2145results about "Fuselages" patented technology

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 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.

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.

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.

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.

An aircraft (10) comprising a first swept wing (14A) and a second swept wing (14B), each swept wing having an inner wing section (26A, 26B) comprising an integrated payload fuselage and an outer wing section (30A, 30B) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section, a central region (12) where the first swept wing meets the second swept wing, a first transition region (23A) where the first inner wing meets the first outer wing section, a second transition region (23B) where the second inner wing meets the second outer wing section, in which at least one extension (44) having an internal volume is provided behind the trailing edge of the wings, the at least one extension being disposed in the central region.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one precondition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one precondition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one precondition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

An extendable holding device including a supply line holding unit, a fastener and an adaptable spacer. The supply line holding unit includes an at least partly enclosed holding opening for holding a supply line. The fastener is configured to mount the supply line holding unit to a support structure. The adaptable spacer is configured to be arranged between the supply line holding unit and the support structure to which the holding device is to be mounted. The adaptable spacer is extendable in a longitudinal direction of the fastener and is temporarily lockable at least at a first and a second predetermined length.

The invention provides a bionic hollow petal-shaped SiC fiber porous thermal insulation material as well as a preparation method and application thereof, and belongs to the technical field of thermal insulation materials. The preparation method comprises the following steps: taking a viscose-based carbon fiber felt as an initial structure template, dipping the carbon fiber felt in siloxane sol, taking out the carbon fiber felt, and carrying out suction filtration to remove redundant sol on the surfaces of carbon fibers; curing the impregnated carbon fiber felt, and carrying out heat treatment to obtain the carbon fiber felt of which the carbon fiber surface is covered with a uniform SiC coating; and carrying out thermal oxidation treatment on the carbon fiber felt with the SiC coating to obtain the bionic hollow petal-shaped SiC fiber porous thermal insulation material. Compared with a traditional sol-gel method, the method has the advantages of being short in preparation period, low in cost, small in volume shrinkage rate and the like, and the obtained bionic hollow petal-shaped SiC fiber porous heat insulation material has good rebound resilience and excellent high-temperature heat insulation performance and has wide application prospects in a high-temperature oxidation environment.

A floor system for a cabin of a vehicle is proposed, the floor system including a floor panel having a bottom layer, a top layer and a continuous stiffening structure having an alternating arrangement of elongated first depressions and elongated protrusions arranged between the bottom layer and the top layer, an elongated cover component, and at least one seat rail component. The cover component has an upper surface, a lower surface, and an elongated second depression reaching from the upper surface to the lower surface and having a shape that corresponds to the shape of the first depressions. The cover component is configured to be mounted inside a first depression that is accessible through an elongated cutout extending along a depression of the stiffening structure. The at least one seat rail component is attachable to the cover component to provide a seat rail along the floor panel.

An aircraft 10 comprising a first swept wing 14A and a second swept wing 14B, each swept wing having an inner wing section 26A, 26B comprising an integrated payload fuselage 20 and an outer wing secti

A system includes a transmitting horn coupled to a first robotic arm and positionable in immediate non-contacting proximity to a transparency, and configured to emit an emitted signal comprising a focused energy beam for impingement on the transparency. The system further includes a receiving horn coupled to a second robotic arm and positionable relative to the transmitting horn in immediate proximity to the transparency, and configured to receive a received signal comprising at least a portion of the emitted signal after transmission through or reflection off of the transparency. The system also includes a processor configured to move the first robotic arm and the second robotic arm in a coordinated manner along a preprogrammed measurement path, and determine at least one transparency characteristic based on an analysis of the received signal.

The invention discloses an Al-Mg-Zn aluminum alloy plate with excellent strong plasticity and light weight characteristics as well as a preparation method and application of the Al-Mg-Zn aluminum alloy plate. The alloy comprises the following components in percentage by mass: 5.0%-5.5% of Mg, 1.5%-2.0% of Zn, 0.4%-0.5% of Mn, 0.1%-0.3% of Cu, 0.15%-0.25% of Sc, 0.1%-0.15% of Zr, 0.05%-0.15% of Ag, less than or equal to 0.1% of impurities and the balance of Al. The density is not more than 2.63 g / cm < 3 >, the tensile strength is not less than 470 MPa, and the ductility is not less than 23%. The preparation method comprises the steps of high-purity raw material smelting and casting, two-stage homogenization, hot rolling, intermediate annealing, cold rolling, solid solution treatment and single-stage aging. Wherein the total pressing amount of hot rolling is 80-85%, the total pressing amount of cold rolling is 20-35%, and the single-stage aging time is 120-140 DEG C * 16-24 h. The microstructure of the alloy is characterized in that the average size of dispersed AlSc particles is smaller than or equal to 100 nm, the area fraction of deformed grains is larger than or equal to 70%, the average size of nanometer beta-AlMg and T-Mg (Al, Zn) composite precipitated phases is smaller than or equal to 20 nm, the number density is larger than or equal to 1 * 10 < m >, the area fraction of micron-order second phases is smaller than or equal to 0.5%, and the alloy is only formed by impurity Fe. According to the method, the traditional two-stage aging process is simplified, low density, high strength and high plasticity are synchronously improved, and the method is suitable for large-scale industrial application.

