37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Maintenance planning and optimization for airlines; business project management for heavy maintenance events; consultancy on fleet utilization and downtime reduction based on operational data and customer insight; Vehicle fleet (business management of-) [for others]; transportation fleet (business management of-) [for others]. Aircraft heavy maintenance; Aircraft maintenance; Maintenance and repair of aircraft; Painting of aircraft; Aircraft fuelling services; Outer and inner cleaning of aircraft. Logistics services relating to the supply, storage and distribution of aircraft parts; organization and management of just in time delivery of spare parts to maintenance locations; inventory management in relation to aircraft components; Aircraft storage; Aircraft handling; Delivery of parts to grounded aircraft via airplane. Providing online, non downloadable software for real time monitoring of airline operations and maintenance status; data analytics and predictive modelling for parts demand and maintenance planning; technological consultancy in the field of aviation maintenance systems; Design of computer programs and software relating to aircraft.
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Maintenance planning and optimization for airlines; business project management for heavy maintenance events; consultancy on fleet utilization and downtime reduction based on operational data and customer insight Aircraft heavy maintenance; Aircraft maintenance; Maintenance and repair of aircraft Logistics services relating to the supply, storage and distribution of aircraft parts; inventory management in relation to aircraft components; organization and management of just-in-time delivery of spare parts to maintenance locations Providing online, non-downloadable software for real-time monitoring of airline operations and maintenance status; data analytics and predictive modeling for parts demand and maintenance planning; technological consultancy in the field of aviation maintenance systems
6.
System Architecture and Method for Deploying Maintenance Tasks by Adding a Secondary Function to Aircraft Cockpit Interfaces
An aircraft operating method comprises receiving inputs from flight controls; responding to the inputs from the flight controls by providing control surface commands to control flight; and responding to alternative operation of the flight controls to select and perform an aircraft maintenance operation other than during flight.
An electromechanical actuation arrangement for a non-mass-balanced primary flight control surface establishes and retains a torsional preload between distributed actuator outputs to eliminate surface freeplay and increase mechanical impedance. Preload is retained mechanically via an interconnect shaft and/or electronically by closed-loop synchronization that maintains a commanded differential torque. An independent flutter-suppression device provides damping and/or locking upon oscillation detection or disconnection. The architecture supports multiple embodiments, including fewer motors than transmissions and a transmission without its own motor, and enables reduction or elimination of hydraulic systems for primary flight controls while meeting aeroelastic requirements under normal and single-fault conditions.
It is described a flow control structure for suppressing tonal noise in high-lift devices (30), the high-lift devices (30) having a concave shape forming a void (32) between the high-lift devices (30) and an edge (11) of an aircraft's wing (10) with which the high-lift devices (30) are movable connected, said high-lift devices (30) being movable between a retracted position in which the high-lift devices (30) are nearby the edge (11) of the aircraft's wing (10) and a deployed position in which the high-lift devices (30) are spaced away of the edge (11) of the aircraft's wing (10), wherein in a first embodiment, the flow control structure comprises a plurality of flow-altering elements (12) linearly positioned in the aircraft's wing (10) along the edge (11) of the aircraft's wing (10) towards the concave shape of the high-lift devices (30) and the void (32), so that the plurality of flow-altering elements (12) is adjacent to each other and is configured to disrupt vortex formation during airflow over the high-lift devices (30) and the aircraft's wing (10) when the high-lift devices (30) are in the deployed position.
An inner hub rotates inside an outer hub. Blades are mounted over these hubs. A plunger is installed inside the inner hub and has axial movement. Inner hub, outer hub and plunger have their axial and rotational movements linked so the mechanism has only a single degree of freedom limited by mechanical stops in respective stow and deploy positions. This link is made using spheres that roll inside grooves, so no sliding occurs during deployment for load path interfaces. This reduces friction and, therefore, wear and hysteresis.
The present invention discloses a fluid level indicator (100) actuated by tape spring (3), preferably of the “constant-force” type, in connection with the piston (6) of the hydraulic actuator (1), so as to keep the load constant throughout the entire stroke of the piston (6). The spring tape (3) has the function of making the connection to the piston (6), providing the flexibility of a spring, in addition to indicating through a graduation, the level of the hydraulic system fluid.
G01F 23/02 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by gauge glasses or other apparatus involving a window or transparent tube for directly observing the level to be measured or the level of a liquid column in free communication with the main body of the liquid
11.
MOBILE HIGH-RIGIDITY ROBOTIC SYSTEM WITH COMPACT END-EFFECTOR
ELECTROIMPACT DO BRASIL INDÚSTRIA AEROESPACIAL LTDA. (Brazil)
EMBRAER S.A. (Brazil)
Inventor
Mosqueira, Glauber
Schraer, Allison
Cortarelli, Raphael
De Mello, João Marcos Gomes
Guedes, Rafael
Abstract
The present invention relates to an apparatus to improve the rigidity of robotic systems by disclosing the introduction of prismatic joints seen on larger scale machines to the kinematic chain of industrial robots, which allows for improved overall rigidity and thus positioning accuracy. The prismatic joints are introduced at the robot base, which have the greatest contribution to TCP error. The invention provides a means to improve positional accuracy passively, thus offering a potential cost reduction, in addition to being compatible with existing methods for a combined effect. Additionally, the invention relates to an apparatus to allow for more compact robotic end-effectors and part access. Specifically with regards to airframe drilling, which requires machine clamp-up and normalization on the part. It introduces a combination of non-contact sensors, rotary asymmetric nosepiece and thin-walled, 3D printed nosetip, which allows for clamp-up on the part, normalization and drilling much closer to vertical objects than the current art, thus enabling the use of automation in areas only currently assisted by traditional manual methods such as drill jigs.
An inner hub rotates inside an outer hub. Blades are mounted over these hubs. A plunger is installed inside the inner hub and has axial movement. Inner hub, outer hub and plunger have their axial and rotational movements linked so the mechanism has only a single degree of freedom limited by mechanical stops in respective stow and deploy positions. This link is made using spheres that roll inside grooves, so no sliding occurs during deployment for load path interfaces. This reduces friction and, therefore, wear and hysteresis.
