469results about "Spars/stringers" patented technology

An assembly for an aircraft includes a wing assembly, a plurality of underwing heat exchangers, and a mounting assembly. The wing assembly includes a wing body. The plurality of underwing heat exchangers are arranged along the wing body in a longitudinal direction. The plurality of underwing heat exchangers includes a first underwing heat exchanger and a second underwing heat exchanger. The first underwing heat exchanger is longitudinally adjacent the second underwing heat exchanger. The mounting assembly includes a first heat exchanger bracket, a second heat exchanger bracket, and a first support bracket. The first heat exchanger bracket is fixedly mounted to the first underwing heat exchanger. The second heat exchanger bracket is fixedly mounted to the second underwing heat exchanger. The first heat exchanger bracket and the second heat exchanger bracket are pivotably mounted to the first support bracket. The first support bracket is fixedly mounted to the wing body.

The invention discloses a deformable wing with the characteristics of large unfolding-folding ratio and high bearing capacity. The deformable wing comprises a bearing structure, a driving mechanism, a wing surface dimensional structure and an accessory structure, the bearing structure comprises a plurality of groups of telescopic mechanisms, wing ribs and corner boxes; the accessory structure comprises a mounting plate, and the mounting plate is connected with the machine body; each group of telescopic mechanisms comprises a plurality of stages of telescopic rods which are arranged along the chord length direction and are fixed on the mounting plate; the wing ribs are arranged in the wingspan direction and are connected with the multi-stage telescopic rods through the angle boxes to form a wing framework; the driving mechanism penetrates through the hollow parts of the wing ribs, and two ends of the driving mechanism are respectively connected with the mounting plate and the wing rib on the outermost side of the wing; the wing skeleton is externally coated with the wing surface dimensional structure to form a wing shape.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

Aerodynamic lifting structures, such as aircraft wings, having embedded engines and associated methods and systems are disclosed herein. A wing assemblies configured in accordance with embodiments of the present technology can include, for example, an upper wing portion, a lower wing portion, and a plurality of independent ducts positioned between the upper wing portion and the lower wing portion. Each duct can extend between a corresponding inlet positioned toward a leading portion of the wing assembly and a corresponding outlet positioned toward a trailing portion of the wing assembly. The wing assembly can further include a plurality of fans and a plurality of electric motors operably coupled to the plurality of fans. The fans and electric motors are positioned in the corresponding individual ducts and the fan is rotatable to propel fluid received in the inlet through the duct to create lift.

The invention discloses a tilt-rotor vertical take-off and landing aircraft and a vertical take-off and landing balance system.The tilt-rotor vertical take-off and landing aircraft and the vertical take-off and landing balance system.The tilt-rotor vertical take-off and landing aircraft comprises an aircraft body, wings are symmetrically arranged on the two sides of the aircraft body, wingtip small wings are arranged at the tail ends of the wings, and the wingtip small wings are arranged on the aircraft body. A pair of tilting mechanisms symmetrically arranged relative to the fuselage is arranged at the front end of the fuselage, each tilting mechanism comprises a front propeller, the front propellers are connected with the fuselage through tilting motor structures, and a micro turbojet engine is arranged at the rear end of the fuselage and connected with the fuselage through a fixing frame. The vertical take-off and landing balance system comprises a hardware part and a software part. Smooth transition between a vertical take-off and landing mode and a horizontal flight mode is achieved through optimized mode switching control logic.

Disclosed here are unmanned aerial vehicle embodiments including some embodiments having a fuselage, tail, and wings including example embodiments with an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle configured with direct connection to moveable flight control surfaces.

A composite material combined layer wall plate structure suitable for combined connection of wings comprises a main box section skin and a plurality of reinforcing ribs which are integrally cured and formed, the front edge and the rear edge of the main box section skin are sequentially provided with recesses, and a front sunken edge for lap joint of the front edge skin and a rear sunken edge for lap joint of the rear edge skin are formed; a front beam reinforcing rib used for being connected with a front spar web is fixedly arranged at the bottom of the transition area of the front sunken edge and the main box section skin body, and a rear beam reinforcing rib used for being connected with a rear spar web is fixedly arranged at the bottom of the transition area of the rear sunken edge and the main box section skin body. The connecting mode of the wall plate and a related structure is simplified, the number of parts is reduced, the assembling efficiency can be improved, and dismounting, replacing and maintaining of an airplane in the using and maintaining process are facilitated.

