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 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

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

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

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 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

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

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

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

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

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

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

Abstract

A linkage mechanism for controlling an aircraft landing gear hatch door includes a primary torsion tube having a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch. A first drive apparatus transfer the driving force of a landing gear support column to the primary torsion tube. A secondary torsion tube has an inner end portion located inside the hatch and an outer end portion located outside the hatch. A second drive apparatus is located outside the landing gear hatch and connects the primary torsion tube and the secondary torsion tube outside the hatch. Two third drive apparatuses are connected between the inner end portion of the secondary torsion tube and one of the hatch doors.

IPC Classes  ?

• B64C 25/20 - Operating mechanisms mechanical
• B64C 25/16 - Fairings movable in conjunction with undercarriage elements
• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like

Abstract

A buffering apparatus for a landing gear buffering strut and a method for using same in an air-oil buffering strut. The buffering strut (200) comprises an outer cylinder (201) and an inner cylinder (205) able to move along the inside wall of the outer cylinder (201); the buffering apparatus comprises: at least one excitation component, arranged on the inner side of the wall of the outer cylinder (201) of the buffering strut (200); at least one induction component, arranged in the inner cylinder (205) of the buffering strut (200) to respond to the excitation of the excitation component, such that the inner cylinder (205) moves along the inside wall of the outer cylinder (201) of the buffering strut (200) and produces buffer damping; a control unit, used for controlling the excitation component in real time on the basis of a motion signal of the buffering strut (200); and a sensing component, arranged on the lower end of the buffering strut (200) to detect the motion signal of the buffering strut (200) and to feed the motion signal back to the control unit. The semi-active control method of the present buffering apparatus is beneficial for adaptation to more complex external conditions, improves the buffering efficiency of an aircraft on landing, and, by using an excellent control algorithm, further enhances the safety and comfort of the aircraft landing process.

IPC Classes  ?

• B64C 25/60 - Oleo legs
• F16F 9/50 - Special means providing automatic damping adjustment

Abstract

Provided is an airplane suspension (20) fairing structure with a wing-mounted arrangement, the fairing structure comprising a front fairing located in front of the leading edge (31) of a wing and a rear fairing located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front fairing is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front fairing of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the fairing aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.

IPC Classes  ?

• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings
• B64C 7/02 - Nacelles
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting

Abstract

A wind shear detection method based on energy management, a wind shear detection device (300), and a wind shear detection monitoring device (400). The method comprises: A, calculating a correction coefficient γ of a wind strength factor f(t) according to residual energy ΔEA of an airplane and current energy EA of the airplane; B, correcting the wind strength factor f(t) into γ·f(t) according to the correction coefficient γ of the wind strength factor; C, calculating average wind field integral strength according to the corrected wind strength factor γ·f(t); and D, determining a wind shear warning signal on the basis of the average wind field integral strength. A wind shear strength calculation method and an airplane maximum available energy management method are combined, the wrong alarm rate and the false alarm rate of low-altitude wind shear dangerous flight condition detection are effectively lowered so as to prevent a pilot from wrongly executing a wind shear circumvention guide operation, and flight safety and economy can be improved.

IPC Classes  ?

• G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H)

Abstract

An airplane wing assembly comprises a wing (20), a winglet (10) and a connection element. The wing is provided with a wing box. The winglet is located at a wing tip of said wing (20) and is connected with the wing (20) by the wing box. Said connection element comprises a butt joint rib (1) which is assembled with the wing box and a central connector (9) which is assembled with the winglet. Said butt joint rib (1) is provided with a first and a second shearing pin holes (31) which are used to be pressed into a first and a second corresponding shearing pins (3) respectively to form interference fit. Said central connector (9) is provided with a first and a second sleeve holes (51, 61).

IPC Classes  ?

• B64C 3/52 - Warping

Abstract

Disclosed is a dewatering device (10) for an air conditioning system in an aircraft, comprising: one or more filter plates (2) located in a mixing chamber of the air conditioning system in the aircraft for filtering liquid water in mixed air in the mixing chamber, and the filter plates (2) are configured to be inclined relative to the shaft of the mixing chamber, and the inclination angle thereof is adjustable so as to change the filtration capacity for the mixed air.

IPC Classes  ?

• 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

Abstract

A testing device for operating force and corresponding displacement of a multi-degree-of-freedom side lever (300). The testing device comprises: the side lever (300), which comprises a side lever bottom plate (304); a side lever clamp unit (200), which is used to clamp the side lever (300); a manually driven measurement device (100), which comprises a mounting bracket unit (101) and a handle unit (103), wherein the mounting bracket unit (101) is connected to the side lever bottom plate (304) to support the side lever (300), and the handle unit (103) is mounted at the top of the mounting bracket unit (101) and used to simulate movement of the side lever (300) corresponding to a pitch axis or a roll axis of an aircraft; a tilt angle sensor (108), which is arranged at the top of the side lever clamp unit (200) and used to collect angles of the pitch axis or the roll axis of the aircraft; and a tension and pressure sensor (105), which is arranged on the side of the side lever clamp unit (200) and connected to the handle unit (103), and used to collect operating force of the pitch axis or the roll axis of the aircraft, wherein the tension and pressure sensor (105) is arranged perpendicularly to the axis of the side lever (300). The testing device can accurately obtain data of the operating force and corresponding displacement of the side lever (300).

