3226results about "Fuselages" patented technology

An electric tilt rotor aircraft and a control system thereof. The aircraft comprises a fuselage (1), wings (2), horizontal stabilizers (3) and a landing gear system (4), wherein the fuselage (1) comprises a fuselage body and a rudder (10) for controlling and adjusting a flight direction of the aircraft; the wings (2) each comprise an integral wing box section (21), an aileron (22), a wing left / right nacelle (23) and a supporting rod left / right nacelle (24); left and right supporting rods are integrated on front sides of the integral wing box sections (21); the wing left / right nacelle (23) is connected to the integral wing box section (21) by means of a tilting shaft (25), and the wing left / right nacelle (23) rotates around the tilting shaft (25); the horizontal stabilizers (3) each comprise a horizontal stabilizer box section (31) and a horizontal stabilizer left / right nacelle (32); the horizontal stabilizer left / right nacelle (32) is connected to the horizontal stabilizer box section (31) by means of the tilting shaft (25), and the horizontal stabilizer left / right nacelle (32) rotates around the tilting shaft (25); the landing gear system (4) uses a tricycle landing gear system, and comprises a nose landing gear (41) and two main landing gears (42); brake systems are integrated in the main landing gears (42); and the nose landing gear (41) plays a role in balancing and controlling direction. By using the electric tilt rotor aircraft, urban air traffic can be realized.

A locking device having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.

Forming a shroud for an ACM by: forming a base having discrete sections including: a first section defining connecting features for connecting with a fixed ACM structure; a second section positioned adjacent to a compressor rotor when installed in the ACM; and a third section disposed adjacent to a drive ring bearing when installed in the ACM; forming the base includes: printing thermoplastic polymer surfaces, respectively from thermoplastic polymers, disposed against each other, a first thermoplastic polymer surface having a CTE, and a second thermoplastic polymer surface having a second CTE; forming a lower support section on the base by printing along the discrete sections of the base a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the shroud by depositing on the lower support section, along each of the discrete sections, via electrolysis deposition, a metallic coating.

An aircraft includes a battery pack mounted inside the aircraft, a vent coupled between the battery pack and a surface of the aircraft to at least partly define a vent path between the battery pack and the surface of the aircraft, and a burst membrane located in the vent path. The vent may be coupled to a rear upper portion of a wing or to an outboard side of a nacelle. The aircraft may also include a flexible coupling between the vent and the surface of the aircraft. The aircraft may also include a fairing over a vent outlet to provide a smooth surface for the vent outlet. The battery pack may include battery modules and an enclosure, the battery modules and the enclosure defining paths along which discharge from a thermal event can flow towards the vent.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and / or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and / or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

A door management system on an aircraft includes a fuselage extending along a longitudinal axis in a fore-aft direction parallel to forward flight, an opening in a sidewall of the fuselage, a door mounted on the sidewall to slide in the fore-aft direction between a closed position covering the opening and an open position revealing the opening, a cable attached to the fuselage and the door and a speed governor operatively coupled to the cable to limit a velocity of the door as it moves between the open position and the closed position.

An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

A rotating pylon assembly for aircraft thrust vectoring control. In embodiments, the rotating pylon assembly of embodiments includes a rotating sleeve disposed within a fixed boom of the aircraft, and configured to support a rotor assembly. The rotating pylon assembly includes a bearing assembly configured to functionally couple the rotating sleeve against an inner surface of the fixed boom. The bearing assembly enables the rotating sleeve to rotate against the inner surface of the fixed boom and about a longitudinal axis of the fixed boom. An actuator is configured to rotate the rotating sleeve about the longitudinal axis of the fixed boom. The rotating sleeve may cause the rotor assembly to be rotated or swung about the longitudinal axis of the fixed boom to position the rotor assembly in a position to vector the thrust provided by the rotor assembly based on a control command.

An aircraft includes a flight deck including a flight deck door configured to be moved between an open position and a closed position, a first monument, second monument, and a secondary barrier door moveably secured between the first monument and the second monument. The secondary barrier door is configured to fold into a stowed position in which a path to the flight deck is open, and unfold into a deployed position in which the path to the flight deck is closed.