A barrier door system to control movement of persons through an opening in an interior space of an aircraft. The barrier door system having a frame with outer members that extend around a gap. A barrier door has a first panel and a second panel that are pivotally connected together with the barrier door pivotally connected to the frame. The barrier door is movable between a stowed position and a deployed position. The stowed position includes the first panel and the second panel folded together in an overlapping configuration and positioned in the gap in the frame and away from the opening. The deployed position includes the first panel and the second panel positioned away from the gap and extending across the opening.

The present invention discloses a porous material transpiration cooling leading edge structure, which includes multiple layers of porous material layers and a cooling cavity provided on one side of the multiple layers of porous material layers. A coolant supply channel is provided in the cooling cavity, and the coolant supply channel is used to supply coolant to the cooling cavity. The multiple layers of porous material layers include an outer layer, an intermediate layer, and an inner layer, and the material of the inner layer is a shape memory alloy porous material. The present invention can adaptively adjust the porosity of the porous material, automatically adjust the usage amount of the coolant, effectively improve the usage efficiency of the coolant, and further enhance the thermal protection effect in the high-temperature tip region. Moreover, the shape memory alloy material can be reused. The porous material transpiration cooling leading edge structure can be used for structures such as the nose cone of an aircraft, the leading edge of a rudder, and the leading edge of a wing that are subjected to more high-temperature heat fluxes.

A preparation method of porous hafnium carbide superhigh-temperature ceramic is characterized by comprising the following steps: dispersing graphene oxide in a solvent to form a graphene oxide dispersion liquid, mixing a monomer hafnium source solution with the graphene oxide dispersion liquid, and carrying out hydrothermal treatment on a hafnium oxide carbon precursor network structure to obtain the porous hafnium carbide superhigh-temperature ceramic. The organic-inorganic hybrid precursor is subjected to two-stage heat treatment, the first stage is inorganic treatment, the second stage is carbon thermal reduction reaction, and the porous hafnium carbide ultrahigh-temperature ceramic material is obtained. Graphene oxide is used as a structure-directing agent and an in-situ carbon source, a monomer hafnium source is uniformly anchored on the surface of a GO sheet layer on the molecular scale, an organic-inorganic hybrid precursor is formed, after the precursor is subjected to hydrothermal crosslinking, Hf species and a carbon skeleton are highly mixed on the nanoscale, and the Hf / GO composite material is obtained. And the subsequent carbon thermal reduction reaction can be efficiently completed in a low-temperature interval of 1300-1450 DEG C.

The invention provides an aircraft passenger accommodation unit (1000) comprising a seat (100), a shell (110) defining an opening (120), and a door (130). The door (130) is translatable along a first path across the opening (120) between a closed position in which passenger egress through the opening (120) is at least partially blocked, and an open position which allows passenger access between a seat (100) and an aisle (300). The door (130) is translatable in a second direction that is transverse to the first direction, between a first configuration and a second configuration. In the first configuration, the door (130) is translatable across the opening (120) along the first path, and when the door (130) is in the second configuration, the door (130) is translatable across the opening (120) along a second path. The invention also provides a door arrangement and a method of using a door.

A system and a method include a substrate having a surface, such as an exterior surface of a vehicle. An electrophoretic display is disposed on the surface. A control unit is coupled to the electrophoretic display. The control unit is configured to selectively change one or more properties of the electrophoretic display.

An aircraft wing having a fixed wing and a moveably mounted wing tip device is disclosed. A first cable harness and a second cable harness which are received in a protective sleeve extend between the fixed wing and the wing tip device. The protective sleeve is in a secured configuration in which at least two opposing parts of the protective sleeve are secured together between the first cable harness and the second cable harness to provide the sleeve with a first channel in which the first cable harness is received a second channel in which the second cable harness is received, and a webbing region extending between the first channel and the second channel such that the first and second cable harnesses are held apart by the webbing region.

The buffering structure capable of being pneumatically separated is installed between an outer cover and protected equipment and is restrained on the periphery of the protected equipment through certain extrusion force between the outer cover and the protected equipment, and impact load energy transmitted to the protected equipment is reduced through deformation energy absorption of the buffering structure capable of being pneumatically separated. Impact protection of protected equipment on an aircraft can be achieved, normal work of the equipment is guaranteed by means of pneumatic load separation, the inverted-cone-shaped structure is arranged to increase the pneumatic load during separation, separation reliability is guaranteed, and separation time is shortened; the weak part of the protected equipment is avoided by optimizing the transmission path of the impact load, the protected equipment is more effectively protected, and meanwhile, the structural weight is effectively reduced.