IPC Classes  ?

• G05B 23/02 - Electric testing or monitoring

Abstract

The present invention provides a recess filling slat for an airplane wing, comprising: a deployable leading edge slat; and at least one recess filling element, movable between an internal folding position of the deployable leading edge slat and an external deploying position of the deployable leading edge slat, the at least one recess filling element being built to move from the folding position to the deploying position during deployment of the deployable leading edge slat, so as to form the recess filling slat together with the leading edge slat. The present invention further provides a low-noise high-lift system for an airplane wing and a method for reducing airplane noise related to a high-lift system. While ensuring a requirement for pneumatic performance of a high-lift system in a low speed state and saving precious space at a leading edge of a fixed wing, the present invention deploys a recess filling element to mitigate or shield a major sound source area of a leading edge slat.

IPC Classes  ?

• B64C 9/24 - Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap

Abstract

A front installation node is suitable for integral forming with a front end frame of an aircraft pylon and includes a first lug and a second lug, each respectively protruding outwardly from one of the two sides of the frond end frame; a first connecting rod and a second connecting rod, one end thereof being respectively connected to the first lug and the second lug, and the other end thereof being respectively suitable for connecting to an aircraft engine. The first connecting rod can pivotally connect to the first lug at a first connection point. The second connecting rod and the second lug are respectively connected at a second connecting point and a third connecting point. Using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.

IPC Classes  ?

• B64D 27/26 - Aircraft characterised by construction of power-plant mounting

Abstract

An integrated pylon structure for a propulsion system is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure includes a pylon box section (110) formed from an upper and a lower bean, a frame (100) and a side wall panel. The pylon structure has a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood having a front fixed hood (301) and a rear movable hood (302). A guide rail allows the rear movable hood to slide and open relative to the pylon box section. The engine thrust reverser hood is directly connected to the side wall of the pylon box section and a guide rail on the side wall guides the opening of the thrust reverser hood.

IPC Classes  ?

• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• F02K 1/72 - Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
• B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings

Abstract

Disclosed is a connecting rod mechanism (100) for controlling an aircraft landing gear hatch door, comprising: a primary torsion tube (10) comprising a first portion located inside a landing gear hatch and a second portion outside the landing gear hatch; a first drive apparatus connected between the first portion and a support column (201) of a landing gear (200) so as to transfer the driving force of the support column to the primary torsion tube (10); a secondary torsion tube (20) comprising an inner end portion located inside the hatch and an outer end portion located outside the hatch; a secondary drive apparatus connecting the primary torsion tube (10) and the secondary torsion tube (20) outside the hatch; and two third drive apparatuses respectively connected between the inner end portion of the secondary torsion tube (20) and one of the hatch doors. The second drive apparatus is located outside the landing gear hatch, saving on space inside the hatch, and reducing interference between motion mechanisms. A single side of the secondary torsion tube (20) transfers torque so that synchronism of the hatch door is high. The number of components is reduced and power transmission performance is high.

IPC Classes  ?

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

Abstract

A nose cone structure for a pylon (20) of an aircraft with a wing-hung layout. The nose cone comprises a front nose cone (21) located in front of a wing leading edge (31) and a rear nose cone (22) located behind the wing leading edge (31). The nose cone is characterized in that at least a part of the rear nose cone (22) is modeled and shaped by cross section control lines and comprises at least one group of horizontal position control lines (P01, P02, P03, P04) and at least a group of longitudinal position control lines (S01, S02, S03, S04, S05). The rear nose cone of the pylon is shaped by horizontal position control lines. The pylon design of the present application optimizes the passageway area of the space between the pylon/wing/engine nacelle by controlling the rear nose cone curvature of the pylon without deflection of the rear portion of the pylon.

IPC Classes  ?

• B64C 7/02 - Nacelles
• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings

Abstract

Provided is an airplane suspension (20) cowling structure with a wing-mounted arrangement, the cowling structure comprising a front cowling located in front of the leading edge (31) of a wing and a rear cowling located at the back of the leading edge (31) of the wing; the vertical section line (G) of the front cowling is curved, ascending along air flow direction from a start point (p) of an engine nacelle (10) to the maximum height position and then descending and extending below the lower surface (32) of the wing. In the present invention, due to the curved vertical section line of the front cowling of the suspension, inner space of the suspension is met only in the position requiring greater inner space, thus enabling the engine to be mounted close to the wing without additional devices; and the cowling aerodynamic surface of the suspension will not extend to the upper surface of the wing, avoiding interference of the suspension with the wing during cruising.

IPC Classes  ?

• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings

Abstract

The present invention provides a method of passive noise reduction for an aircraft leading-edge slat. The method comprises the following steps: mounting a first piezoelectric sensor on an inner surface of a slat slot of a leading-edge slat so as to use the piezoelectric effect to absorb the mechanical energy of impact with airflow eddies and convert the mechanical energy to electrical energy; and providing a piezoelectric shunt circuit module and electrically connecting same to the first piezoelectric sensor, thereby dissipating the electrical energy in the form of heat. The present invention also provides a method for actively reducing noise and a method for integral passive and active reduction of noise for an aircraft leading-edge slat. The present invention can effectively control the aerodynamic noise of a slat while not generating relatively large alterations to conventional high-lift device design, and will not affect the aerodynamic performance of a high-lift device and the safety of the aircraft.

