68 results about "Swept wing" patented technology

A variable-sweep wing for a tiltrotor aircraft includes a fuselage link coupled to the fuselage and a pylon link coupled to a pylon. A wing airframe has a root end pivotably coupled to the fuselage link and a tip end pivotably coupled to the pylon link. A driveshaft is coupled between the fuselage link and the pylon link and is positioned within the wing airframe. The driveshaft is operable to transmit torque from the main gearbox to a proprotor gearbox. A crank is coupled between the fuselage link and the pylon link and is positioned within the wing airframe. The fuselage link, the pylon link, the driveshaft and the crank form a linkage such that pivoting the crank relative to the fuselage link causes the wing airframe to shift between a substantially straight wing configuration for low-speed forward flight and a swept wing configuration for high-speed forward flight.

The invention discloses a distributed electric propulsion box type wing ground effect aircraft which comprises a main fuselage, the two sides of the main fuselage are connected with one ends of sweepback wing main wings, one ends of two empennages above the tail of the main fuselage are connected with the main fuselage through vertical tails, and the other ends of the two empennages are connected with the other ends of the two main wings through end plates respectively. The empennage is connected with a plurality of high ducted fans directly driven by a motor, an elevator and an aileron are arranged at the rear part of the empennage, a rudder is arranged at the rear part of the vertical fin, and the elevator, the aileron and the rudder are controlled by a flight control system and are mutually independent. The ground-effect aircraft provided by the invention adopts a box-type wing structure formed by combining the sweepback main wing and the sweepforward empennage, has better aerodynamic performance in a take-off and climbing low-speed flight state, and can provide larger lift force and better maneuvering characteristics.

The invention discloses a variable-elongation sweepback wing scaling wing deformation device and a deformation method thereof, and relates to the technical field of deformation mechanism design of variant aircrafts, the aerodynamic configuration of a variable-elongation sweepback wing scaling wing is composed of a fuselage section, a sweepback fixed section and a telescopic section, the fuselage section is composed of a fuselage shell and an upper hatch cover, and the upper hatch cover is composed of an upper hatch cover and a lower hatch cover. The sweepback fixed section is composed of an upper wing surface shell and a lower wing surface shell, the telescopic section is an independent telescopic wing shell, the fuselage section and the shell of the sweepback wing fixed section are fixed through a sunk screw, and therefore it is guaranteed that the aerodynamic shape meets the aerodynamic design requirement; the linear guide rail is fixedly connected to the lower wing surface shell, and the telescopic wing can move along the linear guide rail; electric push rods are used for driving and are fixed in the fuselage, and inner rods of the electric push rods are connected with the telescopic wings, so that the telescopic wings are controlled to move along the linear guide rails; according to the method, the aerodynamic configuration of the scaled wing is segmented, so that the aerodynamic configuration and internal movement components of the scaled wing are mounted, and the extension length of the wing is changed by driving the telescopic wing to move along the linear guide rail through the electric push rod, so that the lift-drag ratio of the aircraft in the flying process is changed; the method can provide an implementation method for the equivalent scaling experiment of the deformable wing.

The invention discloses an active and passive control method for inhibiting shock wave buffeting of a sweepback wing, and belongs to the field of aircraft flow active and passive cooperative control. The method comprises the following steps: establishing a numerical simulation geometric model of the sweepback wing and an active and passive cooperative control law design model of the sweepback wing; and performing flow field state analysis by combining with a sweepback wing transonic speed buffeting flow field solver, training the sweepback wing active and passive cooperative control law design model to obtain an optimal sweepback wing active and passive cooperative control law design model, and performing active and passive control on the sweepback wing to complete suppression of shock wave buffeting of the sweepback wing. An active and passive cooperative control thought is adopted, the lift pulsation amplitude is effectively reduced through mutual cooperation of an active control device and a passive control device, meanwhile, deep reinforcement learning control is adopted, and the sweepback wing shock wave buffeting phenomenon can be eliminated in the flowing state within a certain range.

