape laying in conjunction with hot diaphragm forming, automated fiber laying, etc. The wing spar is connected to both an outer wing wall plate and a connector by means of fasteners. At a connection position of the wing spar and wing root, the wing spar is truncated in advance according to connection requirements so as not to be directly connected to the wing root, a wing rib, or a central wing spar. In addition, cutting is performed on an end portion, and an edge region is rounded in order to prevent stress being concentrated at a region having a variable cross-section region during load transfer. The connection structure simplifies a force transmission path of a web, improves the load transferring efficiency of the web, reduces the number of fasteners, and reduces assembly difficulty.

IPC Classes  ?

• B64C 3/18 - SparsRibsStringers

Abstract

The present invention provides a method for monitoring delamination damage in a composite laminate structure, comprising: A plurality pairs of piezoelectric transducers are arranged on the composite laminate structure to form corresponding plurality of monitoring paths, and each pair of the piezoelectric transducers forms one monitoring path, wherein each each pair of the piezoelectric transducers comprises a pair of excitation end transducers and a pair of measurement end transducer, wherein two piezoelectric transducers in the pair of the excitation end transducers and in the pair of the measurement end transducers are symmetrically arranged on the upper and lower surfaces of the composite laminate structure; Exciting each pair of the excitation end transducers by using Lamb waves; Sampling response signals at each pair of the measurement end transducers; And determining whether there is delamination damage in the composite laminate structure and/or the position of the delamination damage on the basis of the response signals. The present invention further provides a corresponding device.

IPC Classes  ?

• G01N 29/04 - Analysing solids
• G01N 29/07 - Analysing solids by measuring propagation velocity or propagation time of acoustic waves

Abstract

An anti-misoperation device for an aircraft passenger cabin door. The anti-misoperation device for an aircraft passenger cabin door comprises a guiding groove (6), a rocker (8), a torsion spring (11), a clamp hook (12), a spline shaft (13), a rocker arm bushing (15) and a rolling shaft (17), wherein the rolling shaft (17) is rigidly connected onto one end of the rocker (8), and may move in the guiding groove (6) against an inner wall of the guiding groove (6); one end of the torsion spring (11) acts on a first cabin door frame (1), and the other end of the torsion spring (11) acts on the clamp hook (12); the spline shaft (13) is rigidly connected to the other end of the rocker (8), and the clamp hook (12) is rigidly connected to the spline shaft (13), such that the rocker (8), the spline shaft (13) and the clamp hook (12) may rotate coaxially; and the rocker arm bushing (15) is mounted on a latch shaft (2) of a lifting system for the aircraft passenger cabin door, is rigidly connected to the latch shaft (2), and may thus rotate coaxially with the latch shaft (2). The described anti-misoperation device for the aircraft passenger cabin door has a relatively simple structure, and may effectively prevent the cabin door in an open state from being closed by a mis-operation of a person on an aircraft.

IPC Classes  ?

• B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens

Abstract

A main power feeder-based power supply system and method for reducing the direct-current starting power generation of an aircraft. The structure of the system is as follows: a first single-pole double-throw switch (43), a starting control contactor (41) and a second single-pole double-throw switch (44) are arranged at two ends of a main power feeder (60) used for supplying power between a starting controller (30) and a three-phase alternating-current starting power generator (110); during the starting and power generation stages, the reuse of the main power feeder (60) is realized by means of controlling the first single-pole double-throw switch (43), the starting control contactor (41) and the second single-pole double-throw switch (44), so that the quantity of main power feeders (60) is reduced. By using the technical solution, the reuse of the main power feeders is realized, the quantity of main power feeders is reduced, the power density of a starting power generation system is increased, the usage amount of main power feeder cables is reduced by 40%, and the purpose of aircraft weight reduction can be achieved.

IPC Classes  ?