It is described a hexagonal structural element (40) applied to any aircraft structural part or tooling devices, wherein the hexagonal structural element (40) is made by additive manufacturing, the hexagonal structural element (40) comprises a hexagonal primary structure (10) with cylindrical beams (11) to avoid stress concentration and that can make the structural part or tooling device lighter, but still meeting the strength and stiffness requirements.
B64C 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
B64C 7/00 - Structures or fairings not otherwise provided for
B33Y 80/00 - Products made by additive manufacturing
B29C 64/00 - Additive manufacturing, i.e. manufacturing of three-dimensional [3D] objects by additive deposition, additive agglomeration or additive layering, e.g. by 3D printing, stereolithography or selective laser sintering
F16S 5/00 - Other constructional members not restricted to an application fully provided for in a single class
B32B 3/10 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material
B32B 15/00 - Layered products essentially comprising metal
09 - Scientific and electric apparatus and instruments
Goods & Services
Electronic and digital display systems for aircraft cabins, namely, virtual window systems comprising hybrid hardware and software technology, including electronic displays, image processors, sensors, and display interfaces, designed to simulate external views of the aircraft environment
09 - Scientific and electric apparatus and instruments
Goods & Services
Electronic and digital display systems for aircraft cabins, namely, virtual window systems comprising hybrid hardware and software technology, including electronic displays, image processors, sensors, and display interfaces, designed to simulate external views of the aircraft environment
09 - Scientific and electric apparatus and instruments
Goods & Services
Electronic and digital display systems for aircraft cabins, namely, virtual window systems comprising hybrid hardware and software technology, including electronic displays, image processors, sensors, and display interfaces, designed to simulate external views of the aircraft environment.
09 - Scientific and electric apparatus and instruments
Goods & Services
Electronic and digital display systems for aircraft cabins, namely, virtual window systems comprising hybrid hardware and software technology, including electronic displays, image processors, sensors, and display interfaces, designed to simulate external views of the aircraft environment.
Method and system of electronic countermeasure comprising an airborne RF and IR decoy, being an independent, autonomous flying body that flies on its own, using its own aerodynamics, rotatable blades and fins, being applied as protection against Radio Frequency (RF) and infrared (IR) threats. Such an aircraft decoy comprises a body; a rotatable blade or vane disposed on the body; a power source capable of generating electrical current in response to rotation of the blade or vane; a wideband radar jammer responding to a radar signal with a wideband phantom radar signature corresponding to a phantom target; corner reflectors generating strong radar reflections corresponding to the phantom target; and an infrared source emitting a phantom infrared signature corresponding to a heat signature of the phantom target. Data stored within the decoy is destroyed automatically upon impact.
The present invention discloses a system and method for adapting the visual and other data information that is delivered to the operator of a remotely piloted aircraft, placing him at the same moment that the aircraft (1) is. In other words, bringing the future image of the aircraft's position compensates the overall delay and allows the pilot to have a proper command the aircraft, thus reducing the chance to occur the PIO phenomenon, considering that his/her commands will be well synchronized with the aircraft response. The compensation of the delays in the transmission of data is done by advancing the image of this immersive environment that is obtained by a filming equipment composed preferably of stereoscopic cameras (2), bringing the appropriate perspective of the scenario for the operator, based on the speed practiced by the aircraft (1) multiplied by the total delay time, then defining the displacement that will be taken as the basis for the "advancement" (space x time) in perspective.
The technology herein will have an automatic cooldown time start and an autonomous APU shutdown right after main engines start if the APU is not supplying any power to the aircraft, such as, pneumatic, electrical, etc. The APU control unit will not wait for pilot input to start the cooldown time, it will be automatically initiated. In parallel, the control unit will also set autonomous APU shutdown. Then, after cooldown time, the APU will shut down if the pilot does not take any action.
42 - Scientific, technological and industrial services, research and design
Goods & Services
Sales promotion; Sales administration; Sales management services; Sales management consultancy; Providing information concerning commercial sales; Commercial management; Business administration services for processing sales made on the internet; Advertising services relating to the commercialization of new products; Providing assistance in the field of product commercialization; Business management, organization and administration; Business investigations; Business management assistance; Professional business consultancy; Providing business information; Providing assistance in the field of business management; Providing commercial information and advice for consumers in the choice of products and services; Arranging and conducting of commercial events; organization of exhibitions for commercial or advertising purposes; Presentation of goods on communication media, for retail purposes; Commercial assistance services; Negotiation of business contracts for others. Engineering services; Engineering research; Engineering design and consultancy; Industrial design; Research and development of new products for others; Technological research; Technological consultancy; Technological engineering analysis; Providing technological information; Conducting technical project studies; Provision of information concerning research and technical project studies.
An aircraft engine emulator comprises a housing; at least one actuator or emulated actuator disposed within the housing; at least one sensor or emulated sensor disposed within the housing; and a wired connection configured to connect the at least one actuator or emulated actuator and the at least one sensor or emulated sensor for communication with components on board an aircraft, wherein the aircraft engine emulator is configured to take the place of an engine to the components on board an aircraft that has at least one missing or non-functional engine.
Hybrid hydraulic/electric brake control systems for aircraft include port and starboard braking channel units that are configured to provide independent braking control to port side and starboard side main wheel assemblies associated with the aircraft. Each of the port and starboard braking channel units will include (i) a master braking cylinder to provide hydraulic braking pressure to a respective one of the port side and starboard side main wheel assemblies associated with the aircraft by port and starboard hydraulic lines, respectively, (ii) a control drive unit configured to output a brake actuation signal, and (iii) a linear actuator in operative electrical communication with the control drive unit, the linear actuator including an actuator rod mechanically connected to the master braking cylinder to thereby modulate the master braking cylinder in response to the brake actuation signal to provide proportional hydraulic braking force to the respective one of the port side and starboard side main wheel assemblies.
B60T 13/74 - Transmitting braking action from initiating means to ultimate brake actuator with power assistance or driveBrake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
B60T 8/17 - Using electrical or electronic regulation means to control braking
B60T 13/70 - Electrical control in fluid-pressure brake systems by fluid-controlled switches
25.