IPC Classes  ?

• B64C 21/00 - Influencing air flow over aircraft surfaces by affecting boundary layer flow

Abstract

A system for measuring the waviness of an aircraft surface and a corresponding method. The system comprises the following components: a laser contour scanning module for emitting laser to an aircraft surface, for receiving laser reflected back from the aircraft surface, and for obtaining the data representing the cross-sectional contour of the aircraft surface; a digital signal processor for processing the data from the laser contour scanning module and obtaining data that can be processed by a waviness calculation module; said waviness calculation module for calculating the waviness of the aircraft surface according to the processed data representing the cross-sectional contour of the aircraft surface. The system can instantaneously obtain the waviness information of a cross section of the aircraft body surface being measured with no contact required. The information collection process is quick and efficient, and can effectively avoid errors generated during the data collection process.

IPC Classes  ?

• G01B 11/30 - Measuring arrangements characterised by the use of optical techniques for measuring roughness or irregularity of surfaces

Abstract

A fuselage butt joint structure (10) connected to an aircraft vertical fin, the fuselage butt joint structure (10) comprising: a structural main body (20) provided with a plurality of reinforcing ribs (21); and a plurality of joints (30), the joints (30) being installed back-to-back in pairs at the front side and rear side of the structural main body (20); two ends of each joint (30) are respectively provided with reinforcing ribs (31); the reinforcing ribs (31) of the joint (30) are connected to the reinforcing ribs (21) of the structural main body (20) via fasteners; and the aircraft vertical fin is installed onto the joint via fasteners. The fuselage butt joint structure of the present invention has performance against fatigue, and is easy to maintain.

IPC Classes  ?

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

Abstract

A force transducer (100) and large-load measuring method capable of multi-angle calibration for an airplane; the force transducer (100) is adapted to be installed on a connector of an airplane structure, and comprises: a cylindrical pin (1) having an axial straight groove (11) and an annular groove (13) perpendicular to the straight groove on the wall of the pin; a pin base (2) provided with a lead hole (21) communicating with the straight groove (11); a first strain meter (3) located at the intersection of the straight groove (11) and the annular groove (13); a second strain meter (4) located in the annular groove (13) and forming a central angle of 90° with the first strain meter (3); and a first strain meter connecting line (31) and a second strain meter connecting line (41) electrically connected to an external sensing signal acquisition instrument; and the length directions of the first strain meter (3) and the second strain meter (4) are consistent with the axial direction of the pin (1). Data sensed by the force transducer (100) can be used to determine the magnitude and direction of a load borne by an airplane structure, and can be used to sense a large load.

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 5/00 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes

Abstract

Disclosed is an integrated pylon structure for a propulsion system, wherein it is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure comprises a pylon box section (110) formed from an upper and a lower beam, a frame (100) and a side wall panel (102). The pylon structure further comprises a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood comprising a front fixed hood (301) and a rear movable hood (302). The thrust reverser hood connection structure comprises at least one guide rail used for guiding the rear movable hood to make the rear movable hood slide and open relative to the pylon box section. The engine thrust reverser hood is directly connected to the side wall of the pylon box section and the opening of the thrust reverser hood is guided by means of the guide rail on the side wall, thus a guide rail beam is eliminated, which saves on space while meeting the installation requirements of an engine and reduces the weight of the entire propulsion system.

IPC Classes  ?

• B64D 29/02 - Power-plant nacelles, fairings or cowlings associated with wings
• F02K 1/76 - Control or regulation of thrust reversers

Abstract

Disclosed is a front installation node integrated with an aircraft pylon. The front installation node is suitable for integral forming with a front end frame (100) of an aircraft pylon and comprises: a first lug (10) and a second lug (20), both respectively protruding outwardly from two sides of the front end frame; and a first connecting rod (70) and a second connecting rod (80), one end thereof being respectively connected to the first lug and the second lug, and the other end thereof being respectively suitable for connecting to an aircraft engine, wherein the first connecting rod can pivotally connect to the first lug at a first connection point (1), the second connecting rod and the second lug are respectively connected at a second connecting point (2) and a third connecting point (3). The front installation node for engine is integrated with the pylon frame, saving on weight; and using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.

IPC Classes  ?

• B64D 27/26 - Aircraft characterised by construction of power-plant mounting

Abstract

An aircraft turning over-travel detection device (100) comprises: an over-travel push rod (20) and a detection assembly, the detection assembly comprising a target (40), a proximity sensor (30), a sleeve (60), an energy storage spring (50), a connecting rod (70) and a linkage clamp hook (80). When a turning over-travel occurs, the over-travel push rod (20) releases the linkage clamp hook (80) to loosen the connecting rod (70), the connecting rod (70) drives the target (40) to move towards the proximity sensor (30) under the action of the energy storage spring (50), and the proximity sensor (30) detects the position of the target (40), and transmits a signal to an aircraft control system. The aircraft turning over-travel detection device easily detects a turning over-travel, and does not easily generate misdetection and false alarm; it does not damage a target during a detection process, and a state in which an over-travel occurs is locked in a mechanical mode; and it is easy for the aircraft crew to discover a turning over-travel, and can perform manual reset.

