Pincer wing for a wide speed range aircraft

Abstract

The present application relates to the field of variant aircraft, and specifically relates to a pincer wing for a wide-speed-range aircraft, comprising: an upper wing, a lower wing, an actuator, a transmission device, a wing linkage device, a track holding device, and a locking device; the actuator is connected with the transmission device, the transmission device is connected with the upper wing and the lower wing respectively, the actuator drives the upper wing and the lower wing to rotate around the fuselage as an axis through the transmission device; the wing linkage device is connected with the transmission device, so that the rotation angles of the first wing and the third wing are consistent, and the rotation angles of the second wing and the fourth wing are consistent; the track holding device is connected with the upper wing and the lower wing respectively, so as to limit the rotation paths of the upper wing and the lower wing; the locking device is connected with the upper wing and the lower wing respectively, so as to lock the positions of the upper wing and the lower wing after rotation; the present application can make the aircraft meet the aerodynamic requirements of different flight speeds.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of variable aircraft, in particular to a pincer wing for a wide-speed-range aircraft. BACKGROUND

[0002] The concept of variable aircraft was first proposed in the United States in the early 20th century. Variable aircraft can change the aerodynamic shape during flight, so that the aircraft can achieve good aerodynamic performance in the entire envelope, improve the flight speed range of the aircraft, and have wide-speed-range flight capability. To date, research on variable aircraft has always been of great concern and importance worldwide. With the improvement of technical level and the continuous accumulation of research experience, various forms of variable methods have been applied to various aircraft, further improving the flight performance of the aircraft and expanding the flight speed range of the aircraft.

[0003] Existing variable methods mainly include: telescopic wings, variable sweep wings, folding wings, and variable airfoils.

[0004] Telescopic wings retract a part of the wing into the main wing, and change the wing area by telescoping the part of the wing along the spanwise or chordwise direction to meet different flight speed requirements. This type of variable can be divided into two-segment telescopic wings and multi-segment telescopic wings. This type of variable is mainly realized by a telescopic mechanism composed of a servo motor, a spring, a telescopic guide rail, etc.

[0005] Variable sweep wings change the sweep angle of the wing by rotating the wing around a vertical rotating shaft arranged near the wing root through a variable sweep mechanism, so that the aircraft adapts to different flight conditions and balances the performance requirements between high-speed and low-speed flight. Variable sweep aircraft generally uses zero sweep angle or small sweep angle to provide sufficient lift during take-off and landing and low-speed flight, and increases the sweep angle of the wing to reduce flight resistance and improve cruising performance during high-speed flight.

[0006] The wings of folding wing aircraft can change the effective wing area by folding during flight to adapt to different flight speeds. The wings are unfolded to obtain a larger wing area during low-speed flight of the aircraft, and the wings are folded to reduce the effective wing area during high-speed flight. This type of aircraft involves many problems such as the reliability of the folding mechanism and flight stability, and has not been widely used.

[0007] Based on the development of flexible skin technology, variable airfoil aircraft emerged as the times require. Variable airfoil aircraft can respond to actual flight conditions in real time and adjust the airfoil of the wing in a timely manner, thereby achieving the effect of optimizing the performance of the aircraft and achieving multiple goals such as improving the range of the aircraft, widening the speed range of the aircraft, and improving the maneuverability of the aircraft.

[0008] With the further development of unmanned aerial vehicles, higher requirements are put forward for the variable form and variable mechanism. The miniaturization trend of unmanned aerial vehicles requires simple variable form and compact and reliable variable mechanism; the functional diversification trend requires further expansion of the flight speed range of the aircraft.

[0009] The prior art proposes the following solutions: The Chinese utility model patent with publication number CN216887196U proposes a new aircraft wing variable mechanism, which can simultaneously change the wing sweepback angle, aspect ratio and wing area through the actuator driving the variable mechanism. The variable form and mechanism of this scheme are relatively simple, but the shaft structure is weak, the mechanism reliability is poor, the mechanical properties of the flexible skin are highly dependent, and this scheme will cause the center of gravity of the whole aircraft to move greatly during the variable process.

