Stacked folding wing of patrol flight unmanned aerial vehicle with trailing edge control surface

Abstract

The invention provides an unmanned aerial vehicle (UAV) stacked folding wing with a trailing edge control surface, and belongs to the field of novel UAVs, the unmanned aerial vehicle comprises a fuselage connecting structure, an inner side half wing, an outer side half wing, a compression nut, a torsion spring and a locker, the inner side half wing and the outer side half wing are sequentially connected to the fuselage connecting structure in a sleeving manner; the two half wings are coaxially stacked and connected with the fuselage connecting structure through the compression nut, the half wing close to the fuselage is an inner side half wing, the other half wing is an outer side half wing, the two half wings provide rotating force through the torsion spring, and position locking is achieved through the locker; according to the invention, the blank of special-layout patrol flight unmanned aerial vehicles, especially stacked folding wings with trailing edge control surfaces, is filled up.

Description

Technical Field

[0001] The invention belongs to the field of novel unmanned aerial vehicles, and relates to a patrol unmanned aerial vehicle with stacked folding wings provided with a trailing edge rudder surface. Background Art

[0002] Patrol UAV is a new type of UAV, with the main features of cruising flight mode, rapid response / rapid launch, low cost, high efficiency and flexible use. Patrol UAVs are generally stored and launched in a launch tube to achieve rapid launch, and for this purpose, a foldable and unfoldable wing design is generally adopted. The wing folding and unfolding mechanism and structure are one of the key technologies of patrol UAVs and have a significant impact on the performance of patrol UAV platforms. The design of the wing folding and unfolding mechanism and structure is quite difficult, and it is even more difficult for special layouts (such as the front wing and the rear wing are both installed on the upper or lower side of the fuselage) and wings with trailing edge rudders. Patrol UAV manufacturers in various countries around the world have developed their own wing folding and unfolding mechanism and structural design schemes when developing patrol UAV products, and some manufacturers and individuals have applied for patents for the wing folding and unfolding mechanism and structural design. However, research on patrol UAV platforms with special layouts, especially stacked folding wings with trailing edge rudders, is still insufficient. Summary of the invention

[0003] The present invention provides a stackable folding wing of a patrol unmanned aerial vehicle with a trailing edge control surface. The wing has a trailing edge control surface, such as an elevator, an aileron, an elevator, etc. The present invention adopts tube-tube matching, hole-axis matching, surface-surface matching and other methods, and forms a stackable folding wing structure through a load-bearing structure-folding and unfolding mechanism, a composite material structure, a leaf spring pin-movable stopper tapered hole locking mechanism and the like.

[0004] A patrol drone with stacked folding wings with trailing edge rudders, the stacked folding wings comprising a fuselage connection structure, an inner half-wing, an outer half-wing, a clamping nut, a torsion spring and a locker, the inner half-wing and the outer half-wing are sequentially sleeved and connected to the fuselage connection structure, the two half-wings are coaxially stacked and connected to the fuselage connection structure through a clamping nut, the half-wing close to the fuselage is the inner half-wing, and the other is the outer half-wing, a torsion spring is installed between the two half-wings to provide rotational force, and the unfolded position is locked by a lock; when folded, the two half-wings are stacked up and down and stored in the lower or upper part of the fuselage to achieve a folded state of the entire aircraft, at which time the cross-sectional size is the smallest; when unfolded, the two half-wings rotate around the axis at specific angles on both sides, and the locker locks the two half-wings in the unfolded position. Specifically:

[0005] The fuselage connection structure is a hollow cylinder, which is used to fix the entire stacked folding wing with the main fuselage. A platform is symmetrically arranged at the bottom or top of the fuselage connection structure according to the central symmetry plane of the fuselage as a horizontal bottom plate. A cylindrical protruding mounting pipe shaft is formed at the center of the horizontal bottom plate. The inner wall of the mounting pipe shaft is formed with a thread for cooperating with the thread of the clamping nut. The mounting pipe shaft is used as the mounting connection bearing structure of the two half wings and the folding and unfolding central rotating shaft; the side wall of the mounting pipe shaft and the horizontal bottom plate at the bottom thereof are formed with openings as line passages for the passage of the rudder servo lines and plugs on the trailing edge of the two half wings; the horizontal bottom plate outside the mounting pipe shaft is formed with a small height concentric ring, and the plane of the ring serves as an annular positioning surface for fitting with the outer surface of the wing root joint of the inner half wing, and is used as the wing surface high-direction positioning surface and bearing surface. When the wing surface is unfolded and folded, the annular positioning surface and the wing root joint plane have relative movement, and a lubricant is used to reduce the friction between the two; a fixed stopper is arranged at the rear end of the fuselage connection mechanism along the central symmetry plane.

[0006] The inner half wing and the outer half wing are symmetrical structures, and their appearance structures are basically the same, both of which include a basic wing surface, a trailing edge control surface, a wing root joint and a control surface actuation system.

[0007] The basic wing surface is an aerodynamic surface, and its cross-section is a standard wing profile; the basic wing surface is connected to the wing root joint at its root by a sleeve fit, and the basic wing surface is connected to the trailing edge rudder surface by a flexible hinge.

[0008] The wing root joint is an integral machined part of aluminum alloy, and its basic structure is a disc with a central cylindrical hole. The disc extends outward to form a front and rear parallel wing surface connection structure and a servo mounting structure, which are respectively used for sleeve connection of the basic wing surface and fixed connection of the rudder surface actuation system; the aperture of the central cylindrical hole matches the mounting tube shaft on the fuselage connection structure to realize the insertion of the mounting tube shaft, and the inner half wing and the outer half wing are successively sleeved on the mounting tube shaft through the central cylindrical hole on their wing root joints, and then the clamping nut is tightened on the end of the mounting tube shaft so that the clamping nut is tightly attached to the outer half wing, thereby fixing the two half wings on the mounting tube shaft and being able to rotate freely around the mounting tube shaft and withstand its gravity and load along the vertical axis; the central cylindrical holes of the two wing root joints are both designed with a single-sided opening, that is, the two opposite sides are processed to form The two wing root joints are cylindrically depressed, and the surfaces of the wing root joints outside the two cylindrical depressions are respectively provided with a depressed annular groove and a convex annular tube. The annular tube and the annular groove fit tightly to transfer the load. After the annular tube and the annular groove fit together, the two cylindrical depressions form an approximately closed space for installing a torsion spring. The rear parts of the two wing root joints are both arranged with movable blocks, and the inner end faces of the two movable blocks respectively cooperate with the end faces on both sides of the fixed blocks on the fuselage connection structure. When the half wings are unfolded, the movable blocks rotate with the half wings. At the end of the unfolding stroke, the movable blocks collide with the fixed blocks, and the impact absorbs the rotation energy of the two half wings, playing the role of a limiting and damping device. Conical holes are formed on the inner end faces of the movable blocks, and guide grooves are formed on the inner sides of the cone holes. The slope surface at the bottom of the guide groove has a specific slope angle, which is used to cooperate with the locker to achieve unfolding position locking.

[0009] The rudder surface actuation system includes a servo, a rocker arm and an angular ear piece. The servo is installed on the servo installation structure of the wing root joint. The servo output shaft is parallel to the trailing edge rudder surface rotating shaft, and a certain distance is left between the two along the longitudinal direction and the height direction of the aircraft. A gear is arranged on the servo output shaft, and a multi-tooth sleeve is arranged at the root of the rocker arm. The gear and the multi-tooth sleeve are sleeved and connected into one by standard screws; a pin is installed on the rocker arm, and the pin and the rocker arm are connected by a pin hole interference fit or a threaded connection; the angular ear piece is installed on the inner side end of the trailing edge rudder surface, and a notch is opened at the end thereof to cooperate with the pin on the rocker arm. The servo output shaft drives the rocker arm to rotate, and the pin on the rocker arm cooperates with the notch on the angular ear piece to drive the trailing edge rudder surface to rotate.