IPC Classes  ?

• G01B 21/22 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapersMeasuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for testing the alignment of axes
• B64C 25/50 - Steerable undercarriagesShimmy-damping

Abstract

Disclosed is a rudder pedal control device for an airplane, wherein a brake pedal connecting rod thereof can be shortened and is provided with a first sensor, and a brake sensing signal is generated by the first sensor when the brake pedal connecting rod is compressed because there is no rotation of a brake pedal crank relative to a rudder pedal control rocking arm. The rudder pedal control device comprises a second sensor for sensing the relative rotation between the brake pedal crank and the rudder pedal control rocking arm; a speed comparator for comparing the current speed of the airplane with a predetermined speed; and a controller for electrically connecting the first sensor, the second sensor and the speed comparator, and shielding the brake sensing signal generated by the first sensor when the second sensor senses that there is no rotation of the brake pedal crank relative to the rudder pedal control rocking arm and the current speed compared by the speed comparator is greater than the predetermined speed.

IPC Classes  ?

• B64C 13/04 - Initiating means actuated personally

Abstract

Disclosed is an aeroplane airfoil leading edge structure to satisfy an anti-bird impact function. The structure comprises three parts: a metal panel (1), a honeycomb sandwich layer (2) and a composite material lining (3), wherein the three parts are laid together from outside to inside and formed by co-curing in an autoclave. The leading edge structure merely requires the aforementioned three components, thereby reducing manufacturing costs while also increasing structural rigidity, strength and impact resistance, thus enabling the leading edge structure to convert the kinetic energy of a bird into plastic deformation of the structure when subjected to a bird impact.

IPC Classes  ?

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

Abstract

Disclosed is an ice detector comprising: an ice assembly (1), at least one vision sensor (31) and a controller (5). The ice assembly (1) comprises an ice rod (11) having an icing surface and a support structure (12), and a cooling element connected with the ice rod (11) and the the support structure (12). The vision sensor (31) is arranged so as to be able to acquire an image of the icing surface. The controller (5) is electrically connected to the vision sensor (31) and comprises an image comparison module (510) for comparing the acquired image with an initial image, thereby judging whether or not the icing surface of the ice rod is icing up. The ice detector has a simple structure, is small in volume, is lightweight, is highly reliable and is easily mounted and arranged on an aircraft.

IPC Classes  ?

• B64D 15/20 - Means for detecting icing or initiating de-icing

Abstract

An integrated design method for an airplane nose having a single curved surface windshield, comprising the following steps: extracting a Catia forming parameter according to an airplane nose design constraint; establishing an airplane nose parameterized curved surface model, and generating a curved surface in the following order: generating an upper main curved surface (ICLJ) on one side of the airplane nose; cutting a windshield area on the upper main curved surface; firstly generating a main windshield curved surface (CERM) and then generating a lateral windshield curved surface (MRFD) in the windshield area; generating a transition curved surface (ACDB) between the main windshield curved surface and the remaining upper main curved surface (IABHJ) after the windshield area is cut; generating an upper front curved surface (EGHF) on one side of the airplane nose; and sequentially generating the remaining curved surfaces on one side of the airplane nose: a lower main curved surface (OPQN), a lower back curved surface (NOKJ), and a lower front curved surface (GPO); and symmetrically generating curved surfaces on the other side of the airplane nose. The upper main curved surface integrally generated with the cutting method ensures the curvature of the upper main curved surface to have high level continuity, thus facilitating integrated manufacturing; and ensures that the airplane nose has good aerodynamic characteristics and flow performance, thus reducing fuel consumption.

IPC Classes  ?

• B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
• G06F 17/50 - Computer-aided design

Abstract

A silencer comprises a shell (21), a vent pipe (22) and baffles (23). The shell (21) is in the cylindrical shape; the vent pipe (22) is provided with a sound attenuation part (24) and a connection part (25). The sound attenuation part (24) is positioned in the shell (21); the sound attenuation part (24) and the shell (21) jointly define a cavity (26) between the shell (21) and the sound attenuation part (24); and the sound attenuation part (24) is provided with a plurality of through holes which penetrate through a pipe wall. The connection part (25) is used for being connected onto the corresponding connection part of a sound source. The baffles (23) are porous, are arranged in the cavity (26) and divide the cavity (26) into at least two compartments. According to the silencer of this disclosure, the noise of a vent system is lowered, the weight of the baffles is reduced, and smoke blockage in the use process of the silencer is avoided.

IPC Classes  ?

• F01N 13/00 - Exhaust or silencing apparatus characterised by constructional features
• F01N 13/08 - Other arrangements or adaptations of exhaust conduits
• F01N 99/00 - Subject matter not provided for in other groups of this subclass

Abstract

A device and method for measuring dynamic resistance coefficient of rubber sealing element, the device comprising a machine base (1), a horizontal direction dragging device (51-54), a vertical direction motive power loading device (61-64), a measuring platform (3) with rolling wheels, a platform guide rail (4), a high and low temperature test box (2), a first force sensor (7), a second force sensor (8) and a microcomputer (9) with data processing program. In the method, a loading head (64) is driven by a servo motor, which is controlled by the microcomputer, to carry out a horizontal and a vertical loading on the sealing element clamped on the platform in a temperature box, and the force sensors are used for measuring the positive pressure in the vertical direction and the friction force in the horizontal direction. The device and the test method can measure the dynamic resistance of the sealing element under different loading and temperature conditions, and have the characteristics that the measurement is convenient and fast, the data is precise, and the like.