• H02P 25/30 - Arrangements or methods for the control of AC motors characterised by the kind of AC motor or by structural details characterised by the circuit arrangement or by the kind of wiring the motor being controlled by a control effected upon an AC generator supplying it

Abstract

Disclosed are an aircraft engine suspension and a suspension box section (100) thereof. The suspension box section (100) comprises: a body; and a suspension-engine connection part and a suspension-wing connection part formed in the body. An engine of an aircraft is connected to the suspension box section (100) through the suspension-engine connection part. The suspension box section (100) is connected to a wing or a fuselage of the aircraft through the suspension-wing connection part. The body of the suspension box section comprises: an upper wall plate (120), a bottom plate and side wall plates (130). The bottom plate is arranged to be opposite to the upper wall plate (120); and the side wall plates (130) are connected between the upper wall plate (120) and the bottom plate, wherein the upper wall plate (120) is composed of at least two plate portions and is formed into a raised structure.

IPC Classes  ?

• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B64D 27/06 - Aircraft characterised by the type or position of power plants of piston type within, or attached to, wings

Abstract

A hole wall thickness measuring device, comprising hooks, a bias spring, a measuring rod, and a measuring rod sleeve. The measuring rod comprises a measuring part and an operating part. The measuring part comprises a conical section, and an actuating member is provided at the operating part. The measuring rod sleeve is provided outside the measuring rod and is provided with a main scale. The hooks have measuring surfaces and are connected to the measuring rod sleeve by means of the bias spring. The bias spring radially biases the hooks inwards such that the hooks fit on the conical section. The hooks can radially extend out or retract in holes provided at corresponding positions on the measuring rod sleeve along with the axial movement of the conical section. The measuring device of the present invention can stably hook the inner side of a hole wall to facilitate measurement.

IPC Classes  ?

• G01B 5/06 - Measuring arrangements characterised by the use of mechanical techniques for measuring length, width, or thickness for measuring thickness

Abstract

A flap retraction and releasing apparatus (100), comprising: a support base (3), which is arranged along an air flow and can be fixedly connected to a fixed trailing edge of an aircraft wing; a first rotating shaft (6), which is rotatably mounted to the support base; a swing arm (5), one end (51) of the swing arm being fixedly connected to the first rotating shaft; a connecting rod (4), one end (41) of the connecting rod being pivotedly connected to the other end (52) of the swing arm, and a spherical hinge (411) being provided at the other end (42) of the connecting rod; and an auxiliary bearing member (1), which is provided with three spherical hinges (111) distributed in a triangular shape, the auxiliary bearing member being connected to the support base by means of one of the three spherical hinges, wherein the spherical hinge on the connecting rod and the other two spherical hinges of the three spherical hinges on the auxiliary bearing member are all connected to the lower side of an aircraft flap. The flap retraction and releasing apparatus has a simple structure and is easy to control; the structure is compact, so that the apparatus is light; it can be ensured that a fairing is provided along the air flow, and the size of the fairing is effectively reduced.

IPC Classes  ?

• B64C 13/24 - Transmitting means

Abstract

A coupling device for inner and outer flaps, comprising: a piston cylinder assembly (2); a piston rod assembly (1), which is provided in the piston cylinder assembly and is radially fixed and axially movable relative to the piston cylinder assembly; an arc-shaped wedge member (3), which is fixed to the outer side of the piston cylinder assembly and comprises a first wedge squeezing surface (7); a concave ring (4), which is fixed to the outer side of the piston rod assembly and comprises a second wedge squeezing surface (8). When the first wedge squeezing surface is in contact with the second wedge squeezing surface, an axial force is generated, realizing forward buffering. The coupling device for the inner and outer flaps can realize an overtravel forward buffering function and is simple in structure and easy to mount and maintain.

IPC Classes  ?

• B64C 9/26 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by multiple flaps

Abstract

A flap/slat control lever (200) and a method for operating the lever. The lever comprises: a first displacement sensor (204), used to detect displacement of the flap/slat control lever and to generate a first displacement detection signal; a second displacement sensor (205), used to detect the displacement of the flap/slat control lever and to generate a second displacement detection signal; a first control command module (CCM1), used to receive the first displacement detection signal; and a second control command module (CCM2), used to receive the second displacement detection signal, wherein the first control command module is in a standby state, and the second control command module is in an active state. The first control command module sends the first displacement detection signal to the second control command module. The second control command module compares the first and second displacement detection signals, and if the difference between the first and second displacement detection signals is within an acceptable error margin, the second control module sends the first or second displacement detection signal to a slat flap control computer (SFCC) to serve as a control signal for controlling operation of a flap and slat. The use of multiple displacement sensors and multiple control command modules ensures that a pilot can, under any anticipated operating conditions, operate a flap/slat control lever to output an available command signal to a high lift system, thereby reducing the likelihood of system failure.