METHOD FOR COMPENSATE CAVITY EFFECT IN AIRCRAFT EMBEDDED ANTENNA IMPEDANCE AND EMBEDDED ANTENNA ARRAY FOR AIRCRAFT
INATEL / FUNDAÇÃO INSTITUTO NACIONAL DE TELECOMUNICAÇÕES (Brazil)
Inventor
Nunes, Sidney Osses
Bellei, Leandro Napoli
De Assis, Rodrigo Rodrigues
De Carvalho, Juliano Vilela
Sodre Junior, Arismar Cerqueira
Da Silva, Luís Gustavo
Abstract
Method for compensate cavity effect in aircraft embedded antenna impedance and Embedded antenna array for aircraft” The present invention relates to a method for compensate cavity effect in aircraft embedded antenna impedance by using radiofrequency (RF) absorber materials applied to entirely embedded antennas (non-protruding installation) particularly used in aircraft. The invention also refers to embedded antenna arrays for aircraft using radiofrequency (RF) absorber materials to enhance and/or optimize its impedance matching.
Sidestick grips are disclosed which minimize cross-axis control coupling about three or more control axes, wherein one of the control axes provides directional (yaw) input by twisting the grip in clockwise/counterclockwise directions. Minimizing cross-axis control according to the embodiments disclosed herein is accomplished principally by having the Grip Reference Point (GRP) (i.e., the theoretical point of application of pitch and roll forces) of the sidestick grip to be substantially coincident with the yaw axis of rotation. By providing the GRP substantially coincident with the yaw axis of rotation, unintentional yaw torque is minimized when control input is exerted on the sidestick in the pitch and roll axes.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
27.
SUBMERSIBLE BOX-WINGED VEHICLE SYSTEMS AND METHODS FOR GENERATING HYDROELECTRIC ENERGY
Submersible box-winged vehicle systems generate hydroelectric energy using naturally occurring tidal flows and/or water currents in a body of water. The vehicle systems include a submersible hull, an upright dorsal fin extending from an aft portion of the submersible hull, port and starboard wing assemblies each having respective proximal ends joined to a forward region of the hull an and an upper region of the dorsal fin so as to establish a box wing configuration, and electrical power generation units attached to the port and starboard wings, wherein each of the electrical power generation units include a generator and a marine propeller operatively connected to the generator so as to cause the generator to generate electrical energy in response to the marine propeller turning. The vehicle system when submerged in a body of water thereby allows tidal flows and/or currents associated with the body of water to responsively turn the marine propeller of each of the electrical power units thereby generating electricity by the generator operably associated therewith
F03B 13/26 - Adaptations of machines or engines for special useCombinations of machines or engines with driving or driven apparatusPower stations or aggregates characterised by using wave or tide energy using tide energy
B63B 21/50 - Anchoring arrangements for special vessels, e.g. for floating drilling platforms or dredgers
B63B 35/44 - Floating buildings, stores, drilling platforms, or workshops, e.g. carrying water-oil separating devices
Submersible box-winged vehicle systems generate hydroelectric energy using naturally occurring tidal flows and/or water currents in a body of water The vehicle systems include a submersible hull, an upright dorsal fin extending from an aft portion of the submersible hull, port and starboard wing assemblies each having respective proximal ends joined to a forward region of the hull an and an upper region of the dorsal fin so as to establish a box wing configuration, and electrical power generation units attached to the port and starboard wings, wherein each of the electrical power generation units include a generator and a marine propeller operatively connected to the generator so as to cause the generator to generate electrical energy in response to the marine propeller turning. The vehicle system when submerged in a body of water thereby allows tidal flows and/or water currents associated with the body of water to responsively turn the marine propeller of each of the electrical power units thereby generating electricity by the generator operably associated therewith
F03B 13/22 - Adaptations of machines or engines for special useCombinations of machines or engines with driving or driven apparatusPower stations or aggregates characterised by using wave or tide energy using wave energy using the flow of water resulting from wave movements, e.g. to drive a hydraulic motor or turbine
F03B 17/06 - Other machines or engines using liquid flow, e.g. of swinging-flap type
F03B 13/10 - Submerged units incorporating electric generators or motors
Advancements in executive aircraft interior design explicitly address the limitations of traditional physical windows within aircraft cabins. The passenger experience is transformed by integrating advanced hybrid technology, replicating expansive exterior views, fostering a sense of connection to the surroundings, and an immersive travel experience through a mimetic virtual display.
Advancements in executive aircraft interior design explicitly address the limitations of traditional physical windows within aircraft cabins. The passenger experience is transformed by integrating advanced hybrid technology, replicating expansive exterior views, fostering a sense of connection to the surroundings, and an immersive travel experience through a mimetic virtual display.
Overhead passenger comfort modules are provided with a module segment having a support frame member which includes a perimetrical trim frame member, and a ventilation system supported by the support frame member. The ventilation system includes a supply conduit adapted to being fluid-connected to a supply of ventilation air, and first and second branch conduits fluid-connected at one end to the supply conduit and terminating in elongate first and second ventilation openings at first and second edge regions of the support frame member. First and second concavely curved edge diffuser portions are provided which are adjacently positioned to and spaced from the first and second ventilation openings respectively. Ventilation air discharged from the first and second ventilation openings will therefore impinge on the concavely curved first and second edge diffuser portions so as create a diffused volume of air which envelops substantially a passenger seated therebelow and establish a personal ambient air zone for the passenger.
Method and system of electronic countermeasure comprising an airborne RF and IR decoy, being an independent, autonomous flying body that flies on its own, using its own aerodynamics, rotatable blades and fins, being applied as protection against Radio Frequency (RF) and infrared (IR) threats. Such an aircraft decoy comprises a body; a rotatable blade or vane disposed on the body; a power source capable of generating electrical current in response to rotation of the blade or vane; a wideband radar jammer responding to a radar signal with a wideband phantom radar signature corresponding to a phantom target; corner reflectors generating strong radar reflections corresponding to the phantom target; and an infrared source emitting a phantom infrared signature corresponding to a heat signature of the phantom target. Data stored within the decoy is destroyed automatically upon impact.
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02J 7/14 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries for charging batteries from dynamo-electric generators driven at varying speed, e.g. on vehicle
H02P 9/04 - Control effected upon non-electric prime mover and dependent upon electric output value of the generator
G01S 13/60 - Velocity or trajectory determination systemsSense-of-movement determination systems wherein the transmitter and receiver are mounted on the moving object, e.g. for determining ground speed, drift angle, ground track
G01S 17/87 - Combinations of systems using electromagnetic waves other than radio waves
F41H 3/00 - Camouflage, i.e. means or methods for concealment or disguise
F41A 33/04 - Acoustical simulation of gun fire, e.g. by pyrotechnic means
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
F41J 2/02 - Active targets transmitting infrared radiation
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraftAdaptations of armament mountings for aircraft
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
H04K 3/00 - Jamming of communicationCounter-measures
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
(1) Aircraft engines
(2) Aircraft; structural parts for aircraft; parachutes (1) Aircraft repair and construction services, as well as repairs, maintenance, conservation, and installation.