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

An electric aircraft according to an embodiment of the present invention comprises: a fuselage equipped with a power means, a front spar and a rear spar extending from the fuselage to an end of a wing, and a plurality of ribs extending from the rear spar to the front spar and coupled to the front spar and the rear spar, in which a plurality of solid state batteries are mounted in a plurality of individual spaces partitioned by the front spar, the rear spar, and the plurality of ribs, respectively, and the front spar and the rear spar are used as members for serial connection of the plurality of solid state batteries, and the plurality of ribs are used as members for parallel connection of the plurality of solid state batteries.

A device to control movement of fluid that is emitted from an aircraft engine that is mounted to a wing of an aircraft. The device includes a support member positioned on an exterior of the aircraft and having an elongated shape with a first end connected to the wing and a second end connected to the fuselage. The support member has a first sectional size. A deflector shield is mounted to the support member and positioned on the exterior of the aircraft. The deflector shield has a larger sectional size than the support member. The deflector shield has an outer edge that extends around the support member and is positioned radially outward from the support member.

A wing-fuselage truss joint assembly for an aircraft includes joining members secured to the aircraft's wing and fuselage structures. The joining members each include forward and aft wing joints and forward and aft fuselage joints connected by an upright member. The forward joining members are pivotally connected using interconnecting members and the aft joining members are connected using aft truss members. The forward-right and aft-right joining members and the forward-left and aft-left joining members are connected by truss link members and diagonal truss link members. The wing-fuselage truss joint assembly is configured to reduce forces experienced by the wing from being transferred to the aircraft fuselage.

The variable-thickness wing structure comprises a composite corrugated skin, a connecting rod assembly and a reinforcing plate, a fixing plate is fixedly arranged in the left side of the composite corrugated skin, a fixing frame is mounted on the outer side of the right end of the fixing plate, and a mounting plate is integrally and fixedly mounted on the right side of the fixing frame; an electric hydraulic rod is arranged in the middle of the left side of the mounting plate, and a connecting plate is fixedly mounted at the output end of the electric hydraulic rod; and a connecting rod assembly is mounted on the outer side of the connecting plate. The invention belongs to the technical field of wing structures, and aims at solving the problems that in the prior art, the thickness deformation degree of the upper side and the lower side cannot be accurately controlled at the same time, the limitation is large, and the supporting effect on the deformed composite corrugated skin is poor. The supporting device has the technical effects that the thickness deformation degree of the upper side and the lower side can be accurately controlled at the same time, the limitation of deformation is reduced, and the supporting effect on the deformed composite corrugated skin is improved.

The invention provides a central wing box and an electric tilting helicopter composite material wing, and belongs to the technical field of helicopter structural design, the central wing box adopts a double-beam type structure, the central wing box comprises a force-bearing covering cap, a front beam, a rear beam, a lower skin and wing ribs, and the front beam, the rear beam and the lower skin jointly form a battery installation room. The battery mounting room is divided into a plurality of battery cabins through a plurality of wing ribs, each battery cabin is provided with a plurality of battery mounting bases, and the force-bearing opening cover is positioned at the upper part of the battery mounting room; the front beam, the rear beam, the first central wing rib and the second central wing rib are connected with the fuselage. According to the invention, the integrated design of the wings is realized, the purpose of weight reduction is realized, the problem of difficult assembly and adjustment of the aircraft body and the wings is solved, the problem of large-opening load transfer caused by battery installation is solved, and the maintainability is greatly improved by adopting the bolt connection measures of the covering caps with uniform specifications.

An aircraft wing assembly includes a wing box including an upper surface, a lower surface, and a leading edge structure connecting the upper surface to the lower surface and secured to the upper surface at a connection point. The aircraft wing assembly includes a drive mechanism secured to the wing box and a high lift device mounted to the drive mechanism. The drive mechanism is configured to move the high lift device between a retracted position and an extended position in use, and wherein the high lift device is configured to overlap the connection point when in the retracted position.