IPC Classes  ?

• B64C 13/00 - Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
• G06F 7/02 - Comparing digital values

Abstract

The present invention relates to a pixel subdivision load transfer method and system. The pixel subdivision load transfer method comprises: obtaining surface pressure distribution data, the data being in the form of surface elements and corresponding pressure; subdividing surface element pixels into subdivision surface elements which are small enough; allocating the subdivision surface elements to corresponding structure bearing points; integrating the subdivision surface elements allocated to the same structure bearing point into concentrated force and moment, and transferring the concentrated force and moment to the structure bearing point; comparing load distribution before the transfer with load distribution after the transfer to obtain a difference, and determining whether the difference is less than given tolerance; if the difference is less than the given tolerance, obtaining a final load; and if the difference is greater than or equal to the given tolerance, continuing performing pixel subdivision on the surface elements, and repeating the subsequent steps until the final load is obtained. The pixel subdivision load transfer method and system of the present invention can achieve the following beneficial technical effects: transferring a pneumatic surface load onto a structure node, and achieving conservation before and after the transfer, and a precise match of load distribution.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

An electric pedal control device for an aircraft. The device comprises several pedal transmission assemblies. Each of the pedal transmission assemblies comprises a motor (1), an elastic connector (3), a transmission mechanism, an angular displacement sensor (5), and a pedal, and the angular displacement sensor (5) is employed to acquire rotation position information of the pedal. Rotation kinematic pairs (6) of the transmission mechanisms in the the pedal transmission assemblies are connected by means of a mechanical connecting rod mechanism (7) to enable linkage. A controller of the electric pedal control device is configured to receive the rotation position information, and control, according to the rotation position information, the motor (1) to produce a damping action on the elastic connector (3). The electric pedal control device simplifies a design of the transmission mechanism, reduces the volume, is easy to maintain, facilitates reconstruction when a single-point failure occurs, and improves dispatching efficiency.

IPC Classes  ?

• B64C 13/04 - Initiating means actuated personally
• B64C 13/24 - Transmitting means

Abstract

In the technical field of dynamics tests, provided is a strain sensor optimization arrangement method based on a virtual test, comprising: a step of representing, by using a Delta function, whether there is a strain sensor; a step of performing transient response analysis during the random movement of an applied impact load acting point; and a step of obtaining an optimal arrangement scheme for the strain sensor using a genetic optimization algorithm by taking the minimization of the total number of sensors and the maximization of a 2-norm of the sum of strain of impact responses as optimization targets. The beneficial effects of the method are that: a Delta function is used to characterize whether there is a strain sensor, wherein same is practical; based on a genetic algorithm, an impact load acting point can randomly move between skinning nodes, so that a strain sensor optimization arrangement result is universal; an optimization target is simple and easy to define and describe; and compared with traditional sensors, at least half of the sensors can be saved on in terms of arrangement number.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

A negative pressure low dead oil anti-bubble aeroplane fuel tank apparatus, comprising a fuel tank outer shell, an oil suction hose (3) arranged inside the fuel tank outer shell, a fueling port (9) arranged on the fuel tank outer shell, and a fuel outlet (2), the aeroplane fuel tank apparatus also comprising an anti-surge baffle (4); there is at least one anti-surge baffle; the anti-surge baffle divides the internal space of the aeroplane fuel tank apparatus into at least two spaces, any two adjacent spaces being in communication by means of a communication opening (8) arranged on the bottom of the anti-surge baffle; the aeroplane fuel tank apparatus uses the pressure difference in adjacent spaces to introduce fuel into a low pressure oil supply space, and uses an inclined surface (1) inside the aeroplane fuel tank apparatus so that the fuel flows automatically to the lower side under the force of gravity.

IPC Classes  ?