37 - Construction and mining; installation and repair services
Goods & Services
Aircraft engines and their parts, such as, turbines, compressors, combustion chambers, and exhaust Aircraft maintenance, repair and construction services, as well as repairs, aircraft interior modifications and installation/upgrade, maintenance, conservation, and installation of avionics equipment, spare parts and other associated aircraft components
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
(1) Aircraft engines and their parts
(2) Aircraft (1) Aircraft repair and construction services, as well as repairs, maintenance, conservation, and installation
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Aircraft engines and their parts, namely, turbines, compressors, combustion chambers, and exhaust Aircraft, their parts, and components, included in this class, namely structural parts, structural fitting, and system components including landing gear, structural parts, interior monuments, seats, actuators, and controllers, and parachutes Aircraft maintenance, repair, and overhaul services, as well as repairs, aircraft interior and exterior modifications and installation/upgrade and modification of aircraft; maintenance, repair, conservation, and installation of avionics equipment and aircraft components
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Aircraft engines and their parts, namely, turbines, compressors, combustion chambers, and exhaust Aircraft, their parts, and components, included in this class, namely structural parts, structural fitting, and system components including landing gear, structural parts, interior monuments, seats, actuators, and controllers, and parachutes Aircraft maintenance, repair, and overhaul services, as well as repairs, aircraft interior and exterior modifications and installation/upgrade and modification of aircraft; maintenance, repair, conservation, and installation of avionics equipment and aircraft components
42.
Access cover panel assemblies especially useful to cover aircraft fuel tank access openings
Access cover panel assemblies are provided that are especially useful to cover access openings of aircraft wing fuel tanks and include an inner cover plate and an outer cover plate spaced from the inner cover plate which defines a circumferentially spaced-apart plurality of apertures. A circumferentially spaced-apart plurality of generally U-shaped floating nut plates dependently extend from the inner cover plate toward the outer cover plate with each nut plate being in alignment with a respective one of the apertures. A corresponding plurality of attachment bolts extend through each of the apertures of the outer cover plate and are threadably coupled to a respective one of the floating nut plates to thereby removably secure the inner and outer cover plates to one another and to the surrounding structure defining the access opening.
Processes for fabricating a partially stabilized honeycomb core is disclosed where a stabilizing layer of an adhesive film is aligned with and adhered to only one exterior surface of a honeycomb sheet. The opposed exterior surface thereby remains uncovered. A preform of the partially stabilized honeycomb core may be subjected to ambient atmospheric pressure cure conditions at an elevated temperature sufficient to adhere the stabilizing layer to the one exterior surface of the honeycomb sheet and thereby provide a partially stabilized honeycomb core that is partially stabilized against compressive forces exerted in widthwise and lengthwise directions thereof yet allows bending of the partially stabilized honeycomb core about axes in the widthwise and lengthwise directions.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 65/00 - Joining of preformed partsApparatus therefor
B32B 3/04 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by a layer folded at the edge, e.g. over another layer
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 29/02 - Layered products essentially comprising paper or cardboard next to a fibrous or filamentary layer
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 37/14 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
B32B 27/10 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of paper or cardboard
Vehicle seat systems, especially seat systems for aircraft passengers are provided. In preferred forms, the aircraft seat systems according to the embodiments disclosed herein will include a seat base assembly, a seat tracking/swivel assembly fixed to the seat base assembly and a seat bucket fixed to the seat tracking/swivel assembly.
Drilling jigs are provided which include a one-piece jig body (preferably additively manufactured from laser-sintered metallic (e.g., aluminum alloy) powders) having at least one set of cylindrical sockets that are spatially separated from one another, and a web member joining the at least one set of sockets. Cylindrical bushings may thus be positioned within each of the cylindrical sockets so as to define respective cylindrical guideways for a drill bit. According to certain embodiments, the web member may be planar and oriented parallel to a substantially longitudinal bisecting plane of the cylindrical sockets.
A control platform for autonomous systems integrates digital product and process information with data obtained by means of sensors, using artificial intelligence, for example, artificial neural networks for system feedback and decision making in the autonomous execution of activities.
A light unit executes up to three different functions (cabin area illumination, individual/dedicated/decorative illumination and emergency illumination) and an emergency illuminated sign unit, each one with an internal controller and a rechargeable capacitor. An example non-limiting embodiment also provides a cabin light system and an emergency lighting system, where each illumination unit (light source or illuminated sign) is as described above.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
B64D 25/00 - Emergency apparatus or devices, not otherwise provided for
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21S 9/02 - Lighting devices with a built-in power supplySystems employing lighting devices with a built-in power supply the power supply being a battery or accumulator
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02J 7/34 - Parallel operation in networks using both storage and other DC sources, e.g. providing buffering
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
H05B 45/00 - Circuit arrangements for operating light-emitting diodes [LED]
H05B 47/105 - Controlling the light source in response to determined parameters
H05B 47/17 - Operational modes, e.g. switching from manual to automatic mode or prohibiting specific operations
48.
Hybrid tooling structures of additively manufactured thermoplastics reinforced with rigid metal supports and methods for the design and manufacture thereof
Hybrid tooling structures are provided which include an additively manufactured thermoplastic tooling unit defining a tooling surface for receiving and supporting a component part to be manufactured, and a rigid metal support member fixed to the tooling unit. The rigid metal support member may be internally provided as an integral part of the additively manufactured tooling unit (e.g., the integral support member serving as an endoskeletal support structure for the tooling unit) which is especially adapted for high temperature/pressure processing conditions or may be externally provided as a support frame to which the additively manufactured tooling unit is fixedly attached (e.g., the frame serving as an exoskeletal support structure for the tooling unit) which is especially adapted for ambient room temperature/pressure and loads during processing conditions.