IPC Classes  ?

• G01N 19/02 - Measuring coefficient of friction between materials

Abstract

A device for measuring high and low temperature durability of sealing member, which mainly comprises a main machine base (1), a high and low temperature testing box (2), a loading device, a test table (3), a pressure sensor (5) and a microcomputer (6) with a data processor. A servo motor (41) is used to load a test piece through a transmission mechanism (42), a vertical press block (43) and a loading head (44). A loading force is measured by the pressure sensor (5) and the measuring signal is fed back to the microcomputer (6) in real time, and a result is displayed in real time. Compared with a traditional durability tester or a fatigue tester the device has a controllable testing temperature, a long loading stroke and a large loading force range. The device is suitable for measuring durability of rubber sealing parts of various types at different temperature.

IPC Classes  ?

• G01N 3/34 - Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by mechanical means, e.g. hammer blows

Abstract

A refrigeration system (200) for aircraft is provided, which includes: a first stage heat exchanger (102) for receiving hot bleed air from an engine; a second stage heat exchanger (106) with an inlet communicated with an outlet of the first stage heat exchanger (102) and an outlet communicated with an inlet of a mixing chamber; a valve (204) is arranged between the outlet of the second stage heat exchanger (106) and the inlet of the mixing chamber; sensors (210, 212) senses at least the temperature of environment air; and a controller (120) receives parameter from the sensors (210, 212) which are compared with a stored preset range, if the parameter is within the preset range, the controller (120) opens the valve (204), and the hot bleed air enters into the mixing chamber after passing through the first stage heat exchanger (102), the second stage heat exchanger (106) and the valve (204) in order. The refrigeration system (200) can save energy and improve economic performance.

IPC Classes  ?

• B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
• F25B 11/00 - Compression machines, plants or systems, using turbines, e.g. gas turbines
• F25B 9/00 - Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point

Abstract

The present invention provides a spoiler for a hatch door on an aeroplane, which spoiler is installed on the inner covering of the hatch door, inside the wind-facing leading edges of the front hatch door on the left and right of the front landing gear of the aeroplane, and is tightly assembled with the inner covering of the hatch door, so as to reduce the force required to open the hatch door. The present invention also provides a hatch door on an aeroplane, which hatch door has the spoiler for a hatch door on an aeroplane of the present invention installed on the inner covering thereof. The spoiler according to the present invention can effectively reduce the force required to open the hatch door, requires little modification to the original mechanism, and is convenient to install and maintain.

IPC Classes  ?

• B64C 1/38 - Constructions adapted to reduce effects of aerodynamic or other external heating

Abstract

An icing detector probe includes three sections arranged sequentially along the direction of air flow, namely, a first section, a second section and a third section. The shape of the outer surface of the first section is suitable for collecting droplets in the air flow. The shape of the outer surface of the second section is suitable for full decelerating and releasing latent heat of large droplets during their movements. The outer surface of the third section is suitable for icing of large droplets. The probe detects icing by distinguishing and identify large droplets icing. The probe effectively detects types of traditional icing, thus being helpful for exact detection of icing thickness. An icing detector including said icing detector probe is also provided.

IPC Classes  ?

• B64D 15/20 - Means for detecting icing or initiating de-icing

Abstract

Disclosed is a telescopic tool for fuel oil precipitate discharge, comprising an initiating apparatus, a collecting bowl (3), a telescopic rod and a locking device (10) and a sheet iron bucket with a magnetic base (12). Use of the telescopic tool for fuel oil precipitate discharge enables a fuel oil precipitate discharge valve on an aircraft to be opened and the precipitate discharged from the precipitate discharge valve to be collected and guided into the underlying sheet iron bucket. The telescopic rod is composed of inner and outer sleeved rods, connected by the locking device (10). When the locking device is unlocked, the inner sleeved rod (8) slides in the outer sleeved rod (9), and when the locking device is locked, the inner sleeved rod expands to be locked within the outer sleeved rod in any position. The fuel tank precipitate discharge apparatus has the function of a high degree of freedom of adjustment, can be adapted to the requirements of wings of different heights, and can accomplish fuel oil precipitate discharge without requiring manual lifting.

IPC Classes  ?

• B64D 37/22 - Emptying systems facilitating emptying in any position of tank

Abstract

Disclosed is a tool for aircraft fuel oil precipitate discharge, which is used within an aircraft wing rectifier hump for opening an aircraft fuel oil precipitate discharge valve to discharge precipitate in a fuel tank. The tool for aircraft fuel oil precipitate discharge comprises: an initiating apparatus, a lighting apparatus, a collecting bowl, a rod and a support plate, etc. Since the tool of the present invention is fixed by means of the support plate, no manual lifting is required in use, thus the operation thereof saves on work and is simpler. Furthermore, the tool contains the support plate and a support spring and by using the tool, the amount of fluid in the collecting bowl varies to balance with the force of the support spring, achieving the function of self-regulating the flow through the fuel oil precipitate discharge valve, thereby avoiding overflow of fuel oil.