• B64D 37/08 - Internal partitioning
• B64D 37/06 - Constructional adaptations thereof

Abstract

An aircraft cockpit view enhancement system and method. The aircraft cockpit view enhancement system has: front-position, left-position and right-position camera devices. The front-position camera device is arranged between a driver's eye position point and an aircraft windshield pillar, with a photographing angle directly facing the aircraft windshield pillar, and the left-position and right-position camera devices are respectively arranged at a left side and a right side of the aircraft windshield pillar, with photographing angles respectively pointing to the right side and the left side deviated from the aircraft windshield pillar. An image processing device for performing image synthesis and image registration on a front-position image, a left-position image and a right-position image photographed by the front-position camera device, the left-position camera device and the right-position camera device, to obtain an image of a region shielded by the aircraft windshield pillar.

IPC Classes  ?

• B64D 47/08 - Arrangements of cameras
• G06T 3/00 - Geometric image transformations in the plane of the image
• G06T 7/30 - Determination of transform parameters for the alignment of images, i.e. image registration
• G06T 7/13 - Edge detection
• G09F 9/30 - Indicating arrangements for variable information in which the information is built-up on a support by selection or combination of individual elements in which the desired character or characters are formed by combining individual elements

Goods & Services

Starters for motors and engines; aeroplane engines; dynamos; Pistons being parts of machines and engines; Cylinders for motors and engines; Pumps being parts of machines, engines or motors; Valves being parts of machines; Compressors being machines; Propulsion mechanisms other than for land vehicles, namely, propellers; Ball bearings being parts of machines; Road rollers; Hoists; Metalworking machines; Igniting devices for internal combustion engines of land vehicles; Machine tools, namely, lathes; Hand-held tools, other than hand-operated, namely, electric drills and electric hammers Vehicles for locomotion by land, air, water or rail, namely, cars, motorcycles, airplanes, boats, and railway rolling stock; Cars; Electric motors for land vehicles; Anti-theft devices for vehicles; Cycle cars, namely, motorcycles; Bicycles; Funicular railcars; Luggage trucks, namely, vehicles for carrying luggage; Airplane tires for airplane wheels; Aeronautical apparatus, machines and appliances, namely, airplane propellers; Air vehicles in the nature of aircraft; Aeroplanes; Boats Providing information about the repair of airplanes; Road paving; Electric appliance installation and repair; Machinery installation, maintenance and repair; Interference suppression services for electrical apparatus; Installation, maintenance and repair of computer hardware; Motor vehicle maintenance and repair; Gas station services, namely, vehicle fueling services; Airplane maintenance and repair; Shipbuilding; Retreading of tires; Disinfecting; Burglar alarm installation and repair Global transportation of freight for others by all available means; Transportation information; Freighting services; Wrapping of goods for baggage protection during travel; Boat rental; Air transport; Piloting; Car parking; Storage of goods; Parcel delivery; Travel reservation services, namely, making reservations and bookings for transportation

Goods & Services

Vehicles for locomotion by land, air, water or rail, namely, cars, motorcycles, airplanes, boats, and railway rolling stock; Cars; Electric motors for land vehicles; Cycle cars, namely, motorcycles; Bicycles; Funicular railcars; Luggage trucks, namely, vehicles for carrying luggage; Airplane tires for airplane wheels; Aeronautical apparatus, machines and appliances, namely, airplane propellers; Air vehicles in the nature of aircraft; Aeroplanes; Boats Providing information about the repair of airplanes; Electric appliance installation and repair; Machinery installation, maintenance and repair; Interference suppression services for electrical apparatus; Installation, maintenance and repair of computer hardware; Motor vehicle maintenance and repair; Gas station services, namely, vehicle fueling services; Airplane maintenance and repair; Shipbuilding; Burglar alarm installation and repair

Goods & Services

Vehicles for locomotion by land, air, water or rail, namely, cars, motorcycles, airplanes, boats, and railway rolling stock; Cars; Electric motors for land vehicles; Cycle cars, namely, motorcycles; Bicycles; Funicular railcars; Luggage trucks, namely, vehicles for carrying luggage; Airplane tires for airplane wheels; Aeronautical apparatus, machines and appliances, namely, airplane propellers; Air vehicles in the nature of aircraft; Aeroplanes; Boats

Abstract

A photocatalytic honeycomb assembly and a photocatalytic purification apparatus, which can maximally increase a contact area between polluted air and a photocatalyst while maximally ensuring that the surface of the photocatalyst receives sufficient irradiation of ultraviolet light, and can also make the flow resistance to air flowing in a channel meet requirements in the field of ventilation systems which have high requirements on flow resistance. The photocatalytic honeycomb assembly is formed of one or more photocatalytic honeycomb cores and a photocatalytic honeycomb assembly housing. The one or more photocatalytic honeycomb cores are arranged in a honeycomb form. The photocatalytic honeycomb core is formed of three or more basic core units and a light guide member that is Y-shaped in an end view.