The utility model discloses an eVTOL aircraft wing body fairing which comprises a skin, a rear supporting beam and a front supporting beam, the front supporting beam is connected with the middle of the skin through a connecting piece and supports the middle of the skin, the rear supporting beam is installed on the right portion of the skin through a connecting piece, and the skin is a carbon fiber composite material piece. The rear sides of the supporting beam and the front supporting beam are connected with supporting ribs, the side edges of the supporting ribs are connected with a skin, a thickening area is arranged on the periphery of the skin, and the skin is connected with the eVTOL aircraft, the rear supporting beam and the supporting ribs through the thickening area in cooperation with connecting pieces. The fairing is good in aerodynamic performance, the bolts are adopted as connecting pieces and do not protrude out of the aerodynamic surface, meanwhile, the supporting ribs, the front supporting beam and the rear supporting beam are adopted for supporting the skin, the precision of the appearance of the skin is ensured, and the aerodynamic performance is consistent with the design.

To provide a method of manufacturing structural components that is reliable, cost-effective, and solves the drawbacks associated with known manufacturing methods.SOLUTION: A structural component (1) having a plurality of subpanels (5) joined to each other, each including a subskin defined by a first layer of composite material, at least one stringer, and at least one rib fixed to an inner surface of the subskin and continuous subwalls defined by the bonded outer surfaces of the subskins of the subpanels (5) connected each other, a second layer (10) of composite material is laminated over the first layer to define a continuous external overskin layered over the subwalls, and a skin (4) is defined by a set of the subskin and overskin, the first layer and a second layer (10).SELECTED DRAWING: Figure 8

A wing for a mobility apparatus include battery modules a plurality of ribs that are spaced apart from one another in a longitudinal direction of the wing, the plurality of ribs respectively defining a plurality of first through-holes through which the battery modules pass, a plurality of first flange portions that are respectively disposed at the plurality of ribs along edges of the first through-holes, the plurality of first flange portions defining battery seating surfaces that support the battery modules, and a spar that supports the plurality of ribs.

Truss-braced wing aircraft engine mounting and associated systems are disclosed. An example aircraft includes a fuselage including a central structural section, a wing extending from the fuselage, a truss extending from the central structural section and coupled to the wing, a pylon coupled to the central structural section, and an engine coupled to the pylon, wherein the pylon is positioned at an angle substantially 45 degrees from a horizontal plane and a vertical plane.

A lightweight structure for a vehicle or aircraft includes a longitudinal member with a base bridge, having a first collective conductor and a transversal member with a central bridge and transversal bridge with a first connection conductor extending on a first surface of the transversal bridge and on a second surface of the transversal bridge oriented opposite the first surface, and a second connection conductor extending separately from the first connection conductor. The transversal member is connected to the base bridge at the first end section, so the first connection conductor contacts the first collective conductor of the base bridge. The lightweight structure includes a carbon fiber structural battery (CFSB) connected with the central bridge of the transversal member, a first collector of the CFSB electrically connected to the first or second connection conductor and a second collector of the CFSB electrically connected to the other connection conductor.

A rib mounting assembly for an aircraft is disclosed including a rib post and a seal member. The rib post has a rib post foot to mount with a longitudinal spar and a rib post web upstanding from the rib post foot. The seal member has a seal body and a mounting flange. The mounting flange is mounted with the rib post foot and the seal body extends from an end of the rib post.

An aircraft wing apparatus includes a plurality of wing-skin sections, an extendable spar assembly, and a controller. The plurality of wing-skin sections includes a first wing-skin section and a second wing-skin section. The extendable spar assembly includes a first spar member coupled with the first wing-skin section and a second spar member coupled with the second wing-skin section. The controller is constructed and arranged to move the second spar member to predefined positions relative to the first spar member to place the plurality of wing-skin sections into predefined configurations. The predefined configurations including a stowed configuration, a first deployed configuration, and a second deployed position that is different from the first deployed position.

A clamp (200) is provided for securing an aircraft wing skin to an aircraft wing support structure. The clamp (200) comprises a means (208) for operating the clamp between a non-clamping configuration and a clamping configuration; an operation interface (211) configured to facilitate movement and / or operation of the clamp by an automated apparatus. The operation interface (211) comprises an attachment arrangement configured to facilitate attachment to a corresponding attachment arrangement provided by an automated apparatus. The means (208) for operating the clamp between a non-clamping configuration and a clamping configuration is provided with (i) an interface configuration configured to facilitate operation of the means for operating the clamp between a non-clamping configuration and a clamping configuration by an automated apparatus, and / or (ii) a prime mover for operating the clamp between a non-clamping configuration and a clamping configuration, the prime mover being operable by an automated apparatus.