[0010] The Chinese invention patent application with publication number CN114872881A proposes a large-stroke telescopic wing unmanned aerial vehicle and a wing telescopic mechanism. The invention can realize large-stroke and rapid telescoping of the wing, and the telescopic wing can make the unmanned aerial vehicle adapt to multiple flight states. However, the telescopic mechanism in this invention has certain requirements for the size of the wing, and it is difficult to apply to small-size wings, and it will cause wing aeroelastic problems caused by excessive aspect ratio.

[0011] The Chinese invention patent with publication number CN103979104B proposes a vertical take-off and landing tail stand type variable micro aerial vehicle and variable mechanism capable of changing the included angle of the wings. The aircraft has vertical take-off, flat flight and hovering capabilities, and has an X-shaped wing layout with two pairs of wings above and below. By changing the included angle of the wings, different flight state requirements are met, and the variable mechanism is compact and reliable, with small size and lightweight characteristics. However, the flight speed range of this aircraft is small, and it can only fly at low speed, without wide speed range flight capability.

[0012] The above technical solutions have researched the variable form and variable mechanism suitable for small aircraft, but there are still problems such as small flight speed range of the aircraft, insufficient strength of the small-size variable mechanism, and low realizability, which makes it difficult to realize reliable variable and wide speed range flight of small aircraft. SUMMARY

[0013] In view of the above problems, the present application provides a wide speed range aircraft and its pincer-shaped wing, which solves the technical problems of insufficient strength of the variable mechanism of the small-size variable aircraft and low realizability in the prior art.

[0014] In a first aspect, the present application provides a pincer-shaped wing for a wide speed range aircraft, comprising:

[0015] upper wing, lower wing, actuator, transmission device, wing linkage device, track retaining device, locking device;

[0016] The actuator is connected with the transmission device, the transmission device is connected with the upper wing and the lower wing respectively, and the actuator drives the upper wing and the lower wing to rotate around the fuselage as the axis through the transmission device;

[0017] The upper wing is a mirror-symmetrical first wing and a third wing, and the lower wing is a mirror-symmetrical second wing and a fourth wing.

[0018] The wing linkage device is connected with the transmission device, so that the first wing and the third wing have the same rotation angle, and the second wing and the fourth wing have the same rotation angle.

[0019] The track retaining device is connected with the upper wing and the lower wing respectively, and limits the rotation path of the upper wing and the lower wing.

[0020] The locking device is connected with the upper wing and the lower wing respectively, and locks the position of the upper wing and the lower wing after rotation.

[0021] Preferably, the root tip ratio and the sweep angle of the upper wing and the lower wing are the same, and the upper wing and the lower wing adopt a decomposable / combining airfoil design, which can completely fit, so that when the rotation angle of the upper wing and the lower wing is 0 degrees, the upper wing and the lower wing can be combined into an integral wing.

[0022] Preferably, the transmission device includes four transmission shafts 9 fixed with transmission gears 10, and the upper wing and the lower wing each include a wing spar 6; the four transmission gears 10 are matched with the wing spar 6 ends of the first wing, the second wing, the third wing and the fourth wing respectively; the wing spar 6 of the first wing 1, the second wing 2, the third wing 3 and the fourth wing 4 is respectively hinged to a first rotating shaft 5a, a second rotating shaft 5b, a third rotating shaft 5c and a fourth rotating shaft 5d fixed on the fuselage of the aircraft; the actuator 7 is two servo motors, the two servo motors are connected with two worm and gear mechanisms 8 respectively, and the two worm and gear mechanisms 8 drive the transmission shafts on which the transmission gears matched with the wing spar 6 ends of the first wing and the second wing are located to rotate.

[0023] Preferably, the wing linkage device 11 includes a linkage shaft and a linkage gear fixed on the linkage shaft, and the linkage gear is matched with the four transmission gears 10, so that the first wing and the third wing have the same rotation angle, and the second wing and the fourth wing have the same rotation angle.

[0024] Preferably, the fuselage partition frame 19 is located at the connection between the upper wing and the lower wing and the fuselage, the track retaining device includes a track groove 18 opened on the fuselage partition frame 19, a track sliding block 13 is arranged on the wing spar 6, and the track sliding block 13 moves in the track groove 18.