The invention discloses a variable sweepback wing based on flexible corrugated skin and a design method, and relates to the field of aircraft structure design, the variable sweepback wing comprises a wing mounting seat matched with a fuselage, and further comprises a rigid edge strip matched with the outer edge of the variable sweepback wing; the rigid edgings are arranged up and down in space, and the wing mounting seats and the rigid edgings are connected into an integrated structure so as to construct a flexible corrugated skin I and a flexible corrugated skin II of the sweepback wing; the supporting assemblies are arranged between the flexible corrugated skin I and the flexible corrugated skin II; the driving mechanism is arranged on the wing mounting seat and is used for pulling the flexible corrugated skin to deform; and the linear displacement sensor is used for measuring the variable quantity of the sweepback angle of the wing. According to the variable-sweepback wing based on the flexible corrugated skin and the design method, the aerodynamic configuration of an aircraft can be adjusted along with the flight path, the cross-speed domain aerodynamic configuration contradiction is effectively solved, the higher available lift-drag ratio is provided for the aircraft, and the comprehensive aerodynamic performance of the aircraft is further improved.

The invention provides a wave rider capable of vertically ascending and descending, and belongs to the technical field of wide-speed-range aircrafts, the wave rider specifically comprises a front edge shock wave generating surface, a central fuselage and sweepback wings located on the two sides of the central fuselage, the two sweepback wings are provided with mounting holes penetrating through the upper surface and the lower surface of the wave rider, and lift fans are mounted in the mounting holes; the lift fans are embedded into the mounting holes and used for providing vertical lift force for the wave rider, the axes of the lift fans are parallel to the vertical axis of the wave rider, and the lift fans on the two sweepback wings are symmetrically distributed on the two sides of the central fuselage. According to the treatment scheme, the vertical lifting capacity is provided for the wave rider, and the high-speed flight aerodynamic performance is considered.

The invention discloses a wide-speed-range variant high-speed aircraft aerodynamic layout, and belongs to the technical field of aircrafts, the wide-speed-range variant high-speed aircraft aerodynamic layout comprises a fuselage, the front end of the fuselage is provided with a drag reduction rod, the rear end is provided with a thrust vectoring nozzle, the left and right sides are symmetrically provided with triangular sweepback wings, and the top is provided with a supporting structure; a high-pressure capturing wing is arranged on the top of the supporting structure. The shock wave separation effect of the drag reduction rod is combined with the high-pressure capture and reflection shock wave induction mechanism of the high-pressure capture wings, so that the aircraft can achieve effective drag reduction and lift augmentation effects in different flight states, and the lift-drag ratio and adaptability of the high-speed blunt cone aircraft are remarkably improved.

The invention discloses a variable sweepback wing aircraft attitude control technology based on reinforcement learning and a self-adaptive switching sliding mode strategy in a complex environment. The method mainly comprises the following steps: firstly, modeling a variable sweepback wing aircraft with a global working mode into a nonlinear switching system form; secondly, designing a reinforcement learning controller, solving a control law for maximizing a strategy objective function gradient by using Actor, and approaching an action value function by using Critic; finally, a nonlinear switching disturbance observer is used for estimating composite disturbance composed of discontinuous disturbance and parameter uncertainty, a dead zone right inverse function is introduced to enable composite nonlinearity composed of a dead zone and saturation nonlinearity to be equivalent to a new saturation link, and an anti-saturation auxiliary system is constructed for processing. And a self-adaptive switching sliding mode controller is provided on the basis of backstepping. The method provided by the invention has effectiveness and superiority.