IPC Classes  ?

• B64D 37/20 - Emptying systems

Abstract

The present invention provides a composite material single-spar structure for a transonic flutter model consisting of a non-metallic core material and a single closed-cell thin-walled casing laid over the outer layer of the core material, characterized in that the casing has a rectangular chamfered closed cross-sectional shape, and is formed from the composite material laid alternately at ±α degrees and 0 degrees, wherein laying at 0 degrees represents laying the composite material along a direction perpendicular to the cross section. Using the single-spar structure of the present invention can effectively satisfy the requirements for strength and cross-sectionally varying stiffness of a transonic flutter model. The present invention also provides a corresponding calculation method for cross-sectional stiffness of the single-spar structure. Data relating to cross-sectional dimensions for realizing a target stiffness design can be quickly acquired by means of this calculation method.

IPC Classes  ?

• G06F 17/50 - Computer-aided design

Abstract

A freezing condition detector (10), comprising: a sensor element (1) that includes a temperature sensing layer (5) and a heat-insulation layer (6), the temperature sensing layer (5) being embedded with resistance wires, and the heat-insulation layer (6) being fixed on the inner surface of the temperature sensing layer (5); a temperature sensor (2) for measuring the real-time temperature of the sensor element (1); and a controller (3). The controller includes: a heating control module (7) for heating resistance wires at a constant electric power, such that the temperature of the sensor element (1) is above 0°C; a data storage module (8) for storing target temperature values of the sensor element (1) in different flight conditions, and for collecting real-time temperature values of the sensor element (1) measured by the temperature sensor (2); a processor (9) for searching the data storage module (8) for the target temperature value of the sensor element (1) in a flight condition, comparing the target temperature value to the real-time temperature value, and determining that an airplane is in freezing conditions if the real-time temperature value is smaller than the target temperature value. Also disclosed is a freezing condition detection method using the freezing condition detector (10).

IPC Classes  ?

• B64D 15/20 - Means for detecting icing or initiating de-icing

Abstract

Provided is a substrate (10) for an air intake throttle. The substrate (10) is provided with two surfaces (11, 12) opposite to each other and a honeycomb-like structure (13) located between the two surfaces (11, 12). The honeycomb-like structure (13) is provided with multiple micro chambers (14). Multiple noise reduction holes (15) respectively in communication with the micro chambers (14) are disposed on one (12) of the two surfaces (11, 12). Further provided is an air intake throttle (40). The substrate for an air intake throttle and the air intake throttle may effectively reduce the noise level of an air intake system on the basis of not excessively changing the weight and the strength of the air intake throttle.

IPC Classes  ?

• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression

Abstract

A side rod control device (10) with three degrees of freedom is provided with a pitch control mechanism (300), a roll control mechanism (400) and a front wheel turning control mechanism (200) which are arranged along three mutually vertical straight lines, wherein the front wheel turning control mechanism (200) is rotatably arranged on a first fixing part (500) through one of a pitch control shaft (301) of the pitch control mechanism (300) and a roll control shaft (401) of the roll control mechanism (400); the first fixing part (500) is rotatably arranged on a second fixing part (600) through the other of the pitch control shaft (301) of the pitch control mechanism (300) and the roll control shaft (401) of the roll control mechanism (400).

IPC Classes  ?

• B64C 13/02 - Initiating means
• B64D 31/04 - Initiating means actuated personally
• G05G 1/04 - Controlling members for hand-actuation by pivoting movement, e.g. levers

Abstract

An aircraft wingtip device, comprising a transition part (1) and a wingtip part (2); the inner end of the transition part (1) is connected to the far end of an aircraft wing, and the outer end of the transition part is connected to the wingtip part (2); the wingtip part comprises a plurality of wingtip sections (3n), and each wingtip section (3n) comprises a wingtip (4n) and a wing root (5n) respectively; the wing root (5l) of the first wingtip section (3l) is connected to the outer end of the transition part (1), the wing root (5n+1) of the n+1 wingtip section (3n+1) is located on the wingtip (4n) of the n wingtip section (3n), and the chord length of the wing root (5n+1) of the n+1 wingtip section (3n+1) is smaller than or equal to the chord length of the wingtip (4n) of the nth wingtip section (3n), where n＞0. Because the wingtip device of the present invention is disposed in a stepped fashion, more than one discontinuity surface is added to the wingtip thereof, so that the wingtip vortices induced by the wingtip suppress each other, thereby reducing the strength of the vortices, and thus achieving drag reduction effect. In addition, the wing root of the present invention has a smaller bending moment increment, thus reducing the structural weight of the airplane and having less effect on the flutter properties.

IPC Classes  ?

