40 results about "Swept wing" patented technology

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 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 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 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.

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.

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 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.

The application provides a method for assigning aerodynamic heat boundary conditions of variable sweep wing structure heat transfer simulation, which comprises defining a wing surface position with a first sweep angle in a whole trajectory as a reference position, rotating heat environment data to the reference position, and dividing a structure heat transfer grid at the reference position; then, creating a "point method" equation for the outer edge of a wing box, establishing a structure heat transfer grid surface grid point space position criterion based on the equation, and dividing the grid points into a set of aerodynamic heating points and a set of non-aerodynamic heating points; taking the set of aerodynamic heating points as an aerodynamic heat data interpolation target area, performing heat environment interpolation, and assigning 0Kw / m 2 to the cold wall heat flux of the set of non-aerodynamic heating points, restoring the constant value of enthalpy, and forming an adiabatic boundary condition. The method solves the problems that aerodynamic heat environment data cannot be directly interpolated to the structure heat transfer calculation grid surface due to the change of the spatial position of the variable sweep wing structure, and the structure heat transfer grid spatial position changes, resulting in that heat transfer analysis cannot be continuously performed along the whole trajectory.

An aircraft 10 has a pair of swept wings 14A,14B meeting at a central region 12. Each wing has an inner wing section 32A,32B containing an integrated payload fuselage; an upper surface and a lower su

The present invention proposes a distributed supersonic air film cooling method for near-space waverider aircraft. A first cooling device is positioned on the upper surface of the waverider near the head of the waverider. This device generates a tangential supersonic air film. A second cooling device is positioned on the leading edge of the waverider's swept wings. This device generates a normal supersonic air film. The tangential supersonic air film flows in the same direction as the incoming air flow, while the normal supersonic air film flows perpendicular to the incoming air flow. This supersonic cooling air film coats the waverider surface with cooling gas, resulting in a large coverage area, stable cooling effect, and applicability to optical windows, without requiring high-quality aircraft structural materials. Similar cooling devices can also be positioned at different locations on the waverider for combined cooling, achieving distributed, large-area heat reduction.

The invention discloses a longitudinal aerodynamic force rapid analysis and attitude stability control method and device for a sweepback-wing-variable cross-medium aircraft and electronic equipment. The method comprises the steps that pneumatic analysis of independent analysis is adopted for wings, a fuselage and an elevator of the aircraft; open source aerodynamic analysis software XFLR5 software is used for carrying out aerodynamic analysis on the wing, and comparison verification is carried out on results of aerodynamic analysis on the wing in multi-physical field simulation and computational fluid dynamics software STAR-CCM + software; establishing a mathematical model of the aircraft, and performing mathematical abstraction on a control problem of the aircraft; an extended state observer ESO is designed to observe disturbance and nonlinearity of the model, and a backstepping method controller is designed to control the attitude of the variable swept wing cross-medium aircraft, so that the aircraft is fast and stable. According to the method, the aerodynamic parameter obtaining efficiency can be remarkably improved, the theoretical verification process is accelerated, and stable control over the water outlet stage of the cross-medium variable sweepback wing aircraft can be effectively achieved.

This invention discloses a variable-sweep wing and an aircraft. The variable-sweep wing includes an external linkage system based on a multi-link mechanism, an internal linkage system based on a crank-slider mechanism, and a power assembly. The external linkage system is hinged to the fuselage of the aircraft to form the wing body. The internal linkage system is also hinged to the fuselage to maintain the attitude of the wing body formed by the external linkage system. The internal linkage system is connected to the external linkage system via at least one intermediate link, forming a single-degree-of-freedom planar multi-link structure with multiple hinges. The power assembly can drive changes in the attitude of each link in the external and internal linkage systems, thereby altering the sweep angle of the wing body. This invention has the advantages of a simple driving method and more uniform overall force distribution.

Wing assembly with slats and aircraft. A wing assembly comprising: a swept wing body, a leading edge of the wing body extending outwardly and rearwardly from a wing root to a wing tip; a first slat selectively movably connected to the wing body; and a second slat selectively movably connected to the wing body, the second slat disposed outwardly of the first slat, a flexible seal member disposed and connected between the first slat and the second slat; at least a portion of the first slat, at least a portion of the second slat, and at least a portion of the flexible seal member defining therebetween a slat gap, at least a majority of the slat gap being substantially parallel to a predetermined local airflow direction. Also disclosed is an aircraft comprising a fuselage; and two oppositely disposed wing assemblies connected to the fuselage.

The utility model relates to the technical field of gliding extended range type missile weapon systems, in particular to a gliding diamond back folding wing assembly capable of self-adaptively changing sweepback wings, which comprises a diamond back base and a set of sliding assembly, wings are arranged on both sides of the diamond back base, the lower sides of the two wings are connected with the tail of the diamond back base through two connecting rods, and the two connecting rods are connected with the diamond back base. A one-way supporting and locking mechanism is installed near each TBR guide rail, the side, close to a guided missile, of the diamond back base is in a circular arc shape, hanging lugs with round holes are arranged at the four corners of the diamond back base respectively, and a circular arc pressing plate is installed on each hanging lug. The problem that wings of gliding missiles cannot be put down in a folded state due to the fact that the wings are too long and the back space of the missiles is too short can be solved, in addition, the method can adapt to missiles with different missile diameters, and the adaptability of diamonds back to the missiles is improved.