The utility model discloses a deformable wing unit structure and a deformable wing applying the same, and relates to the technical field of flight wings, the deformable wing unit structure comprises a leading edge wing, a trailing edge wing, a driving mechanism and flexible deformable wing ribs, the horizontal two sides of the leading edge wing and the trailing edge wing are connected through the wing ribs, one end of the driving mechanism is connected with the leading edge wing, and the other end of the driving mechanism is connected with the trailing edge wing. Driving mechanisms are correspondingly arranged on the upper side and the lower side of the leading edge wing in the vertical direction, and each driving mechanism comprises fibers and conductive fibers which are wound with each other; when the conductive fibers are electrified, a heat source can be provided, and the fibers generate strain by utilizing the heat source, so that the driving mechanisms arranged on the upper side and the lower side form an antagonism structure to realize upward and downward bending deformation, the weight is light, the structure is simple, and the energy consumption of the aircraft is effectively reduced; the shape of the wings can be changed smoothly, smoothly, autonomously and continuously along with the change of the external environment, so that the performance in the whole flight process is kept optimal, and the cost can be reduced.

The invention discloses a built-in main control actuator connecting structure of an aircraft wing box, and relates to the technical field of aircraft structure design, an actuator is located in the aircraft wing box structure, an actuating rod of the actuator penetrates through an actuator rod avoiding hole of the aircraft wing box structure, and the actuating rod stretches out and draws back to cooperate with the actuator to rotate up and down in the wing box to achieve deflection of a control surface. The invention is suitable for small airfoils and small and medium-sized airfoils with low airfoil height, solves the problems that the small airfoils of the small airfoils are small, the trailing edge space is limited, and a control surface actuating system cannot be mounted, and avoids the problem that the aerodynamic efficiency is influenced as an actuating structure is arranged outside the airfoils; the structure of the actuator connector is designed and arranged on the front main bearing beam of the wing box, the load transfer continuity of the wall plate structure is not broken, meanwhile, the actuating load can be directly diffused to the skin through the support connector, and the load transfer efficiency is higher. By separating a daily inspection and maintenance passage from a disassembly and assembly passage, the opening size of the airfoil wall plate is reduced, the load transfer capacity of the lower airfoil skin is guaranteed, and structural weight reduction is facilitated.

Apparatus and methods for ultrasonic inspection of elongated composite members in a single scan pass using pulse echo phased arrays (97, 98, 99) operating in a bubbler method. The system concept is fully automated by integrating an inspection NDI probe assembly (32, 34, 36) to a robot (100) and using the robot to move the inspection NDI probe assembly along the part (i.e., outside of an inspection tank); and by integrating tooling fixtures that move out of the way as the inspection NDI probe assembly travels along the length of the part during the inspection. In addition, the system allows for generally elongated composite members having lengthwise variation in shape, curvature and dimensions.

A method for producing a torsion box for a structure of an airplane. The method includes providing a first component made of a fiber composite material, the first component has a first planar base having a first inner side and a first outer side, first stiffening elements on the first inner side forming a composite with the first base. A second component is provided of a fiber composite material and has a second planar base having a second inner side and a second outer side. Second stiffening elements are on the second inner side and form a composite with the second base. The method includes superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side. The methods includes connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

A composite laminated layup panel structure suitable for wing combined connection, comprising a main box section skin (100) and a plurality of stiffeners (200) which are integrally cured and formed. The main box section skin is sequentially provided with recesses (300) at a front edge and a rear edge, forming a front recessed edge (110) for overlapping with a leading edge skin (400) and a rear recessed edge (120) for overlapping with a trailing edge skin. A front spar stiffener (600) configured to be connected to a front spar web (500) is fixedly arranged at the bottom of a transition region between the front recessed edge (110) and a main box section skin main body. A rear spar stiffener (700) configured to be connected to a rear spar web is fixedly provided at the bottom of a transition region between the rear recessed edge (120) and the main box section skin main body. The panel structure simplifies connection forms of panels and related structures, reducing the number of parts, improving assembly efficiency, and also facilitating disassembly and replacement maintenance during aircraft use and maintenance.