• B64C 3/10 - Shape of wings
• B64C 3/36 - Structures adapted to reduce effects of aerodynamic or other external heating
• B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices

Abstract

Disclosed is a dehumidification system for use in an airplane, comprising： a cooling assembly (1) having an air inlet port (11) for a first round of dehumidification and an air outlet port (12) for the first round of dehumidification, when the cooling assembly (1) conducts the first round of dehumidification on the fresh air entering from the air inlet port (11) for the first round of dehumidification so as to reduce the absolute humidity thereof; a heat exchanger (2) having a waste gas inlet port (21), a waste gas outlet port (22), an air inlet port (23) for a second round of dehumidification and an air outlet port (24) for the second round of dehumidification, with the waste gas inlet port (21) being in communication with an electronics bay (5), the heat exchanger (2) being used for conducting a heat exchange on the hot waste gas discharged from the electronics bay (5) and the cold fresh air discharged from the cooling assembly (1) so as to perform a second round of dehumidification for the reduction of the relative humidity thereof to obtain dehumidified air; a distribution pipeline (3) for transporting the dehumidified air into an interlayer of the fuselage; and a control assembly (4).

IPC Classes  ?

• B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
• B01D 53/26 - Drying gases or vapours

Abstract

A navigation light comprises: a light source (1), a transparent lampshade (2), a reflective mask (3) and a baseboard (4). The reflective mask (3) and the transparent lampshade (2) are connected as a whole and fixed together on the baseboard (4). The light source (1) is arranged on the baseboard (4) and is close to the reflective mask (3). A ray of light emitted by the light source (1) passes through the transparent lampshade (2) after being reflected by the reflective mask (3). The navigation light has a compact structure and reduces the pneumatic influence while ensuring the light distribution.

IPC Classes  ?

• F21V 7/04 - Optical design
• F21S 8/00 - Lighting devices intended for fixed installation
• B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
• F21V 17/00 - Fastening of component parts of lighting devices, e.g. shades, globes, refractors, reflectors, filters, screens, grids or protective cages
• F21W 101/06 - for aircraft

Abstract

An apparatus for testing and driving a control column having two degrees of freedom, comprising a mechanical part. The mechanical part comprises a machine platform (1), an outer frame (21), an inner frame (31), a control column clamp (4), and a friction cancellation mechanism (5). A method for installing the apparatus for testing and driving the control column having two degrees of freedom, comprising: installing the control column on a motion platform of two axis, driving the control column mechanism into either an independent motion or a coupled motion on the pitch axis and on the roll axis; during installation, ensuring the rotation axis of the control column (6), the rotation axis of the outer frame (21), and the rotation axis of the inner frame (31) intersect at one point; avoiding the generation of excess stress when the control column (6) is in motion to prevent damages to the control column; employing a stress cancellation mechanism (5) at the point where the control column (6) is connected to the inner frame (31), cancelling a stress on control column generated due to a mechanical error, thereby protecting the control column mechanism. Provided is a method for controlling the apparatus for testing and driving the control column having two degrees of freedom.

IPC Classes  ?

• G01M 13/00 - Testing of machine parts
• B64C 13/04 - Initiating means actuated personally
• B64C 13/00 - Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
• G09B 9/08 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer

Abstract

An apparatus for testing and driving a control column having two degrees of freedom, comprising a mechanical part. The mechanical part comprises a machine platform (1), an outer frame (21), an inner frame (31), a control column clamp (4), a friction cancellation mechanism (5), and a control lever (6). The outer frame (21) is pivotably fixed on the machine platform (1); the rotation axis of the outer frame (21) and the rotation axis of the control lever (6) intersect at the pivot of the control lever (6). The inner frame (31) is pivotably fixed on the outer frame (21); the rotation axis of the inner frame (31) and the rotation axis of the control lever (6) intersect at the pivot of the control lever (6). The control column clamp (4) is fixedly connected to a control column handle (7). The stress cancellation mechanism (5) is connected to the inner frame (31) and to the control column clamp (4). Also disclosed is a method for controlling the apparatus for testing and driving the control column having two degrees of freedom.

IPC Classes  ?

• G01P 1/04 - Special adaptations of driving means
• G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
• B64C 13/16 - Initiating means actuated automatically, e.g. responsive to gust detectors

Abstract

A method for spraying and sintering a warning sign on a surface (2) of a heating part or an equipment component of an airplane comprises the following steps: 1) treating a surface (2) of an airplane where a warning sign is to be sprayed, to form a character patterned surface (12) on the surface (2) of the airplane, and forming multiple coloration depressions (11) on the character patterned surface (12); 2) spaying capsulated reversible thermochromic pigment (3) on the character patterned surface (12), so that capsule particles (8) encapsulating the pigment (3) are filled in the coloration depressions (11) on the character patterned surface (12); 3) sintering the character patterned surface (12); 4) after sintering, applying a protective film layer (4) on the character patterned surface (12); and 5) secondarily sintering the character patterned surface (12), and polishing the character patterned surface (12) after the secondary sintering. The warning character sprayed through the method can directly reflect a surface temperature status of the heating part or the equipment component of the airplane, thereby preventing an operator from being burned.

IPC Classes  ?