[0025] Preferably, the locking device comprises a position locking rudder 16 and a locking pin 17, a circular position locking hole 12 is formed at the end of the wing spar 6, the position locking rudder 16 is fixed to the fuselage bulkhead 19 and connected with the locking pin 17; the position locking rudder 16 drives the locking pin 17 to insert into the position locking hole 12 to complete the locking of the wing position.

[0026] Preferably, a fixed connection annular fairing 14 is further included, which is located at the connection between the wing and the fuselage, fixedly connected with the wing spar 6, and used for maintaining the integrity of the aerodynamic shape of the fuselage.

[0027] In the second aspect, the application provides a wide-speed-range aircraft with pincer wings, comprising a fuselage 20, a fuselage track groove 22, a horizontal tail 23 and a vertical tail 24, and the first wing 1 and the third wing 3 and the second wing 2 and the fourth wing 4 are mirror-symmetric about the XOZ plane of the body axis system.

[0028] The movement range of the first wing 1 and the third wing 3 is 0 degree to 40 degrees of upwash angle, and the movement range of the second wing 2 and the fourth wing 4 is 0 degree to 40 degrees of downwash angle.

[0029] Preferably, the fuselage 20 is an elongated body of revolution along the X axis of the body axis system, and adopts a truss beam type semi-hard shell structure.

[0030] Four fuselage track grooves are formed at the connection between the fuselage 20 and the wing for the rotation of the wing.

[0031] An installation interface is formed at the connection between the rear of the fuselage 20 and the horizontal tail 23 and the vertical tail 24.

[0032] Preferably, the first wing, the second wing, the third wing, the fourth wing, the horizontal tail 23 and the vertical tail 24 are all internally provided with a wing spar and a wing rib, and a reinforcing wing rib is arranged at the wing root.

[0033] The horizontal tail 23 and the vertical tail 24 are connected with the fuselage 20 through a fuselage reinforcing bulkhead.

[0034] Compared with the prior art, the application has at least the following beneficial effects:

[0035] (1) The pincer wings for the wide-speed-range aircraft provided by the application have the functions of decomposition and combination, so that the aircraft has the variable configuration capability of converting between the X type configuration and the conventional configuration; in the X type configuration state, the wings can further change the lift coefficient and the effective wing area by changing the included angle of the upper and lower wings, so that the aircraft meets the aerodynamic requirements at different flight speeds; the pincer wings can effectively improve the stall performance and cruising performance of the aircraft at low speed, and the upper and lower wings can be combined to further improve the upper limit of the flight speed of the aircraft, thereby expanding the flight speed range;

[0036] (2) The pincer-shaped wing variant implementation mechanism provided by the present application is a one-way power mechanism, which can ensure that the wing position is automatically locked after the wing is rotated, and prevent the wing from being displaced by external forces such as aerodynamic force and inertial force, and causing adverse effects on the mechanism and actuator;

[0037] (3) The pincer-shaped wing variant provided by the present application is simple in form, and the variant process does not cause the center of gravity to move significantly, and the implementation mechanism is compact and accurate in transmission, which can ensure that the left and right wings have symmetry, the number of actuators is small, different variant strategies can be met by simple adjustment, and the application range is wide. BRIEF DESCRIPTION OF DRAWINGS

[0038] The accompanying drawings are included to provide a further understanding of the present application, and are incorporated herein and constitute a part of this application.

[0039] Figure 1 A two-dimensional airfoil schematic diagram of the pincer-shaped wing for the wide-speed-range aircraft provided by the present application is shown in the figure.

[0040] Figure 2 A single-side wing merging state schematic diagram of the pincer-shaped wing for the wide-speed-range aircraft provided by the present application is shown in the figure.

[0041] Figure 3 A single-side wing disassembled state schematic diagram of the pincer-shaped wing for the wide-speed-range aircraft provided by the present application is shown in the figure.

[0042] Figure 4 A pincer-shaped wing variant implementation mechanism schematic diagram for hiding the fuselage partition frame and other structural members provided by the present application is shown in the figure.

[0043] Figure 5 A variant implementation mechanism schematic diagram for showing part of the fuselage partition frame structure provided by the present application is shown in the figure.