The invention discloses an active thermal protection system for a high-speed aircraft and a using method of the active thermal protection system. The system comprises a liquid storage tank, an active thermal protection plate, a gas high-pressure storage tank and a thrust engine. The liquid storage tank, the active thermal protection plate and the gas high-pressure storage tank are connected in sequence to form a loop; a first electromagnetic valve and a fourth electromagnetic valve are respectively arranged on a connecting pipeline between the liquid storage tank and the active thermal protection plate and a connecting pipeline between the gas high-pressure storage tank and the liquid storage tank; the gas high-pressure storage tank is further provided with two gas paths, one gas path is connected with the thrust engine through a third electromagnetic valve, and the other gas path is communicated with the outside through a second electromagnetic valve. The liquid storage tank is used for storing a liquid heat-absorbing working medium; and the active thermal protection plate is filled with a catalyst. The active thermal protection system is high in heat absorption capacity, high-temperature and high-pressure gas can be generated through aerodynamic heat to do work, waste heat utilization is achieved, the thickness of a thermal insulation layer of the aircraft is reduced, the effective load of the system is increased, and the maneuverability of the aircraft is effectively improved.

The invention provides a high-lightning-stroke-resistant toughness continuous carbon fiber reinforced composite material, which is obtained by paving a plurality of layers of continuous carbon fiber resin prepregs and intercalation layers to obtain a preform and curing the preform through a conventional composite material molding process, each resin-based prepreg layer used in a preset layer number range close to the anti-lightning side is a first resin prepreg layer, the other resin-based prepreg layers are second resin prepreg layers, an intercalation is arranged between every two adjacent second resin prepreg layers, and the intercalation material is a micron conductive material with the surface density of 2-20 g / m < 2 >; wherein the resin in each resin-based prepreg layer is added with 2-10wt% of carbon nanomaterial, and the compressive strength of the rest resin-based prepreg layers after impact is higher than 250MPa. The composite material provided by the invention realizes integrated compounding of high lightning stroke resistance and high impact toughness. The anti-lightning performance of the composite material can meet the requirements of no internal layering and low fiber damage on the surface, and meanwhile, the compression strength CAI after impact can reach more than 200MPa.

A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.

There is provided a strut assembly for a wing of an aircraft. The strut assembly has a strut having an outboard end, an inboard end, and an elongate body. The outboard end is coupled to the wing of the aircraft, and the inboard end is coupled to a fuselage of the aircraft. The strut assembly further has at least one tensioner member having a first end coupled to the strut. The strut assembly further has a first fitting element having a through opening receiving a first portion of the strut and a bearing surface facing inboard. The strut assembly further has a second fitting element having a through opening receiving a second portion of the strut and a bearing surface facing outboard. The at least one tensioner member maintains tension in the strut, to keep the strut taut and in tension, to prevent or to minimize drooping of the strut.

Provided are: a window material and a light-transparent roof material which can autonomously change white turbidity in accordance with the temperature, and which have a simple structure and are easy to manufacture; and a vehicle, a ship, or an airplane, and a building comprising the window material and / or the light-transparent roof material. A window material or a light-transparent roof material according to the present invention comprises at least one light-transparent base material layer and at least one pressure-sensitive adhesive layer. The pressure-sensitive adhesive layer is formed from a pressure-sensitive adhesive composition containing, with respect to 100 parts by mass of a pressure-sensitive adhesive agent, 1-20 parts by mass of a thermosensitive noncrosslinked polymer and 1-100 parts by mass of thermosensitive crosslinked fine particles. The refractive index of the thermosensitive crosslinked fine particles is reduced as the temperature increases, and the reduction rate of the refractive index is larger in the vicinity of the melting temperature of the thermosensitive crosslinked fine particles than in a temperature range other than the vicinity of the melting point. The adhesive power of the pressure-sensitive adhesive composition is reduced as the temperature increases, and the reduction rate of the adhesive power is larger in the vicinity of the melting temperature of the thermosensitive non-crosslinked polymer than in the temperature range other than the vicinity of the melting point.