The invention discloses a momentum body appearance of an upper atmospheric aircraft. The momentum body appearance comprises an aircraft head, a body, a sweepback airfoil and a wingtip V-shaped tail. The head of the aircraft is a wedge-shaped polyhedron and is in butt joint with a rear body. The body is a multi-stage trapezoidal boss which shrinks backwards, so that the resistance of the body is reduced; the sweepback airfoil is connected with the body to realize static pitching stability; and the two V tails are positioned at the positions of wingtips. According to the invention, the momentum exchange principle that the upper atmospheric layer gas interacts with the object plane is adopted, a polyhedral aerodynamic shape meeting the low-resistance aerodynamic characteristic is designed, the fusion design of the aerodynamic performance and the solar wing is realized, the aerodynamic resistance compensation requirement of the aircraft in the airspace can be effectively reduced, and the hang time of the aircraft is prolonged.

The invention discloses a method for quickly acquiring unsteady aerodynamic characteristics of a flexible variable sweepback wing, which comprises the following steps of: determining design variables, sampling each design variable based on a Latin hypercube design method, and calculating simulation response values corresponding to sample points; forming a sample data set by the sample points and the corresponding response values, establishing a Kriging agent model on the basis, and training the model; performing fitting precision test on the trained Kriging model by adopting a goodness-of-fit method, if the Kriging model is unqualified, adding new sample points, obtaining corresponding simulation response values, adding the simulation response values into a sample database, re-training the Kriging model, and obtaining the unsteady aerodynamic characteristics of the flexible variable sweepback wing under different flight conditions based on the qualified Kriging model. According to the method, the Kriging model is constructed and trained based on different flight working conditions and the corresponding unsteady aerodynamic characteristic sample data sets, the unsteady aerodynamic characteristics of the flexible variable sweepback wing under the unknown flight working condition can be rapidly obtained, high calculation cost of CFD simulation calculation is avoided, and the method has practical engineering value.

The invention provides a smooth variable-sweepback wing based on an elastic rotation assembly and a variable-wing aircraft, belongs to the field of aerospace equipment, and solves the problems of low actuation driving efficiency, motion clamping stagnation and the like of the existing variable-sweepback wing at present. Wherein the supporting seat is fixedly arranged on the inner wing; the outer wing penetrates through the inner wing; the driving structure is arranged on the inner wing; the elastic variable sweepback structure comprises a plurality of first elastic rotation structures, the first ends of the first elastic rotation structures are fixedly arranged on the supporting base, the second ends of the first elastic rotation structures are connected with the outer wings, and the second ends of the first elastic rotation structures are further connected with the driving structure through first connecting ropes. The driving structure can pull the second end of the first elastic rotary structure to move through the first connecting rope so as to drive the outer wing to rotate relative to the inner wing; one side of the shape-maintaining structure is fixedly connected with the inner wing, and the other side of the shape-maintaining structure is elastically lapped on the outer surface of the outer wing. The smooth continuous deformation capacity of the variable sweepback wing can be achieved, clamping stagnation is avoided in the movement process, and the actuation driving efficiency is high.

The invention provides a supersonic velocity gas film distributed cooling method for a near space waverider aircraft, and the method comprises the steps: arranging a first cooling device on the upper surface of a waverider close to the head of the waverider, and enabling the first cooling device to be used for generating a tangential supersonic velocity gas film; a second cooling device is arranged at the front edge of a sweepback wing of the waverider, and the second cooling device is used for generating a normal supersonic velocity gas film; the flowing direction of the tangential supersonic air film is consistent with the incoming air flow, and the flowing direction of the normal supersonic air film is perpendicular to the incoming air flow. The surface of the wave rider is covered with cooling gas through the supersonic cooling gas film, the coverage area is large, the cooling effect is stable, and the wave rider is suitable for optical windows and has no requirement for aircraft structural materials. And meanwhile, similar cooling devices can be arranged at different positions of the wave rider for combined cooling, and distributed large-area cooling is achieved.