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
B29C 33/38 - Moulds or coresDetails thereof or accessories therefor characterised by the material or the manufacturing process
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B33Y 80/00 - Products made by additive manufacturing
Near Field Communication (NFC) technology is applied to connect Personal Electronic Devices (PEDs) to a Wi-Fi network of a vehicle such as a business jet without the need for users to follow conventional steps to establish such a connection. Once a Wi-Fi connection is established, the same approach is also used to automatically open any web application to remotely control functions without having to manually open a web browser and enter the application's URL.
An aircraft stores cryogenic fuel in one or more right sized fuel tanks inside the aircraft fuselage or at other appropriate positions on the aircraft, and stores non-cryogenic fuel in plural standard jet fuel tanks e.g., inside the aircraft wings. The tanks are sized to using an automated aircraft sizing computational tool based on the defined missions ranges requirements, tanks sizing logic, Top-Level Aircraft Requirements, and aircraft geometry and engine thrust levels, to iteratively develop at least cryogenic fuel tank size for a particular aircraft. A controller controls selective routing of non-cryogenic fuel or cryogenic (e.g., hydrogen) fuel to dual fuel engines. In one operating mode, the dual fuel engines normally use the cryogenic hydrogen fuel as the main fuel, and reserve the non-cryogenic fuel for application to the dual fuel engines only on an exception basis, thereby providing cleaner and more environmentally friendly operation.
Air systems for a fuel cell powered aircraft include at least one compressor for supplying heated compressed air, at least one heat exchange system for receiving the heated compressed air and from the at least one compressor and discharging cooled compressed air, and at least one turbine for receiving the cooled compressed air from the heat exchange system and directing the cooled compressed air to on-board aircraft cabin pressurization and temperature control systems. At least one shaft operatively interconnects the at least one compressor and the at least one turbine. An electric motor is provided and adapted to being powered by electrical power supplied by an on-board fuel cell of the aircraft, the electric motor being operatively connected to the shaft interconnecting the at least one compressor and the at least one turbine so as to operatively cause the shaft to drive the at least one compressor and the at least one turbine.
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
B60L 50/70 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
UNIVERSIDADE FEDERAL DE SÃO PAULO—UNIFESP (Brazil)
Inventor
Scotton, Rogério Scafutto
Da Silva, Fabio Dos Santos
De Albuquerque Bonifácio, Marcelo Andrey
De Oliveira, Flavio Luiz
Guerrini, Lília Müller
Molina, Celso
De Oliveira, Maurício Pinheiro
Abstract
Methods and systems for painting surfaces (especially vehicle surfaces such as exterior aircraft surfaces) are provided whereby an applied basecoat layer may be treated with plasma (e.g., a non-thermal atmospheric pressure plasma) or laser radiation so as to form a treated basecoat layer which exhibits a decreased contact angle and an increased wetting energy as compared to the contact angle and wetting energy of the basecoat layer which is untreated. At least one inkjet printed color layer may be applied onto the treated basecoat layer followed by the application of a clearcoat protective layer over the one or more inkjet printed color layers.
B41J 11/00 - Devices or arrangements for supporting or handling copy material in sheet or web form
B41J 3/407 - Typewriters or selective printing or marking mechanisms characterised by the purpose for which they are constructed for marking on special material
B05B 13/04 - Means for supporting workArrangement or mounting of spray headsAdaptation or arrangement of means for feeding work the spray heads being moved during operation
B05D 3/14 - 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 by electrical means
B25J 11/00 - Manipulators not otherwise provided for
55.
Aircraft tail mounted fuel cell power train and thermal management systems
A system and method for collecting and analyzing time sequences of signal data produced by a product development effort including but not limited to aircraft signals. A time sequence signal data analyzer receives a signal event specification, searches time sequenced signal data for time slices that meet the signal event specification, analyzes a located time slice that meets the event specification to determine if it satisfies a criterion; and generates a data structure that (a) indicates a portion of the time sequenced signal data that meets the signal event specification and (b) indicates whether or not the portion of the time sequenced signal data that meets the event specification satisfies the analysis criterion or criteria.
A fuel line coupling component (e.g., for aircraft fuel lines) allow for axial, rotational and radial displacements. The fuel line coupling component includes outer and inner tubular members with each having coaxially aligned pairs of coaxially sleeved tubular sections that are coaxially displaceable relative to one another. A pair of terminal end connectors includes a journalled connection assembly with the respective opposed distal ends of the outer and inner tubular members to thereby allow simultaneous rotational movements of the outer and inner tubular members about a longitudinal axis thereof and simultaneous radial displacements of outer an inner tubular members relative to a reference plane. C-clamps associated with fuel tank fittings and band clamps allow coupling of the fuel line coupling component to the fuel tank fittings and thereby fluid-connect aircraft fuel tanks (e.g., the aircraft main and auxiliary fuel tanks).
A longitudinal control augmentation surface of aircraft, particularly turboprop/propfan aircraft with engines mounted on the rear portion of the fuselage. This longitudinal control augmentation surface is positioned in the connecting structure of the engine with the fuselage. A longitudinal control augmentation system for aircraft with engines arranged in a rear portion of the fuselage close to a vertical tail, this system comprising means of controlling the longitudinal control augmentation surfaces of the aircraft to distribute a longitudinal offset of the aircraft between these surfaces by means of functions, and an aircraft comprising the longitudinal control augmentation surface and the longitudinal control augmentation system.
Aircraft door seals, especially door seals for aircraft cargo doors, include individual door seal sections joined together by a lap joint assembly. The door seal sections may have abutted ends establishing a seal junction, and a lap joint junction seal assembly to sealingly join the abutted ends of the door seal sections, wherein the lap joint junction seal assembly includes (i) a lap joint member having a lap joint base and a lap joint shelf extending from the lap joint base and sealingly engaged with a lower surface of the door seal sections over the seal junction, and (ii) an interior support spigot inserted within the interior space of each of the door seal sections at the abutted ends thereof. Each of the door seal sections may be a hollow profiled door seal defining the interior space and formed of an elastomeric sealing material.
Seat mounting assemblies and vehicle seat systems which include the same are provided whereby a pivot bracket is operatively connected to a mounting bracket for reciprocal vertical movements while a tubular support member is operatively be associated with the pivot bracket so as to be pivotally movable about a substantially vertical central axis of the pivot bracket. A cantilevered support base arm is fixed to and extends outwardly from the tubular support member. An arm member is telescopically connected to the cantilevered support base arm to allow reciprocal rectilinear movements relative to the support base arm along a substantially horizontal axis thereof between retracted and extended positions thereof and carries a swivel plate at a distal end thereof to thereby allow swivel movements of a vehicle seat about a substantially vertical seat axis parallel to the substantially vertical central axis of the pivot bracket.