Embodiments relate generally to systems and VTOL aerial vehicles. An example central server system comprises: at least one central server system processor; and central server system memory storing central server system program instructions accessible by the at least one central server system processor, and configured to cause the at least one central server system processor to: receive vehicle registration data associated with a manned VTOL aerial vehicle; and determine that the vehicle registration data is associated with a manned VTOL aerial vehicle that is authorized to communicate with the central server system. Some embodiments include VTOL aerial vehicles in communication or communicable with a central server system.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and / or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

An aircraft comprising an aircraft transceiver to transfer data to and from the aircraft by free-space-optical communication when parked. The aircraft transceiver comprises a transmitter to generate outgoing light carrying aircraft-to-ground data; a lens to collimate the outgoing light to generate a collimated beam; a beam steering device to transform the collimated beam to generate a steered beam; a control system to operate the beam steering device to adjust an angle of the steered beam; and a receiver to sense incoming light carrying ground-to-aircraft data. The receiver receives the incoming light via the beam steering device and the lens. Also a vehicle with a similar transceiver to transfer data to and from a parked aircraft by free-space-optical communication.

The present invention relates to a protective foldable cage (100) adapted to flying drones. It comprises several ribs linked at their extremities by a ring and comprising on their length several connection points allowing strings to join each of the adjacent ribs. The length of the string corresponds to the maximal angular shift between the first and the last ribs. The protective cage further comprises easily removable locking means adapted to maintain the ribs at predetermined relative angular position once deployed. The present invention further relates to a system comprising such a protective cage and a drone support, as well as a method of protection of flying drones.

A door assembly configured to be mounted in an opening of a cabin area of an aircraft. The door assembly includes a door configured to be movable between a deployed position across the opening and a stowed position out of the opening. A lock is mounted to the door and movable between a locked position and an unlocked position. An engagement assembly is mounted to the door and movable between an engaged position and a disengaged position. The engagement assembly includes a plunger, a lock mechanism, and an elongated member that extends between the lock and the lock mechanism. In the engaged position, the lock mechanism and the elongated member position the plunger in an extended position outward from the door. In the disengaged position, the lock mechanism and the elongated member position the plunger in a retracted position relative to the door.

The invention discloses a sweating and cooling composite thermal protection structure based on a porous metamaterial, which belongs to the technical field of active thermal protection of aircrafts and comprises a layered metamaterial composite structure body. The layered metamaterial composite structure body sequentially comprises a spectrum stealth porous superstructure layer, an infrared thermal stealth porous superstructure layer and a hydrogel filling layer from top to bottom. The infrared thermal stealth superstructure porous material is used as a core, the anisotropic thermal conductivity characteristic of the infrared thermal stealth porous superstructure layer is achieved through the micro-nano structure design and different porosity distribution, transfer of surface heat flow in the horizontal direction and transfer of heat to the coolant phase change layer in the vertical direction can be accelerated, a sweating cooling mechanism is triggered, and the heat transfer efficiency is improved. Local high temperature of the surface is effectively eliminated, the average temperature of the surface is rapidly reduced, and the heat radiation amount is reduced, so that efficient thermal protection is achieved, the infrared thermal stealth function is achieved, and the spectrum stealth requirement is also met by combining the surface spectrum stealth porous superstructure layer.

A method for automated spacecraft design includes receiving mission parameters provided by a client for spacecraft design, generating one or more concept designs based on the received mission parameters, a concept design including one or more components selected for each subsystem included in a designed spacecraft, for the concept design, automating a generation of a frame design that includes a plurality of thermal management components to be formed through a single metal-additive manufacturing process, performing a series of analyses or simulations to evaluate a performance of the frame design, and generating a digital twin representing a virtual representation of the designed spacecraft based on the generated frame design and the series of analyses and simulations.

The invention relates to a heat protection structure of a dredging coupling semi-open type dissipation structure, which belongs to the technical field of heat protection of high-speed aircrafts and comprises a dredging structure shell, a dredging structure capillary core body, a dredging structure working medium, a semi-open type dissipation structure, a semi-open type dissipation working medium, a semi-open type dissipation structure exhaust pipe and a semi-open type dissipation structure control switch. Aiming at a local high-heating part of a hypersonic aircraft, on the basis of semi-active dredging type uniform-temperature heat protection, phase change heat absorption and discharge heat dissipation of an active dissipation working medium are combined, and heat absorption and dissipation ways are increased, so that the total heat amount is effectively reduced while the internal heat distribution of the structure is optimized, and the heat dissipation efficiency is improved. Internal heat control and management of the structure are realized through coupling of dredging semi-active heat protection and active dissipation, the problem of non-ablative heat protection in an extreme environment is solved, and a feasible heat protection technical approach is provided for performance improvement of high-speed aircrafts in the future.