The utility model discloses a variable sweepback wing flight device which comprises a fuselage, wings and a vertical fin, a fixing plate is installed on the fuselage to install a steering engine, the steering engine is used for driving two clamping and locking gears fixedly installed on the wings, and sweepback movement of the wings is controlled in real time; meanwhile, clamping and locking control over the two clamping and locking gears is achieved through a shape memory spring which is fixedly installed on the machine body and can be electrically controlled, and clamping and locking pieces are arranged at the two ends of the shape memory spring; through the structural design of a motor, a conveyor belt, a battery and a belt pulley arranged in the fuselage, the gravity center of the whole flight device is adjusted in real time, and automatic balance control over the variable sweepback wings is achieved. According to the variable sweepback wing flight device, the sweepback movement of the sweepback wings can be accurately and steplessly controlled in real time in the flight process, the task execution capacity of different flight speeds can be considered, the weight can be reduced, and the size of a fuselage can be reduced.

An aircraft 310 has a pair of swept wings 314A meeting at a central region 312. Each wing has an inner wing section 326A containing an integrated payload fuselage (fig.1,20); a thinner thickness oute

A small form factor aircraft comprising: a body comprising an internal volume; at least one motor disposed within the internal volume; at least one lead screw driven by the at least one motor; at least one collar disposed at least partially within the internal volume of the body; at least one pair of wings, each wing being rotatably attached to the collar adjacent a forward or rear edge; at least one coupler, each coupler being rotatably coupled to a pair of adjacent wings, the coupler comprising a threaded, central section configured to engage with the at least one lead screw such that rotation of the at least one lead screw results in axial translation of the at least one coupler within and relative to the body; and a controller configured to control the at least one motor.

The utility model provides a multi-form small underwater exploration robot based on octopus ghost bionics, which is a small underwater exploration robot with a novel movement mode designed by observing the underwater movement mode of the octopus ghost, and specifically comprises a robot front body, a tail propeller, two sweepback wings and a steering mechanism, the sweepback wings are arranged on the two sides of the robot front body through the steering mechanisms correspondingly, and the steering mechanisms are electrically connected with the terminal. The sweepback wings are additionally arranged on the two sides of the front body of the robot and matched with the jet pump, rapid turning of the robot is achieved through the flapping speed difference of the sweepback wings on the left side and the right side and the flow difference of the jet pump, and the turning amplitude reaches 360 degrees. According to the underwater exploration robot, the high-degree-of-freedom holder is arranged between the connecting parts of the sweepback wings and the shell, the underwater exploration robot is helped to move forwards and turn, the movement is very stable, and the concealment and comprehensiveness of the robot in the exploration process are perfectly achieved.

The invention discloses a vertical take-off and landing freight flight device based on a composite lift system. The vertical take-off and landing freight flight device comprises a cargo hold, a connecting rod and a multi-rotor aircraft, the cargo hold comprises a hold body, an upper single sweepback wing and an empennage; wherein the sweepback wing and the empennage play a supporting role when on the ground, one end of the connecting rod is coaxially and fixedly connected with the top end of the cargo hold, and the other end of the connecting rod is connected with the center of the bottom end of the multi-rotor aircraft through the universal hinge. During forward flight, the rotor wings can distribute more power into forward thrust, so that the aim of increasing the voyage or increasing the speed is fulfilled.

An aircraft (10) comprising: a starboard swept wing (14) and a port swept wing, each swept wing having an inner wing section (32) comprising an integrated payload fuselage (20) and an outer wing section (30) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section; and in which a sweep angle of the inner wing section is greater than a sweep angle of the outer wing section a front spar 36 close to a leading edge (18) of each wing, in at least the outer wing section, and a rear spar (38) close to a trailing edge (22) of each wing, for carrying loads along each wing; a central region (12) where the starboard swept wing meets the port swept wing; a starboard transition region where the starboard inner wing section meets the starboard outer wing section; a port transition region where the port inner wing section meets the port outer wing section; and a load-bearing structural element (40) disposed across each wing from the front spar to the rear spar in the transition region for carrying loads between the front spar and the rear spar of each wing.