IPC Classes  ?

• A61L 9/20 - Ultraviolet radiation
• A61L 9/18 - Radiation
• B01D 53/86 - Catalytic processes
• B01D 53/88 - Handling or mounting catalysts
• F24F 3/16 - Air-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by purification, e.g. by filteringAir-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by sterilisationAir-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by ozonisation
• B01J 35/00 - Catalysts, in general, characterised by their form or physical properties
• B01J 35/04 - Foraminous structures, sieves, grids, honeycombs
• B60H 3/00 - Other air-treating devices

Abstract

A safety belt and an identification method based on a safety belt in the field of safety belts. The safety belt comprises: a fingerprint reading device (3) configured to recognize a received user operation to obtain fingerprint information, and to send the fingerprint information and a seat number corresponding to the fingerprint reading device (3) to a processing module (4); the processing module (4) configured to compare the received fingerprint information with the seat number, and to form opening information or closing information according to comparison result and send the same to a buckle locking mechanism (2); and the buckle locking mechanism (2) configured to control opening of the buckle (1) based on the opening information or to control closing of the buckle (1) based on the closing information. By embedding the fingerprint reading device (3) into the buckle (1) of the safety belt, the passenger's fingerprint information can be collected, thereby conveniently, quickly and safely determining whether the passenger corresponds to the seat number, preventing unlawful actors from boarding so as to avoid security risks.

IPC Classes  ?

• B60R 22/48 - Control systems, alarms, or interlock systems, for the correct application of the belt or harness

Abstract

A ventilating and lighting apparatus (100) for an individual cabin can improve a contact area between air and a photocatalyst and ensure sufficient light irradiation on the surface of the photocatalyst, and implements rational utilization of an internal space of a cabin by combining with a lighting system. The apparatus (100) comprises an apparatus body housing (110) and an individual lighting assembly (120); a space enclosed by an inner circumferential surface of the apparatus body housing (110) and an outer circumferential surface of the individual lighting assembly (120) constitutes a ventilating flow passage (140); the ventilating flow passage (140) has an air supply inlet (141) and an air supply outlet (142); air from an upstream air inlet component flows from the air supply inlet (141) into the ventilating flow passage (140), and is exhausted from the air supply outlet (142) to an air environment where the individual cabin is located; the inner circumferential surface of the apparatus body housing (110) is coated with a photocatalyst coating (160); a photocatalyst exciting light source (150) is disposed on the outer circumferential surface of the individual lighting assembly (120); air flowing in the ventilating flow passage (140) is purified by means of photo-catalytic oxidation.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
• B60Q 3/20 - Arrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors for lighting specific fittings of passenger or driving compartmentsArrangement of lighting devices for vehicle interiorsLighting devices specially adapted for vehicle interiors mounted on specific fittings of passenger or driving compartments

Abstract

A system for manual laying process control, and a laying method therefor. The system mainly consists of a dynamic laser projection device (1) and a manual laying tool that is provided with a signal emitting head. Bar codes of cut pieces can be scanned by using the dynamic laser projection device (1), so as to determine whether the cut pieces are consistent to laying boundaries (3) of the cut pieces of a projection; in addition, by means of the dynamic laser projection device (1), information such as the laying starting region (4), the sequential compaction region (6) and the shearing opening position (7) can be sequentially and dynamically projected; relevant operations are performed in a corresponding region by using the manual laying tool provided with a signal emitting head; the dynamic laser projection device (1) analyzes and determines whether relevant operations are completed by sensing signals emitted by the signal emitting head; further, a corresponding region to be operated in a next step is projected. By means of the system, the whole manual laying process is controlled, the uniformity of laying layers among products can be effectively ensured; meanwhile, the consistency of the designed laying layer and the manufactured laying layer can be ensured, thereby reducing the impacts of artificial factors on the laying quality.