• B05D 7/24 - Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials for applying particular liquids or other fluent materials
• B05D 5/00 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
• B05D 3/00 - Pretreatment of surfaces to which liquids or other fluent materials are to be appliedAfter-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials

Abstract

A silencer (10) comprising a housing (11), an exhaust pipe (12), and a chamber (17). The housing (11) has a first end part (13a), a second end part (13b), and a conical wall part (14); the exhaust pipe (12) has an air intake (15a) corresponding to the first end part (13a), and an exhaust outlet (15b) corresponding to the second end part (13b). The chamber (17) is formed between the interior surface of the housing (11) and the exterior surface of the exhaust pipe (12). The exhaust pipe (12) extends beyond the first end part (13a) of the housing (11) and is sealed with the first end part (13a). The second end part (13b) of the housing (11) has an opening (16). The exhaust outlet (15b) of the exhaust pipe (12) is arranged within the chamber (17), and a gap is arranged between the exhaust outlet (15b) and the opening (16) of the second end part (13b). The conical wall part (14) of the housing (11) has arranged thereon a vent (18). When the exhaust pipe (12) discharges waste gas, the outside air enters into the chamber (17) via the vent (18), and exits via the opening (16) of the second end part (13b) of the housing (11), thereby cooling the silencer (10). As ventilation cooling is allowed, the operating temperature of the silencer is reduced, and the range of choices for manufacturing materials for the silencer is expanded.

IPC Classes  ?

• F02K 1/46 - Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing

Abstract

A hermetical wall penetration piece (100) comprises a cylindrical body (10) and a stopping ring (50), wherein the body is provided with a center hole (15) for an electric wire harness to pass through and comprises a fixing part (20), a flange (30) and a connection part (40). The fixing part is located at one end of the body and provided with at least one glue inflow hole (21), with the glue inflow hole being in communication with the center hole. The flange is located on the peripheral surface of the body and provided with at least one glue outflow hole (31), with the glue outflow hole being in communication with the center hole. The connection part is located at the other end of the body and provided with a stopping ring groove (41) for placing the stopping ring and a shield groove (42) for fixing a shield sleeve of an electric wire harness (60), with the stopping ring groove being closer to the flange than the shield groove. The hermetical wall penetration piece enables the electric wire harness for an airplane to conveniently pass through the airtight bulkhead without the need to break the electric wire harness and without the need to pass the electric wire harness through the hermetical wall penetration piece wire by wire.

IPC Classes  ?

• H02G 3/22 - Installations of cables or lines through walls, floors or ceilings, e.g. into buildings
• F16L 5/02 - Sealing

Abstract

An icing detector probe includes three sections arranged sequentially along the direction of air flow, namely, a first section (I), a second section (II) and a third section (III). Wherein, the shape of the outer surface of the first section (I) is suitable for collecting droplets in the air flow; the shape of the outer surface of the second section (II) is suitable for full decelerating and releasing latent heat of large droplets during their movements; the outer surface of the third section (III) is suitable for icing of large droplets. The probe could distinguish and identify large droplets icing, thus effectively detecting it. Furthermore, it could effectively detect types of traditional icing, thus being helpful for exact detection of icing thickness. An icing detector including said icing detector probe is also provided.

IPC Classes  ?

• B64D 15/20 - Means for detecting icing or initiating de-icing
• G08B 19/02 - Alarm responsive to formation or anticipated formation of ice

Abstract

A detecting device for detecting icing by an image includes an image acquiring system (1-A) and an image processing system (2-A). The image acquiring system (1-A) can acquire an image of an object's surface. The image processing system (2-A) can analyze the image and obtain an icing condition of the object's surface. The image acquiring system (1-A) also includes an image-carrying fiber bundle (104). The detecting device can meet the requirements of application in a special space without miniaturizing the image acquiring system (1-A).

IPC Classes  ?

• G01C 11/12 - Interpretation of pictures by comparison of two or more pictures of the same area the pictures being supported in the same relative position as when they were taken
• G02B 6/06 - Light guidesStructural details of arrangements comprising light guides and other optical elements, e.g. couplings formed by bundles of fibres the relative position of the fibres being the same at both ends, e.g. for transporting images
• G06T 7/00 - Image analysis

Abstract

A detecting device for detecting icing by an image includes an image acquiring system (1-A) and an image processing system (2-A).The image acquiring system (1-A) can acquire an image of an object's surface. The image processing system (2-A) can analyze the image and obtain an icing condition of the object's surface. The detecting device is simple and reliable. It can identify the category of the icing effectively. So, it can improve the accurateness of the icing detection significantly and can accomplish the detection of the object's whole surface. Furthermore, it can detect an icing condition of a super-cooled large droplet. A method for detecting an icing condition of an object's surface using the detecting device is also provided.

IPC Classes  ?

• G01C 11/12 - Interpretation of pictures by comparison of two or more pictures of the same area the pictures being supported in the same relative position as when they were taken
• G06T 7/00 - Image analysis

Abstract

A fastener model representation device (10) for use in a fastener-aided design system includes: at least one fastener model (101,102) which comprises an information memory module (1011, 1021) for storing three-dimensional information of the fastener model (101,102). Also provided, and corresponding to the aforementioned device, is a fastener model representation method for use in a fastener-aided design system. By storing the three-dimensional information of the fastener model into the local storage area of the fastener model and directly accessing the information, various graphic representations of the fastener model and statistical information about the fastener model can be provided to the user for browsing, editing, modifying or configuring. At the same time, specific graphical representations in the form of lines and circles make the illustrative representations of the fastener models easier to read.

IPC Classes  ?

• G06F 17/50 - Computer-aided design