The present invention discloses an active and passive control method for suppressing the shock wave flutter of a swept wing, which belongs to the field of active and passive coordinated control of aircraft flow, and includes: establishing a numerical simulation geometric model of a swept wing, and a design model of an active and passive coordinated control law of a swept wing, and combining a swept wing transonic flutter flow field solver to analyze the flow field state, training the design model of the active and passive coordinated control law of the swept wing, obtaining the optimal design model of the active and passive coordinated control law of the swept wing, and performing active and passive control on the swept wing to suppress the shock wave flutter of the swept wing. The present invention adopts the idea of ​​active and passive coordinated control, and effectively reduces the amplitude of lift pulsation through the mutual cooperation of an active control device and a passive control device. At the same time, the present invention adopts deep reinforcement learning control, which can eliminate the shock wave flutter phenomenon of the swept wing within a certain range of flow states.

This application provides a rapid wing deployment and locking mechanism for swept-wing aircraft. The mechanism includes: a base, a slider, a guide mechanism, a linkage mechanism, a rotating mechanism, and a locking mechanism. The guide mechanism, linkage mechanism, rotating mechanism, and locking mechanism are all mounted on the base. The slider is slidably connected to the guide mechanism and connected to the linkage mechanism. The end of the linkage mechanism away from the slider is connected to the rotating mechanism. The wing is fixedly connected to the rotating mechanism. The locking mechanism is located on the side of the rotating mechanism and is used to lock the rotating mechanism. When the slider is impacted by a pyrotechnic device, the slider moves along the guide mechanism, causing the linkage mechanism to swing. The linkage mechanism drives the rotating mechanism to rotate, which in turn causes the wing to deploy. After the wing is fully deployed, the locking mechanism locks into place with the rotating mechanism. This application eliminates the need for wing reassembly, reduces the need for large packaging space, and allows for rapid wing deployment from under the fuselage. Locking the deployed wing ensures stable flight.

The application discloses a rear-swept wing distributed non-equal-diameter rotorcraft and a control method thereof, which comprises a fuselage, a wing, a tilt-rotor group, a landing gear, a horizontal tail and a vertical tail; the tilt-rotor group comprises four tilt-rotors which are connected to the leading edge of the wing through a support rod; the rotor disc area near the wing tip is larger than the rotor disc area near the wing root, so as to balance the flight efficiency at low speed and the flight speed at high speed, and the rear sweep of the wing is beneficial to improving the stability of the tilt-rotor aircraft in the fixed-wing mode flight, and the environmental adaptability of the aircraft is improved. The application balances the efficiency of the tilt-rotor aircraft in the hovering and cruising states, the aircraft structure is relatively simple, is beneficial to the attitude control of the aircraft and the flight control software design.

The application relates to a variable sweep wing stealth aircraft afterbody wedge shape design method, and belongs to the field of aircraft general design and stealth technology. The application is simple and practical in shape; comprehensive design factors are considered, and comprehensive requirements such as variable tail wing rotation, component coupling, stealth principle and aerodynamic resistance are covered; design constraints can be accurately converted into geometric design; variable tail wing rotation, the stealth principle, aerodynamic resistance and component coupling can be effectively converted into afterbody wedge shape point position and line tangent vector control design to be realized; the fusion design of the afterbody wedge and the surrounding curved surface is better realized; under the premise of guaranteeing the variable tail wing rotation space requirement and the binary nozzle requirement, the aerodynamic and stealth shape integration design of the afterbody wedge shape is realized. The application is mainly applied to the scheme design of the afterbody wedge shape of the variable tail wing. The method is novel, ingenious and compact in structure, has strong applicability, has a wide application range, and has a wide application prospect in the design of military aircraft.