Towplate units and assemblies are disclosed for airborne extraction of a cargo load. The towplate unit includes an extraction and jettison links having a pair of spaced-apart parallel extraction and jettison link arms and an extraction and jettison cross-connector extending between and rigidly joining the extraction and jettison link arms, respectively. A locking system removably locks the jettison link to the extraction link to thereby allow the jettison link to be removed from the extraction link when unlocked. A towplate assembly is also provided which includes a towplate unit removably assembled with a deck plate and an actuator control assembly operatively interconnected to the towplate unit so as to cause the towplate unit to separate from the deck plate during a normal cargo deployment condition or to cause the jettison link to separate from the extraction link of the towplate unit during an aborted cargo deployment condition.
A first Flight Control system configuration, and the method to obtain such first configuration, has controllers of effector actuation able to receive commands directly from at least three Flight Control Computers (FCCs). A second Flight Control system configuration, and the method to obtain such second configuration, has retransmitters (RTX) that receive commands from the three FCCs and then retransmit to the controllers of effector actuation. A third Flight Control system configuration, and the method to obtain such third configuration, is a hybrid configuration.
Thermo-pneumatic anti-icing systems include port and starboard anti-icing subsystems operatively interconnecting heated engine bleed air discharged from port side and starboard side turboprop engines with port and starboard airfoils, respectively, associated with an aircraft to thereby provide in-flight anti-icing protection to the port and starboard airfoils, and an auxiliary power unit (APU) capable of discharging a supply of heated APU bleed air to the port and starboard anti-icing subsystems during an abnormal single engine or a single pneumatic bleed air operational condition. A controller may command respective port and starboard cross bleed valves to open and thereby allow the APU bleed air to be supplied to the one port or starboard anti-icing subsystem that is incapable of delivering heated engine bleed air from the port side turboprop engine or the starboard side turboprop engine, respectively. The port and starboard airfoils are thus each protected against inflight icing during the abnormal single engine or single pneumatic bleed air operational condition.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Geodesic, navigation, measuring, signaling, detection, testing, communication, inspection and control apparatus, instruments, and devices for use in aircraft. Airplanes, aircraft and aeronautical vehicles, their parts and fittings, included in this class.
09 - Scientific and electric apparatus and instruments
Goods & Services
Geodesic, navigation, measuring, signaling, detection, testing, communication, inspection and control apparatus, instruments, and devices for use in aircraft.
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
Goods & Services
Geodesic, navigation, measuring, signaling, detection, testing, communication, inspection and control apparatus, instruments, and devices for use in aircraft, namely, GPS navigation devices, avionic sensor systems in the nature of aircraft airspeed sensors and aircraft altitude indicators, computers for managing control devices for aircraft, wireless communication devices for voice, data or image transmission Airplanes, aircraft, space vehicles in the nature of aeronautical vehicles, and structural parts for all of the aforementioned goods; Aircraft and airplane parts, namely, fuselages, landing gear, brake discs, brake linings
09 - Scientific and electric apparatus and instruments
Goods & Services
Geodesic, navigation, measuring, signaling, detection, testing, communication, inspection and control apparatus, instruments, and devices for use in aircraft, namely, GPS navigation devices, avionic sensor systems in the nature of aircraft airspeed sensors and aircraft altitude indicators, computers for managing control devices for aircraft, wireless communication devices for voice, data or image transmission.
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Business administration and management (an accelerator of startups and disruptive/exponential businesses) focused on contributing to the creation, development and improvement of solutions for mobility and urban mobility; Business administration and management (an accelerator of startups and disruptive/exponential businesses) focused on contributing to the creation, development and improvement of solutions for connectivity and communication; Business administration and management (an accelerator of startups and disruptive/exponential businesses) focused on contributing to the creation, development and improvement of solutions for logistics, airline operations and for the aerospace industry; Business administration and management (an accelerator of startups and disruptive/exponential businesses) focused on contributing to the creation, development and improvement of solutions for use of drones, as well as solutions for precision agriculture, for areas of defense and public safety and power generation; all of them of technology basis, in order to ensure the solution of major problems and the improvement in the performance of such activities, encouraging the technological innovation. Education (instruction) and practical training (demonstration) focused on the creation, development and improvement of solutions for mobility and urban mobility, connectivity and communication, logistics, air operations and for the aerospace industry; Education (instruction) and practical training (demonstration) focused on the creation, development and improvement of solutions for use of drones, as well as solutions for the agriculture of precision, for areas of defense and public safety and power generation; all of them of technology basis, in order to ensure the solution of major problems and the improvement in the performance of such activities, encouraging the technological innovation. Technological consulting services, engineering, studies for technical projects and technical research focused on the creation, development and improvement of solutions for mobility and urban mobility, connectivity and communication, logistics, air operations and for the aerospace industry; Technological consulting services, engineering, studies for technical projects and technical research focused on the creation, development and improvement of solutions for use of drones, as well as solutions for the agriculture of precision, for areas of defense and public safety and power generation; all of them of technology basis, in order to ensure the solution of major problems and the improvement in the performance of such activities, encouraging the technological innovation.
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Business administration and management, and business development services in the nature of providing business acceleration and development of startups and disruptive and exponential businesses, all pertaining to the creation, development and improvement of technology-based products and services for mobility and urban mobility, connectivity and communication, logistics, airline operations and the aerospace industry, the use of drones, as well as the creation, development and improvement of technology-based products and services for precision agriculture, for areas of defense and public safety and power generation; all of the foregoing services to ensure the solution of major problems, improve the performance of such activities, and encourage technological innovation Educational services, namely, classes, instruction and practical training in the nature of educational demonstrations, all in the field of the creation, development and improvement of technology-based products and services for mobility and urban mobility, connectivity and communication, logistics, air operations and for the aerospace industry, the use of drones, as well as technology-based products and services for precision agriculture, for areas of defense and public safety and power generation; all of the foregoing services to ensure the solution of major problems, improve the performance of such activities, and encourage technological innovation Technology consultation, engineering services and innovation consulting services in the nature of advising others in the areas of technology-based product development, all provided to the aerospace, defense, agriculture and energy industries, in the fields of transportation engineering, precision agriculture, telecommunications technology, and aerospace engineering; studies of technical projects in the nature of conducting scientific feasibility studies and research and development of technology, all in the fields of transportation engineering, precision agriculture, telecommunications technology and aerospace engineering; all of the foregoing services to ensure the solution of major problems, improve the performance of such activities, and encourage technological innovation
A control platform for standalone systems is described, which integrates digital product and process information with data obtained by means of sensors, making use of artificial intelligence, such as artificial neural networks for example, for system feedback and decision-making in the autonomous execution of activities.