[0044] Figure 6 A variant aircraft schematic diagram using the pincer-shaped wing for the wide-speed-range aircraft provided by the present application is shown in the figure.

[0045] Figure 7 A schematic diagram of different states of the variant aircraft using the pincer-shaped wing for the wide-speed-range aircraft provided by the present application is shown in the figure.

[0046] Reference numerals: 1-first wing, 2-second wing, 3-third wing, 4-fourth wing, 5a-first rotating shaft, 5b-second rotating shaft, 5c-third rotating shaft, 5d-fourth rotating shaft, 6-spar, 7-actuator, 8-worm-gear mechanism, 9-transmission shaft, 10-transmission gear, 11-left-right wing linkage, 12-position locking hole, 13-track slider, 14-flow straightening shell, 15-stiffened wing rib, 16-position locking steering gear, 17-locking pin, 18-separation frame track slot, 19-fuselage separation frame, 20-fuselage, 21-variant realization mechanism, 22-fuselage track slot, 23-horizontal tail, 24-vertical tail. DETAILED DESCRIPTION

[0047] In order to enable a more clearly understanding of the above-mentioned objects, features and advantages of the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict. In addition, the present application can also be implemented in other ways different from those described herein, and therefore the protection scope of the present application is not limited by the specific embodiments disclosed below.

[0048] The following references Figure 1-Figure 7 A pincer wing for a wide-speed-range aircraft and an aircraft according to an embodiment of the present application are described in detail. Figure 1 A two-dimensional airfoil schematic diagram of the pincer wing for a wide-speed-range aircraft disclosed by the present application; Figure 2 A single-side wing merging state schematic diagram of the pincer wing for a wide-speed-range aircraft disclosed by the present application, wherein (a) is an isometric view of the wing merging state; (b) is a schematic diagram of the wing merging state viewed along the x-axis direction; Figure 3 A single-side wing disassembled state schematic diagram of the pincer wing for a wide-speed-range aircraft provided by the present application, wherein (a) is an isometric view of the wing disassembled state; (b) is a schematic diagram of the wing disassembled state viewed along the x-axis direction; Figure 4 A pincer wing variant realization mechanism schematic diagram provided by the present application for hiding structural members such as fuselage separation frames, wherein (a) is an isometric view of the mechanism; (b) is a schematic diagram of the mechanism viewed along the x-axis direction; Figure 5 A variant realization mechanism schematic diagram provided by the present application for showing part of the fuselage separation frame structure; Figure 6 A variant aircraft schematic diagram provided by the present application using the pincer wing for a wide-speed-range aircraft; Figure 7 A schematic diagram of different states of a variant aircraft provided by the present application using the pincer wing for a wide-speed-range aircraft, wherein (a) is a state of the aircraft when the rotation angles of the upper and lower wings are both greater than 0 degrees, at which time the aircraft is in an X-shaped layout; (b) is a state of the aircraft when the rotation angles of the upper and lower wings are both 0 degrees, at which time the aircraft is in a conventional layout.

[0049] As Figure 1 As shown in the drawings, the present application provides a pincer-shaped wing for a wide-speed-range aircraft, which is divided into an upper wing and a lower wing, wherein the upper wing uses a large-camber and small-thickness airfoil, and the lower wing uses a small-camber and medium-thickness airfoil; the lower surface curve of the upper wing airfoil is consistent with the upper surface curve of the lower wing airfoil, so that the upper and lower wing airfoils can be combined into an integral airfoil.

[0050] In some embodiments, the present application provides a pincer-shaped wing for a wide-speed-range aircraft, which has different operating states, and the left and right wings are symmetrical about the aircraft symmetry plane, the upper and lower wing root-tip ratios and the geometric parameters such as the sweepback angles are all the same, and the upper and lower wings can rotate about a rotation shaft parallel to the aircraft body and parallel to the body axis X; the upper and lower wings are combined as shown in Figure 2 , at this time, the rotation angles of the upper and lower wings are both 0 degrees, the upper and lower wings are combined into an integral wing, and the aircraft configuration is a conventional configuration suitable for high-speed flight; the upper and lower wings are separated as shown in Figure 3 , at this time, the rotation angles of the upper and lower wings are greater than 0 degrees, the upper wing is upside down and the lower wing is downside down, and the aircraft is an X-shaped configuration with excellent stall performance and cruising performance in low-speed flight. The pincer-shaped wing realizes the variable configuration of the aircraft through separation and combination, thereby further widening the flight speed range of the aircraft.