A modular vertical take-off and landing aircraft for transporting persons and / or loads, comprising a flight module with multiple drive units arranged on a supporting framework structure, each drive unit having an electric motor and a propeller operatively connected to the electric motor, a transport module having a conveying pod and a connection device for connecting the conveying pod to the flight module. The connection device has an elongated shaft, one end of which is attached to the conveying pod, and a coupling device for connecting the flight module to another end of the elongate shaft of the transport module.

An embodiment herein provides a re-configurable unmanned aerial vehicle that re-configures its shape based on the shape, size, weight of a payload, and efficiently performs payload delivery in real-time. The re-configurable unmanned aerial vehicle includes one or more rotor units placed at corners and is connected by one or more scissor units. The re-configurable unmanned aerial vehicle approaches the payload in a first location, and analyses the position and dimension of the payload with a camera, that enables the one or more scissor units to adjust its length by at least one elongation or compression following size and shape of the payload and fit the payload within the re-configurable unmanned aerial vehicle. The re-configurable unmanned aerial vehicle takes off carrying the payload from the first location and lands at a second location.

A wing fuselage joint for an aircraft having joining members which include a first configuration and a second configuration. The joining members of the first configuration include a platform and bracket configured to pivot in a lateral plane and translate in a longitudinal direction. The joining members of the second configuration include a platform and bracket configured to pivot in a longitudinal plane and translate in a lateral direction. The joining members of either configuration join the fuselage structure and the spar of an aircraft together.

The present invention relates to a transparent colorless spinel microcrystalline glass, and preparation and a use thereof. The microcrystalline glass contains (Zn, Mg)Al2O4 as a principal crystalline phase and ZrO2 as a secondary tetragonal crystalline phase, and does not contain TiO2. In mole percentage on an oxide basis, an oxide contained therein satisfies the following relational expressions: Al2O3 / (MgO+ZnO)=1.40~2.00, and K2O+Li2O+Na2O+B2O3) / (SiO2+Al2O3)=0.10~0.20. The microcrystalline glass is obtained by performing heat treatment at a temperature of being not greater than 800°C. The microcrystalline glass has a transmittance of 85.0% or above for light having a wavelength of 550 nm. Anti-abrasive paper drop testing is performed on the microcrystalline glass by using 80-mesh abrasive paper, the average anti-abrasive paper drop height of the microcrystalline glass is greater than or equal to 1.00 m; the Vickers hardness is 800kgf / mm2 or above, and the fracture toughness of the microcrystalline glass is 1.200MPa·m1 / 2 or above. According to the present invention, the colorless transparent spinel microcrystalline glass having high transparency and excellent mass productivity can be obtained, and the microcrystalline glass can be subjected to chemical strengthening to obtain a chemically strengthened microcrystalline glass having excellent deep stress characteristics.

A sidewall assembly includes a window and a sidewall portion having an inner-facing side and at least partially surrounding the window. The sidewall assembly further includes a transparent display panel coupled to the sidewall portion covering the inner-facing side of the sidewall portion and the window. The sidewall assembly further includes a display controller operatively coupled with the transparent display panel. The sidewall assembly further includes a window shade movable between an open position to allow light to pass between the window and the transparent display panel and a closed position to obstruct light from passing between the window and the transparent display panel. The sidewall assembly further includes a blackout feature disposed between the window and the transparent display panel and a blackout control device configured to control the blackout feature to selectively obstruct light from passing between the window and the transparent display panel.

Systems, devices and methods related to unmanned aerial vehicles and landing systems are described herein. One example disclosed unmanned aerial vehicle comprises a vehicle body comprising an airfoil shape, a plurality of rotors, a payload void within the airfoil shape profile, and a rotatable payload bay disposed within the payload void. A payload delivery system is also described. The payload delivery system comprises a payload void, a payload bay, at least one actuator operative to rotate the payload bay with respect to the payload void, and a payload controller operative to eject a payload from the payload bay. Several landing systems and devices for unmanned vehicles are also described. One example landing device comprises a frame comprising a rear surface operative to attach the frame to a vertical glass surface and an aircraft support element operative to receive and support an unmanned aerial vehicle.