G05B 13/04 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
G05D 1/02 - Control of position or course in two dimensions
Thermal barrier curtain systems include a thermal barrier curtain and port and starboard anchor/hoist strap assemblies. The thermal barrier curtain includes forward and aft flexible air-impervious panels which are sealed about peripheral edges thereof so as to define a central thermal barrier region and separator elements positioned between and attached to the forward and aft panels within the central thermal barrier region so as to define a dead air space therebetween. Each of the port and starboard anchor/hoist strap assemblies includes an elongate strap, upper and lower attachment members positioned at opposed upper and lower ends of the elongate strap, an upper attachment loop adapted to receive and be attached to a respective connection element of the thermal barrier curtain, and an intermediate retaining loop which is adapted to receive and be attached to the lower attachment member of the anchor/hoist assembly.
In the event of a failed engine, an automatic takeoff thrust asymmetry compensation system (“ATACS”) for an aircraft improves capabilities to reduce VMCG and deal with the potential side-effects simultaneously. The system commands selected control surfaces (which can be e.g., rudder and/or ailerons and/or spoilers or any combinations thereof) for a short period of time, improving the capability to reduce the VMCG without increasing the penalty on system failures or poor handling qualities.
Actuation assemblies for emergency devices (e.g., inflatable life rafts carried on-board an aircraft) are provided with enhanced (preferably multiple) levels of security to preclude inadvertent unlatching and/or deployment but also allow access to an on-board emergency device removably positioned within a device bay of the vehicle which is normally covered by an access panel. The actuation assembly may be provided with a rotatable actuation shaft, a manually operated actuation lever fixed to the actuation shaft so as to rotate the actuation shaft in response to movement of the actuation lever between stowed and deployed conditions thereof, and a safety locking system operably connected to the rotatable shaft and having a locked condition which prevents operation of the actuation lever to thereby maintain the actuation assembly in a safe mode during normal vehicle operation, and an armed mode which allows the actuation lever to be moved into the deployed condition thereof.
Exhaust nozzles for outflow valves (OFVs) that are usefully employed in aircraft pressurization systems include an upstream solid (e.g., cylindrical) wall section and a downstream solid exhaust wall section fixed to the upstream solid wall section. The downstream solid exhaust wall section includes a circumferential portion defining a series of air intake perforations. A pair of vortex generators may also be provided upstream of the series of air intake perforations. The air intake perforations and optional vortex generators thereby allow air from the ambient pressure environment to be introduced into the boundary layer of pressurized air discharged by the OFV in the interior of the perforated region of the downstream solid exhaust wall section of the nozzle thereby reducing adverse pressure gradients therewithin which in turn results in a more attached air flow and hence less perceived noise.
B05B 1/34 - Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
G05D 16/20 - Control of fluid pressure characterised by the use of electric means
77.
Universal latch assembly to allow selective latch handle orientations
Latch assemblies are provided with a paddle lever having an outwardly extending actuator flange and a rotary actuator plate which includes a fixed actuator pin extending outwardly from the actuator plate and adapted to being operatively engaged with the actuator flange of the paddle lever when manually moved into the unlatched condition thereof. At least one pair of arcuate spirally patterned and circumferentially separated cam slots are defined in the rotary actuator plate such that a latch pin associated with a latch bolt is operatively received within a selected one of the cam slots. Movement of the paddle lever from the latched condition into the unlatched condition thereof responsively engages the actuator flange with the actuator pin thereby causing rotation of the actuator plate about a rotary axis thereof and movement of the latch pin within the selected one of the cam slots whereby the latch pin is retracted to unlatch a moveable component from a fixed component.
E05C 3/16 - Fastening devices with bolts moving pivotally or rotatively with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch
E05B 5/00 - Handles completely let into the surface of the wing
E05C 1/14 - Fastening devices with bolts moving rectilinearly with latching action with operating handle or equivalent member moving otherwise than rigidly with the latch the handle or member moving essentially towards, or away from, the plane of the wing or frame
78.
TWIN PROPULSOR, PARALLEL HYBRID, STREAMLINED NACELLE PROPULSION SYSTEM
An aircraft with an aft-fuselage propulsion system comprises a thermal engine, a first electric motor coupled to a first propulsor, a second electric motor coupled to a second propulsor, and a mechanical interlink system integrating the thermal engine, the first electric motor, the second electric motor, plural battery systems and associated power electronics, and cabling elements connecting the electric machines. An aircraft has plural mirrored aft-fuselage propulsion systems, each aft-fuselage propulsion system comprising a thermal engine, an electric motor, a propulsor, and a mechanical interlink system integrating the thermal engine, electric motor, and propulsor elements.
B64D 27/08 - Aircraft characterised by the type or position of power plants of piston type within, or attached to, fuselages
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 35/04 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
An aircraft with an aft-fuselage propulsion system comprises a thermal engine, a first electric motor coupled to a first propulsor, a second electric motor coupled to a second propulsor, and a mechanical interlink system integrating the thermal engine, the first electric motor, the second electric motor, plural battery systems and associated power electronics, and cabling elements connecting the electric machines. An aircraft has plural mirrored aft-fuselage propulsion systems, each aft-fuselage propulsion system comprising a thermal engine, an electric motor, a propulsor, and a mechanical interlink system integrating the thermal engine, electric motor, and propulsor elements.
B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants
B64D 29/04 - Power-plant nacelles, fairings or cowlings associated with fuselages
B64D 35/08 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission being driven by a plurality of power plants
80.