[0051] As shown in Figure 4 , Figure 5 , the present application provides a variable mechanism for a pincer-shaped wing of a wide-speed-range aircraft.

[0052] The variable mechanism mainly includes an actuator, a transmission device, a left and right wing linkage device, a track holding device, and a locking device. The actuator 7 is two servo motors, which respectively control the first and third wings and the second and fourth wings, and is powered by a battery and an engine power module. The control signal line is connected to the flight control equipment to receive the variable command to drive the wing to change. The transmission device includes a transmission shaft 9 and a transmission gear 10, which transmits the force and motion output by the actuator 7 to the corresponding wing. The left and right wing linkage device 11 transmits the motion of the third wing 3 and the fourth wing 4 to the first wing 1 and the second wing 2, and ensures that the rotation angles of the left and right wings are the same. The track holding device is composed of track sliders 13 on the wing spars 6 and partition frame track grooves 18, which can effectively ensure that the motion path of the wing is consistent with the planned path. The locking device is composed of a position locking hole 12, a position locking rudder 16, and a locking pin 17, which can further ensure that the position of the wing remains fixed after the variable change. The transmission device, the connection relationship, the track holding device, and the locking device of the left and right wings are consistent and symmetrical about the body axis XOZ plane.

[0053] In some embodiments, to avoid the wing position moving or the actuator 7 being damaged by the external force such as aerodynamic force and inertial force, the variable implementation mechanism is designed as a one-way power mechanism. In the variable implementation mechanism, a worm-gear mechanism 8 is arranged, which can ensure that the actuator 7 can normally drive the wing to rotate when it is working, and the wing position is self-locked and the external force cannot be transmitted back to the actuator 7 after the actuator stops working, thereby effectively avoiding the adverse effects of the external force on the wing on the mechanism.

[0054] In some embodiments, the variable implementation mechanism further includes a first rotating shaft 5a, a second rotating shaft 5b, a third rotating shaft 5c and a fourth rotating shaft 5d, all of which are fixedly connected to the aircraft fuselage and parallel to the body axis system X-axis where the fuselage axis is located, and the four wing spars 6 are respectively hinged to the corresponding rotating shafts. The end of the wing spar is a involute tooth shape, and the center of the tooth shape division circle is located on the center line of each rotating shaft; taking the first wing 1 and the third wing 3 as an example, the servo motor in the upper part of the actuator 7 is fixedly connected to the worm, and the motion is transmitted to the corresponding transmission shaft 9 and transmission gear 10 fixedly connected to the worm through the worm-gear mechanism 8; the transmission gear 10 is an involute tooth shape, and the modulus is the same as the modulus of the tooth shape at the end of the third wing 3 spar 6, and is engaged with the wing spar 6 to drive the third wing 3 to move; the motion of the third wing 3 is transmitted to the first wing 1 through the left and right wing linkage device 11 between the third wing 3 and the first wing 1, and the rotation angles of the first wing 1 and the third wing 3 are strictly the same. The variable method of the second wing 2 and the fourth wing 4 is the same as the above method, and the power is provided by the servo motor in the lower part of the actuator 7.

[0055] In some embodiments, a locking device and a track retaining device are also designed on the wing spar 6 and the fuselage bulkhead 19. The locking device is composed of a position locking hole 12, a position locking rudder 16 and a locking pin 17, the position locking rudder 16 is fixed to the fuselage bulkhead 19 and connected with the locking pin 17, and the position locking hole 12 is a circular small hole opened in the corresponding position of the wing spar 6 and the fuselage bulkhead 19; in the non-locking state, the locking pin 17 is located outside the position locking hole 12, when the wing moves to the corresponding position, the position locking rudder 16 drives the locking pin 17 to insert into the position locking hole 12, so that the locking of the wing position is realized, thereby further ensuring the absolute fixation of the wing position; the track retaining device includes a bulkhead track groove 18 on the fuselage bulkhead 19 and a track slider 13 on the wing spar 6, and the movement of the track slider 13 in the bulkhead track groove 18 can further constrain the rotation track of the wing, avoiding the wing deviating from the normal movement track due to the deformation of the structure.

