653results 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.

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.

The invention discloses a method for manufacturing a wing rib by using a three-dimensional woven composite material and the wing rib, and relates to the technical field of wings, the method comprises the following steps: S1, determining the form of an integrally woven three-dimensional woven preform according to the geometrical shape of the wing rib to be manufactured; s2, determining a tissue form and basic weaving parameters of a three-dimensional woven fabric of the preform according to the geometric dimension of the wing rib; s3, weaving a prefabricated body; s4, preparing a forming mold; and molding in a molding cavity through a vacuum-assisted resin transfer molding process to obtain the wing rib. According to the wing rib woven through the method, due to the strengthening effect generated by interweaving of the yarn in the three-dimensional woven fabric, the layering resistance of the wing rib is improved when the wing rib bears complex loads, and the bearing capacity of a web flange connecting area is also improved.

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.

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.

There is provided an extendable compression chain system for extending a structure. The system includes a track assembly, a curved guide assembly, an extendable compression chain assembly, an actuation mechanism, and a mechanical power apparatus. The extendable compression chain assembly is configured to travel along the track assembly and to follow the curved portion of the track assembly, to move from a retracted position to an extended position, to extend the structure coupled to the extendable compression chain assembly. The extendable compression chain assembly includes a compression chain structure having a first end, a second end, and modules. The modules are movable between a rigid position and a collapsed position, as the compression chain structure follows the curved portion of the track assembly, and wraps around the curved guide assembly. The extendable compression chain assembly includes an actuation end fitting and a structure interface end fitting.

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 connector for truss work members to a support structure for a mounting interface of a trusswork. The connector has a body with a first portion and a second portion. A central opening is provided in the body having an inner wall configured for receiving a connection end of a truss member. The first portion and the second portion are arranged concentrically. The first portion has first circumferential edge sections, and the second portion has second circumferential edge sections. The first and second circumferential edge sections are spaced apart by gap sections that are configured to receive connecting flanges of a support structure. The gap sections are forming segments along a virtual surface that is curved at least in one direction.

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.

An aircraft wing includes a center wing section having a continuous structure that spans beyond a first side of an aircraft fuselage and beyond a second side of the aircraft fuselage. The aircraft wing also includes a first outboard wing section attached to a first end of the center wing section by a first truss system that is accessible via a first closeout panel. The first end of the center wing section in on the first side of the aircraft fuselage. The aircraft wing also includes a second outboard wing section attached to a second end of the center wing section by a second truss system that is accessible via a second closeout panel. The second end of the center wing section is on the second side of the aircraft fuselage.

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 utility model discloses a composite material aircraft spar and metal joint assembly in the technical field, which comprises a spar and a joint and is characterized in that the spar is made of composite materials, the joint is made of metal materials, the spar and the joint are both of C-shaped structures, the joint is connected to the inner side of one end of the spar, and the other end of the spar is connected with the metal joint. A step face is machined on the inner side, corresponding to the installation connector, of the end of the spar, and a step face is correspondingly machined on the outer side of the connector.

According to the electric tilting helicopter wing, a flap steering engine end adjusting support is connected with a middle hinge structure of a flap conversion rocker arm, one end of a flap control surface connecting rocker arm is connected with the right end of the flap conversion rocker arm, and the other end of the flap control surface connecting rocker arm is connected with a flap control surface fixing connector; the aileron steering engine root mounting frame is located on the wing rib, and a single lug of the aileron steering engine root mounting frame is connected with double lugs of the aileron steering engine root; a middle fixing frame of the aileron steering engine is positioned on the rear beam, and two sides of the aileron steering engine are respectively arranged on the wing ribs; an aileron steering engine end adjusting support is connected with the rear beam, and an aileron steering engine end double-lug connector is connected with the left end of an aileron conversion rocker arm; an aileron steering engine end adjusting support is connected with a middle hinge structure of an aileron conversion rocker arm, one end of an aileron control plane connecting rocker arm is connected with the right end of the aileron conversion rocker arm, and the other end of the aileron control plane connecting rocker arm is connected with an aileron control plane fixing connector. A force transmission path of bending, twisting and shearing loads caused by concentrated mass of aerodynamic loads, a transmission system and a rotor system is provided, and the strength and rigidity of the flap and aileron steering engine connecting structure are guaranteed.

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.

The aircraft comprises an aircraft body, and wings are arranged on the left side and the right side of the aircraft body respectively. Each wing comprises a wing frame, wing cloth and a winding roller; each wing frame comprises a heel section, a middle section and a tail section which are sequentially distributed from near to far from the fuselage in the left-right direction; one end of the heel section is rotationally connected with the fuselage; one end of the middle section is rotationally connected with the other end of the heel section, and the other end of the middle section is rotationally connected with one end of the tail section; driving mechanisms for driving the heel section and the fuselage, the heel section and the middle section as well as the middle section and the tail section to rotate relatively are respectively arranged between the heel section and the fuselage, between the heel section and the middle section and between the middle section and the tail section, so that the wing frame can be switched between an unfolded state and a folded state; wing cloth penetrating gaps are arranged on the heel section and the middle section respectively; the winding roller is rotationally mounted on the machine body; one side edge of the wing cloth is connected with the winding roller, and the other side edge of the wing cloth penetrates through the wing cloth penetrating gap and then is connected with the tail section. The wing frame has the advantage that when the wing frame is folded, the wing cloth can be rolled, so that the wing cloth cannot be wrinkled.

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.

An aircraft panel assembly with a panel and a plurality of stiffeners on the panel is disclosed. Each stiffener has an attachment part attached to the panel and a structural part spaced apart from the panel. A rib foot beam crosses the stiffeners at a series of intersections. At each intersection the rib foot beam is located between the panel and the structural part of a respective one of the stiffeners.

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.