IPC Classes  ?

• B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core

Abstract

Provided is a preforming method for a double-bag thermal diaphragm made of composite material. The method mainly relates to the technical field of composite material preforming. The method comprises: first, packaging a prepreg laying layer in double diaphragm bags consisting of an inner diaphragm bag and an outer diaphragm bag; and then, mounting the double diaphragm bags comprising the prepreg laying layer on a preforming device, and preforming the double-bag thermal diaphragm. During the preforming process of the double-bag thermal diaphragm, by controlling the pressure in the inner diaphragm bag and the pressure in the outer diaphragm bag, the normal pressure outside the surface of the prepreg laying layer is decreased zero, and the prepreg laying layer is preformed by using the preforming device, so as to prepare and obtain a preformed product of a composite material. In the method, the normal pressure outside the surface of the prepreg laying layer is decreased to zero, interlayer slipping of fiber laying layers is effectively promoted, defects such as fiber buckling and wrinkles are avoided, the control process of a double-diaphragm preforming technology is effectively simplified, and the existing preforming device does not need to be specially transformed.

IPC Classes  ?

• B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations

Abstract

An illumination device for passengers comprises a substrate (1) for fixed mounting and a reading light source (10) disposed on the substrate (1). The illumination device for passengers further comprises at least one first light distribution unit and a light guide (26) integrated into the illumination device for passengers. Each first light distribution unit comprises a first scenario light source (22) independent of the reading light source (10) and at least one first light distribution curved-surface (24) facing the first scenario light source (22). The first light distribution curved-surface (24) guides light, emitted by the first scenario light source (22), to the light guide (26), such that the light guide (26) enables scenario lighting. In addition to providing passengers with functional lighting for reading, the illumination device for passengers achieves an improved integrated effect by adapting lighting to different user scenarios.

IPC Classes  ?

• F21S 8/10 - specially adapted for vehicles
• F21V 3/04 - GlobesBowlsCover glasses characterised by materials, surface treatments or coatings
• F21V 13/02 - Combinations of only two kinds of elements
• F21V 33/00 - Structural combinations of lighting devices with other articles, not otherwise provided for
• F21W 101/08 - Interior lights
• F21Y 115/10 - Light-emitting diodes [LED]

Abstract

The present invention provides a dewatering device for an air-conditioning system of a plane, comprising: one or more filter plates disposed within a mixing cavity of an air-conditioning system of a plane, for filtering liquid-state water in mixed air in the mixing cavity, wherein the filter plates are configured to be inclinable relative to an axis of the mixing cavity, and an inclination angle thereof is adjustable so as to change a filtering amount of the mixed air.

IPC Classes  ?

• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• B01D 46/00 - Filters or filtering processes specially modified for separating dispersed particles from gases or vapours
• B01D 46/10 - Particle separators, e.g. dust precipitators, using filter plates, sheets or pads having plane surfaces
• B01D 46/46 - Auxiliary equipment or operation thereof controlling filtration automatic
• B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
• G05D 22/02 - Control of humidity characterised by the use of electric means
• F24F 3/14 - Air-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by humidificationAir-conditioning systems in which conditioned primary air is supplied from one or more central stations to distributing units in the rooms or spaces where it may receive secondary treatmentApparatus specially designed for such systems characterised by the treatment of the air otherwise than by heating and cooling by dehumidification
• B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
• F24F 13/04 - Air-mixing units

Abstract

An airplane wing assembly includes a wing, a winglet and a connection element. The wing has a wing box. The wing box is located at a wing tip of the wing and the winglet is connected with the wing by the wing box. The connection element includes a butt joint rib, which is assembled with the wing box, and a center connection, which is assembled with the winglet. The butt joint rib has a first shearing pin hole and a second shearing pin hole, into which are press fitted a corresponding first and a second shearing pin respectively to form interference fit. The center connector has a first sleeve hole and a second sleeve hole.

IPC Classes  ?

• B64C 3/52 - Warping
• B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
• B64C 3/18 - SparsRibsStringers
• B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided forHandling, transporting, testing or inspecting aircraft components, not otherwise provided for