[0056] In some embodiments, a ring-shaped fairing 14 is fixedly connected at the position where the four wing spars contact the fuselage, which moves with the wing spar and can always maintain the integrity of the aerodynamic shape of the fuselage during the movement of the wing, avoiding the additional aerodynamic resistance caused by the gap of the fuselage to reduce the flight efficiency.

[0057] As Figure 6 The present application provides a variable aircraft using the pincer wing of the present application. The aircraft comprises a fuselage 20, wings 1-4, a variable mechanism 21, a fuselage rail slot 22, a horizontal tail 23 and a vertical tail 24. Inside the fuselage are arranged engines, fuel tanks, batteries, data link devices, flight control devices and mission airborne devices. The first wing 1 and the third wing 3, and the second wing 2 and the fourth wing 4 are left-right symmetrical about the XOZ plane of the body axis system; the four wings can rotate about four rotating shafts fixed to the fuselage and parallel to the X axis, the movement range of the first wing 1 and the third wing 3 is 0 degree to 40 degrees of up angle of attack, and the movement range of the second wing 2 and the fourth wing 4 is 0 degree to 40 degrees of down angle of attack; in the X-shaped variable aircraft, no control surface is arranged on the wing, and the pitch, roll and yaw movements of the aircraft are controlled by the all-moving horizontal tail 23 and the vertical tail 24.

[0058] In some embodiments, in the variable aircraft, the fuselage 20 is an elongated body of revolution along the X axis of the body axis system, adopts a truss beam type semi-hard shell structure, mainly uses longitudinal beams and partition frames to bear force; at the connection between the variable mechanism and the wings, the horizontal tail 23 and the vertical tail 24 and the fuselage, the reinforced fuselage partition frame is arranged, and the ordinary partition frame is arranged at the remaining positions; four fuselage rail slots 22 are opened on both sides of the corresponding positions of the wings for the rotation of the wings; the horizontal tail 23 and the vertical tail 24 mounting interfaces are opened at the rear of the fuselage. The wings 1-4, the horizontal tail 23 and the vertical tail 24 are all double-beam structures, and the wing beams and wing ribs are arranged inside, and the reinforced wing ribs are arranged at the wing roots; the wing beams of the wings 1-4 are directly connected with the variable mechanism, and the wing beams of the horizontal tail 23 and the vertical tail 24 are connected with the fuselage 20 through the fuselage reinforced partition frame.

[0059] As Figure 7 shown, the variable aircraft has different operating states, and based on the variable mechanism provided by the present application, the variable aircraft can automatically change the wing included angle during flight or through receiving ground instructions, and realize variable configuration through the decomposition and combination function of the pincer wing, so as to realize wide speed range flight.

[0060] In the present application, unless otherwise clearly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integrated; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0061] In the present application, unless otherwise explicitly specified and limited, "on" or "under" of a first feature to a second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, "on", "above" and "over" of a first feature to a second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the first feature is horizontally higher than the second feature. "Under", "below" and "underneath" of a first feature to a second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the first feature is horizontally lower than the second feature.

[0062] In the present application, the terms "first", "second", "third", "fourth" are only for descriptive purpose, and should not be understood as indicating or implying relative importance. The term "a plurality of" means two or more, unless otherwise explicitly limited.