Thermally configurable structural elements especially useful for aircraft components
Thermally configurable structural elements (e.g., aircraft components such as an aircraft winglet spar) capable of assuming at least first and second structural configurations are provided whereby the structural element includes an integral actuation mechanism may be formed of sintered shape memory alloy (SMA) particles and sintered non-SMA particles formed by an additive layer manufacturing (ALM) process, such as 3D printing. The ALM process thereby provides by at least one thermally configurable region, and at least one non-thermally configurable region which is unitarily contiguous with the at least one thermally configurable region. The at least one thermally configurable region is capable of assuming at least first and second positional orientations in response to the presence or absence of a thermal input to thereby cause the structural element to assume the at least first and second structural configurations, respectively.
B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
B33Y 70/00 - Materials specially adapted for additive manufacturing
B33Y 80/00 - Products made by additive manufacturing
F03G 7/06 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for using expansion or contraction of bodies due to heating, cooling, moistening, drying, or the like
Processes for forming fiber reinforced composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin by a dried and cured film layer of a water-based primer paint material to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29K 63/00 - Use of epoxy resins as moulding material
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
82.
METHOD FOR COMPENSATE CAVITY EFFECT IN AIRCRAFT EMBEDDED ANTENNA IMPEDANCE AND EMBEDDED ANTENNA ARRAY FOR AIRCRAFT
INATEL / FUNDACAO INSTITUTO NACIONAL DE TELECOMUNICACOES (Brazil)
Inventor
Nunes, Sidney Osses
Bellei, Leandro Napoli
De Assis, Rodrigo Rodrigues
De Carvalho, Juliano Vilela
Sodre Junior, Arismar Cerqueira
Da Silva, Luís Gustavo
Abstract
Method for compensate cavity effect in aircraft embedded antenna impedance and Embedded antenna array for aircraft" The present invention relates to a method for compensate cavity effect in aircraft embedded antenna impedance by using radiofrequency (RF) absorber materials applied to entirely embedded antennas (non-protruding installation) particularly used in aircraft. The invention also refers to embedded antenna arrays for aircraft using radiofrequency (RF) absorber materials to enhance and/or optimize its impedance matching.
The non-limiting technology described herein is a failure managing framework for complex systems that determines and restores functionality of failing systems and sub-systems using a function-based intervention approach having ontological content such as provided in a System State Graph directed graph. An integration framework allows integration of multiple intervention definition paradigms and selects the best for the current scenario; modifies procedures according to current context by encapsulating operator's tacit knowledge; provides an additional safety net during application of intervention and allows both autonomous operations and assistance to a human operator in the loop.
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64F 5/60 - Testing or inspecting aircraft components or systems
An aircraft stores cryogenic fuel in one or more fuel tanks inside the aircraft fuselage or at other appropriate positions on the aircraft, and stores non-cryogenic fuel in plural standard jet fuel tanks e.g., inside the aircraft wings. A controller controls selective routing of non-cryogenic fuel or cryogenic (e.g., hydrogen) fuel to dual fuel engines. In one operating mode, the dual fuel engines normally use the cryogenic hydrogen fuel as the main fuel, and reserve the non-cryogenic fuel for application to the dual fuel engines only on an exception basis, thereby providing cleaner and more environmentally friendly operation.
An aircraft stores cryogenic fuel in one or more fuel tanks inside the aircraft fuselage or at other appropriate positions on the aircraft, and stores non-cryogenic fuel in plural standard jet fuel tanks e.g., inside the aircraft wings. A controller controls selective routing of non-cryogenic fuel or cryogenic (e.g., hydrogen) fuel to dual fuel engines. In one operating mode, the dual fuel engines normally use the cryogenic hydrogen fuel as the main fuel, and reserve the non-cryogenic fuel for application to the dual fuel engines only on an exception basis, thereby providing cleaner and more environmentally friendly operation.
A disinfection system and method for aircraft interiors based on a control of the intensity and irradiation of ultraviolet waves, particularly FAR-UVC in the range of 220nm to 224nm such that allows its application without causing clinical problems with humans, to be used during flight operation, as well as preparation of aircrafts, pre-boarding and deplaning.
A longitudinal control surface (30) for an aircraft (10) is described, in particular a turboprop/propfan aircraft with engines (12) mounted on the rear of the fuselage (11). This longitudinal control surface (30) is positioned in the structure (20) linking the engine to the fuselage. Also described is a longitudinal control system for an aircraft (10) with engines (12) arranged on the rear of the fuselage (11) close to a vertical tail, this system including means for controlling the longitudinal control surfaces (30) and the control surfaces (40) for distributing the longitudinal and stability control of the aircraft between the two surfaces, and an aircraft (10) including such a system.
A brushless DC motor is integrated with an aeropropulsive thrust generator that is hubless, not in tandem (co/counter) rotating propeller disks, and not having magnetic bearings.
A brushless DC motor is integrated with an aeropropulsive thrust generator that is hubless, not in tandem (co/counter) rotating propeller disks, and not having magnetic bearings.
One-piece molded thermoplastic L-shaped and Z-shaped support brackets are described for supporting wiring and/or tubing. The support brackets will include a lower support flange, a backing flange, and a junction region having a concave inner surface and a convex outer surface which integrally joins the lower support flange and the backing flange to one another at a substantially right angle. The support brackets may be provided with a unitarily molded nut plate boss and a metal threaded nut cylinder which is embedded within and overmolded with the nut plate boss. Alternatively, a wire, cable or tubing mount unitarily formed as a one-piece molded unit with one of the support flanges so as to dependently extend therefrom.
F16L 3/12 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing
H02G 3/04 - Protective tubing or conduits, e.g. cable ladders or cable troughs
An aircraft with the capability of taxiing with main engines off uses the energy stored in a mechanical flywheel to power a propulsor(s) providing taxiing thrust. The flywheel can store energy generated by the propulsor operating as a wind turbine and/or by a power turbine in fluid coupling with the exhaust of a gas turbine engine and/or an expansion turbine operating with bleed and/or APU air.
Installation of powered actuators in the leading edge of a control surface in order to have a better weight distribution. The systems described herein propose an actuation system with a static ground structure used to move a control surface of an aircraft. The actuation system, and the ground structure are aligned with the center of rotation of the control surface, providing the aircraft with flutter suppression. This proposal is an approach to use the actuator in a place favorable to the mass balancing and reducing or even dismissing the usage of mass balancing, saving weight and cost.