The invention belongs to the technical field of mobile communication, particularly relates to an orthogonal frequency division multiplexing (OFDM)-based communication and inductance integrated unmanned aerial vehicle (UAV) detection method, and provides a micro-Doppler signal model based on an OFDM signal by combining OFDM signal characteristics on the basis of motion characteristics of UAV rotors and flapping wings, sweeping wings and the like of birds. After short-time Fourier transform coarse extraction is carried out on a target echo signal, the scheme provides a high-precision extraction and transformation method based on a maximum value point, micro-motion features can be effectively extracted, accurate identification and parameter estimation of an unmanned aerial vehicle are realized, and an innovative solution is provided for an unmanned aerial vehicle detection method based on ISAC.

The application provides a low-subsonic to high-subsonic wide-speed-range deformable aerodynamic layout of a cruise missile, comprising double-axis variable sweep wing mechanisms arranged at the bottom of a fuselage, capable of arbitrarily changing and locking a sweep angle in a range of 0-90 degrees, each double-axis variable sweep wing mechanism comprising an inner wing segment and an outer wing segment, the inner wing segment being pivotally connected with the fuselage at a wing root, and the inner wing segment being adjusted at a front sweep angle in a range of 0-90 degrees; the outer wing segment being pivotally connected with the inner wing segment at a wing tip, and the outer wing segment being adjusted at a rear sweep angle in a range of 0-90 degrees; and the nose being blunt. In the embodiment, the double-axis variable sweep wing mechanism has opposite influence trends of the inner wing segment and the outer wing segment on the center of pressure of the cruise missile during stretching, folding and flying, so as to control the change range of the center of pressure of the cruise missile in a very small interval, and make the wing sweep process have good maneuvering and stability characteristics and flight stability. In addition, the double-axis variable sweep wing mechanism is parallel to the fuselage when being folded, so that the cruise missile is convenient to store and transport, and the storage and deployment capability is improved.

An aircraft (10) comprising: a starboard swept wing (14A) and a port swept wing (14B), each swept wing having an inner wing section (32) comprising an integrated payload fuselage, an upper surface and a lower surface, 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; 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; one or more rear spars (34), in which the rear spar is disposed close to a trailing edge (22) of each wing to carry loads along each wing; a semi-buried engine (16)disposed at the trailing edge of the inner wing section of each wing; an encasement fairing comprising an upper surface and a lower surface; wherein the upper surface of the encasement fairing is disposed in front of the engine and forms a continuous surface with the upper surface of the wing to guide air flow into the engine; wherein the lower surface of the encasement fairing joins with the lower surface of the wing to form a cavity, and the lower surface of the encasement fairing extends below at least a portion of the lower surface of the wing; landing gear (40) movable between a retracted position and a deployed position, the landing gear comprising a strut (44) attached to a bogie (42), the strut pivotably attached to the aircraft, close to the rear spar of the aircraft at one end, and attached to the bogie at the opposite end, the landing gear disposed behind the rear spar; and in which the cavity is formed underneath the upper surface (48A) of the encasement fairing, in front of the engine, in which the cavity is for the storage of equipment, fuel or cargo.

The sub-span and super-span speed domain aerodynamic layout comprises double-shaft variable-sweep-wing mechanisms arranged at the bottom of a fuselage, the sweep angle can be freely changed and locked within the range of 0-90 degrees, each double-shaft variable-sweep-wing mechanism comprises an inner wing section and an outer wing section, the wing root of each inner wing section is in pivot connection with the fuselage, and the wing root of each outer wing section is in pivot connection with the fuselage. The sweep-forward angle of the inner wing section is adjusted within any angle of 0-90 degrees; the wing root of the outer wing section is pivotally connected with the wing tip of the inner wing section, and the sweepback angle of the outer wing section is adjusted at any angle of 0-90 degrees; the machine body is in a flat shuttle shape, and the machine head is in a pointed-end shape. According to the implementation mode, in the stretching, folding and flying processes, the influence trends of the double-shaft variable-swept-wing mechanism on the pressure center focus of the patrolling bomb are opposite, so that the pressure center focus change range of cross-speed domain deformation flight is controlled within an extremely small interval, and the pneumatic control stability is remarkably improved. In addition, when being stored, the double-shaft variable-swept-wing mechanism can be completely folded and parallel to the fuselage and is adaptive to narrow spaces such as a launch canister or a transport case, so that the storage and deployment capabilities are improved.

The application discloses a method and device for longitudinal aerodynamic force rapid analysis and water-exit attitude stability control of a variable-sweep wing trans-medium aircraft and electronic equipment, and comprises the following steps: aerodynamic analysis is carried out on the wings, fuselage and elevators of the aircraft separately; the aerodynamic force analysis of the wings is carried out by using open-source aerodynamic analysis software XFLR5 software, and the results of the aerodynamic force analysis of the wings in the multi-physical field simulation and computational fluid dynamics software STAR-CCM+ software are compared and verified; a mathematical model of the aircraft is established, and the control problem of the aircraft is mathematically abstracted; an extended state observer (ESO) is designed to observe the disturbance and the nonlinearity of the model, and a backstepping controller is designed to control the attitude of the variable-sweep wing trans-medium aircraft, so that the aircraft is rapidly stabilized. The application can significantly improve the aerodynamic parameter acquisition efficiency, accelerate the theoretical verification process, and effectively solve the stability control of the variable-sweep wing trans-medium aircraft in the water-exit stage.

The embodiment of the present application provides a main beam (3) of a curved variable sweep wing. The main beam (3) of the curved variable sweep wing is generated by combining a flexible leaf spring and a flexible hinge. According to the embodiment of the present application, on the basis of the leaf spring, a flexible cross hinge geometry feature is added, so that the main beam (3) has good large deformation stiffness decoupling performance keeping ability, and is suitable for the curved variable sweep wing.