[0063] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. The present application can have various modifications and changes for those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A pincer wing for a wide speed range aircraft, characterized in that Comprise: Upper wing, lower wing, actuator, transmission device, wing linkage, track keeping device, locking device; The actuator is connected with the transmission device, the transmission device is connected with the upper wing and the lower wing respectively, and the actuator drives the upper wing and the lower wing to rotate around the fuselage as the axis through the transmission device respectively; The upper wing is a mirror image of the first wing and the third wing; the lower wing is a mirror image of the second wing and the fourth wing; The wing linkage is connected with the transmission device, so that the rotation angles of the first wing and the third wing are consistent, and the rotation angles of the second wing and the fourth wing are consistent; The track keeping device is connected with the upper wing and the lower wing respectively, and limits the rotation path of the upper wing and the lower wing; The locking device is connected with the upper wing and the lower wing respectively, and locks the position of the upper wing and the lower wing after rotation; The transmission device comprises four transmission shafts (9) fixed with transmission gears (10), and the upper wing and the lower wing each comprise a wing spar (6); the four transmission gears (10) are matched with the wing spars (6) at the ends of the first wing, the second wing, the third wing and the fourth wing respectively; The wing spars (6) of the first wing (1), the second wing (2), the third wing (3) and the fourth wing (4) are respectively hinged to the first rotating shaft (5a), the second rotating shaft (5b), the third rotating shaft (5c) and the fourth rotating shaft (5d) fixed on the fuselage of the aircraft; The actuator (7) is two servo motors, the two servo motors are connected with two worm and gear mechanisms (8) respectively, and the two worm and gear mechanisms (8) drive the transmission shafts where the transmission gears matched with the wing spars (6) at the ends of the first wing and the second wing are located to rotate.

2. The wide speed range aircraft pincer wing of claim 1, wherein: The root-tip ratio and the sweepback angle of the upper wing and the lower wing are the same; the upper wing and the lower wing each adopt a decomposable / combining airfoil design, can be completely fitted, so that when the rotation angle of the upper wing and the lower wing is 0 degree, the upper wing and the lower wing can be combined into an integral wing.

3. The pincer-shaped wing for wide-speed-range aircraft according to claim 1, characterized in that: The wing linkage (11) comprises a linkage shaft and linkage gears fixed on the linkage shaft, the linkage gears are matched with the four transmission gears (10), so that the rotation angles of the first wing and the third wing are consistent, and the rotation angles of the second wing and the fourth wing are consistent.

4. The pincer-shaped wing for wide-speed-range aircraft according to claim 3, characterized in that: The fuselage partition frame (19) is located at the connection between the upper wing and the lower wing and the fuselage, the track keeping device comprises track grooves (18) opened on the fuselage partition frame (19), and track sliders (13) are arranged on the wing spars (6) and move in the track grooves (18).

5. The pincer-shaped wing for wide-speed-range aircraft according to claim 4, characterized in that: The locking device comprises a position locking rudder (16) and a locking pin (17), circular position locking holes (12) are opened at the ends of the wing spars (6), the position locking rudder (16) is fixed on the fuselage partition frame (19) and connected with the locking pin (17); the position locking rudder (16) drives the locking pin (17) to insert into the position locking hole (12) to complete the locking of the position of the wing.

6. The wide-speed-range aircraft pincer wing according to claim 1, characterized in that: Further comprising a fixed ring-shaped fairing (14) fixedly connected with the spars (6) for maintaining the integrity of the aerodynamic shape of the fuselage.

7. A wide speed range aircraft having the pincer wing of any one of claims 1-6, characterized in that Comprise: The fuselage (20), the fuselage rail groove (22), the horizontal tail (23) and the vertical tail (24), the first wing (1) and the third wing (3), the second wing (2) and the fourth wing (4) are mirror symmetric about the body axis system XOZ plane; The movement range of the first wing (1) and the third wing (3) is 0 degree to 40 degree up angle, and the movement range of the second wing (2) and the fourth wing (4) is 0 degree to 40 degree down angle.

8. The aircraft according to claim 7, characterized in that: The fuselage (20) is an elongated body of revolution along the body axis system X axis, and adopts a truss type semi-hard shell structure; Four fuselage rail grooves are arranged at the connection between the fuselage (20) and the wings for the rotation of the wings; Mounting interfaces are arranged at the connection between the rear of the fuselage (20) and the horizontal tail (23) and the vertical tail (24).

9. The aircraft according to claim 8, characterized in that: The first wing, the second wing, the third wing, the fourth wing, the horizontal tail (23) and the vertical tail (24) are all internally provided with spars and ribs, and are all arranged with reinforced ribs at the wing roots; the horizontal tail (23) and the vertical tail (24) are connected with the fuselage (20) through fuselage reinforcing bulkheads.

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