The application discloses a lightweight variable-trailing-sweep wing based on a hot knife-torsion spring and a method thereof. The variable-trailing-sweep wing comprises a wing, a torsion spring unfolding mechanism, an unfolding locking mechanism, a telescopic rod, a fuse rope, a hot knife mechanism and a connecting frame. Before unfolding, the unfolding locking mechanism is positioned and locked by the telescopic rod, the fuse rope and the connecting frame; the torsion spring in the torsion spring unfolding mechanism is twisted to store potential energy. During unfolding, the torsion spring is released, the wing is unfolded under the action of the torsion spring unfolding mechanism and is locked with the unfolding locking mechanism, and meanwhile, the tension spring in the torsion spring unfolding system stores energy. Meanwhile, the torsion spring is caused to fall off after the wing is unfolded, so that the torsion spring does not work during the trailing sweep. When trailing sweep is needed, the hot knife mechanism is powered to heat and then the fuse rope pressed on the heating pipe is broken, the unfolding locking mechanism and the wing are trailing swept under the action of the tension spring and aerodynamic force, and the telescopic rod is lengthened to the designed position to be locked, so that the wing is locked in the trailing sweep state. The application can be widely applied to variable-body aircrafts.

The design method of a super / hypersonic natural laminar wing considering strong cross-flow effect belongs to the field of aerodynamic shape design of aircraft. In order to improve the aerodynamic efficiency of super / hypersonic aircraft, the present invention designs the optimal target pressure distribution curve of the high Reynolds number and large swept wing of the super / hypersonic aircraft according to the initial super / hypersonic aircraft high Reynolds number and large swept wing section pressure distribution, and parametrically describes the airfoil in the wing. The airfoil of each section of the wing controls the wing geometry and performs parametric design of the airfoil based on the Hicks-Henne parameterization method; the amplitude and direction changes of the cross-flow velocity type are comprehensively adjusted by optimizing design means, the natural laminar range under high Mach number and high Reynolds number conditions are expanded, and the adaptability range and effect of the natural laminar design are improved. The present invention is applied to the design process of super / hypersonic natural laminar wings, which can improve the laminar range of the wing surface of the super / hypersonic aircraft and improve the aerodynamic efficiency of the super / hypersonic aircraft.

The invention discloses a variable sweepback wing aircraft with a movable winglet, and relates to the technical field of aircrafts. Comprising an aircraft body, a mounting groove and a winglet body, a Hall effect sensor is fixedly mounted on the front end wall of the interior of the mounting groove, and a swing device is arranged in the mounting groove; the swing device comprises a hydraulic telescopic rod, a sliding rod, a first sliding block, two connecting blocks, a limiting block, a second sliding block, a second sliding strip, a first sliding rail, a center shaft, a spherical support, a spherical stand column, a swing seat, a swing frame, a mounting seat and a second sliding rail, the number of the connecting blocks is two, and a magnet is fixedly mounted on the winglet main body. And the right side of the winglet main body is fixedly connected with a second sliding strip.

The variable sweep angle missile wing unfolding mechanism comprises a cam slider, a gas actuating cylinder mounting seat, a linear motor, an actuating cylinder sliding rail, a cam sliding rail, a rack, a right gear missile wing, a left gear missile wing and a roller. The invention realizes the unfolding of the missile wing through the actuating cylinder-rack-gear, and realizes the adjustable unfolding angle of the missile wing through the motor-cam mechanism, which can simultaneously satisfy the functions of synchronous unfolding of the missile wing, storage and transportation in small space, and adjustment of the sweep angle according to requirements. The invention has simple and reliable structure and is convenient to maintain.

The invention belongs to the technical field of aircrafts, and aims to solve the problems of resistance divergence effect and difficult engine air intake of a traditional aircraft. The air-breathing high-subsonic-velocity aircraft comprises a nose, a fuselage, a tail, wings and an empennage, the nose is connected with the tail through the fuselage, the wings and the empennage are connected with the fuselage, the wings are supercritical airfoil type sweepback wings, an embedded air inlet channel is formed in the lower surface of the tail and communicated with an engine in the tail, and the engine is connected with the tail through the embedded air inlet channel. The embedded air inlet channel can introduce air on the lower surface of the tail into the engine so as to meet the air inlet requirement of the engine. According to the aircraft, the wings are arranged to be the supercritical wing type sweepback wings, through the unique geometric shape and sweepback arrangement, the resistance divergence phenomenon is effectively delayed, the effective speed of airflow perpendicular to the front edge is reduced, accordingly, shock wave generation is delayed, an embedded type air inlet channel is formed in the lower surface of the tail, and the impact resistance of the aircraft is improved. The air inlet requirement of an engine of an aircraft is met, and meanwhile the flight resistance and the radar cross section are reduced.

An aircraft (10) comprising: a starboard swept wing (14A) and a port swept wing (14B), each swept wing having an inner wing section (26A) comprising an integrated payload fuselage (20) and an outer wing section (30A) for extending the wingspan and providing lift; the inner wing section comprising: a rear spar (40) disposed close to a trailing edge (22A) of each inner wing section to carry loads along each inner wing section; a wing surface (30), in which the wing surface is substantially shaped as an aerofoil, and in which the wing surface comprises a rear fairing (62) disposed behind the rear spar, and near to the trailing edge, and in which the wing surface comprises an upper curved portion (50) which has a substantially arcuate cross section, a front curved portion (52) which has a substantially arcuate cross section, and a lower wing surface, the upper curved portion meeting the rear spar at a rear of the upper curved portion, and the upper curved portion meeting the front curved portion at a front of the upper curved portion, and the front curved portion meeting the lower wing surface at a front of the lowerwing surface, a cabin structure (32) in each inner wing, in which the cabin structure comprises one or more floor beams (36) and a rear wall defined by the rear spar; in which the lowerwing surface comprises a front lower curved portion (117), in which the front lower curved portion is substantially arcuate in profile and extends from a front edge of the floor beam(s) of the cabin structure towards the rear wall; in which the lower wing surface of each inner wing extends below a first line A, the first line being a line on the rear wall of the cabin structure where a projection of the arcuate front lower curved portion of the wing surface meets the rear wall, and in which a rear lower portion of the lower wing surface meeting the front lower portion and continuing the lowerwing surface to a second line, which is spaced from and below the first line.

The utility model discloses a fixed-wing unmanned aerial vehicle based on flexible perovskite solar cells, which adopts a wing body fusion design and comprises an equipment compartment in the middle of a vehicle body and wings on two sides, and a pair of ailerons with rolling and pitching control functions is arranged on the rear edge of the outer section of each wing; a pair of vertical stabilizers are arranged at the tips of the wings so as to enhance the course stability during flight; two flexible perovskite solar cells which accord with the shapes of the wings and are tightly attached to the wings are mounted on the surfaces of the fuselage and the wings, and power is provided for the unmanned aerial vehicle. According to the utility model, the sweepback wing flying wing type layout is adopted, so that the effective lift area of the wings and the laying area of the solar cells are increased while the structural weight is reduced; the battery is laid on the surface of the wing, damage to the battery in the laying process can be reduced, and the installation difficulty is lowered; meanwhile, the flexible perovskite solar cell has the advantages of low cost, good folding and bending performance and the like, so that the flight efficiency of the unmanned aerial vehicle is improved, the effective load is increased, and the endurance is prolonged.

An aircraft (10) comprising: a port swept wing (14B) and a starboard swept wing (14A), each swept wing having an inner wing section (26A) comprising an integrated payload fuselage (20) and an outer wing section (30A) for extending the wingspan, in which each outer wing section has a thickness less than a thickness of the corresponding inner wing section; and in which the sweep angle of each outer wing section is lower than the sweep angle of the corresponding inner wing section; a central region (12) where the port swept wing meets the second swept wing; a port transition region (23A) where the port inner wing section meets the port outer wing section; a starboard transition region (23B) where the starboard inner wing section meets the starboard outer wing section; at least one rear spar on each wing, in which each rear spar is disposed close to a trailing edge (22A) of the wing to carry loads along the respective wing; one or more elevons (34A) or ailerons on each outer wing section; and one or more roll spoilers (32A) on each inner wing section.