[0010] The torsion spring is fixedly installed in the space formed between the cylindrical recesses on the wing root joints of the two half wings, and is sleeved on the installation pipe shaft of the fuselage connection structure.

[0011] The locking device comprises a long strip leaf spring and tapered pins fixed at both ends thereof, the long strip leaf spring being fixed on a fixed stopper of the fuselage connecting structure, and being arranged horizontally symmetrically along the center plane of symmetry, the two tapered pins respectively cooperate with tapered holes on the inner end faces of the movable stops on the two half wings to lock the two half wings in the deployed position, specifically: at the end section of the half-wing deployment stroke, the tapered pin enters the entrance section of the slope surface at the bottom of the guide groove inside the tapered hole, the end face of the tapered pin contacts the slope surface of the guide groove and slides upward along the slope to generate an extrusion force, the leaf spring deforms backward under the action of the extrusion force, and the two half wings continue to rotate until the tapered pin passes over the top of the slope surface and is inserted into the tapered hole under the action of the elastic force of the leaf spring, the tapered pin cooperates with the tapered hole to lock the two wings in the deployed position, at this time, the end face of the movable stopper of the wing root joint on the two half wings contacts the fixed stopper of the fuselage connecting structure.

[0012] Furthermore, the basic wing surface structure includes a main wing surface and a metal wing tip, which are connected by a sleeve fit; the main wing surface includes a core and a shell wrapped around the core, the core includes a carbon tube beam, a filling material and a foam core, the inner root of the carbon tube beam is inserted into the wing root joint, and is fixedly connected to the wing root joint by an adhesive, the carbon tube beam is filled with filling material, and there are two foam cores, which are arranged on both sides of the carbon tube beam; the inner surface of the shell is adapted to the outer surface of the wing root joint, and the two are connected by co-bonding / co-curing; the metal wing tip includes an end plate and a connecting block, the connecting block is sleeved in the shell, and the end plate and the connecting block are connected by fasteners or integral machining.

[0013] Furthermore, the trailing edge control surface includes a rigid foam core and a carbon fiber panel wrapped thereon.

[0014] Furthermore, the flexible hinge piece is a Kevlar fiber cloth of a certain thickness, and the front and rear parts of the flexible hinge piece are respectively connected to the inside of the trailing edge of the basic airfoil and the inside of the front edge of the trailing edge rudder.

[0015] The beneficial effect of the present invention is that the stacked folding wings of the patrol UAV with trailing edge control surfaces provided by the present invention fill the gap in patrol UAVs with special layouts, especially stacked folding wings with trailing edge control surfaces. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is the overall layout diagram when the wing is unfolded, where (a) is the axonometric diagram from a top-down perspective, and (b) is the axonometric diagram from a bottom-up perspective.

[0017] Figure 2 This is a schematic diagram of the fuselage connection structure.

[0018] Figure 3 Schematic diagram of the inner half-wing structure, where (a) is a top view, (b) is a CC cross-sectional view, (c) is a DD cross-sectional view, and (d) is a bottom view.

[0019] Figure 4 Schematic diagram of the outer half-wing structure, where (a) is a schematic diagram from a top view, (b) is a FF cross-sectional view, (c) is a GG cross-sectional view, and (d) is a schematic diagram from a bottom view.

[0020] Figure 5 The partial enlarged views of the present invention, wherein (a) is the overall partial enlarged view of the wing in the unfolded state, (b) is the HH cross-sectional view, and (c) is the partial enlarged view of the outer half wing.

[0021] Figure 6 This is the AA section view.

[0022] Figure 7 This is the BB cross-sectional view.

[0023] In the figure: 1 fuselage connection structure; 2 inner half wing; 3 outer half wing; 4 clamping nut; 5 locker; 6 torsion spring; 11 mounting tube shaft; 12 annular positioning surface; 13 fixed stopper; 14 line through-hole; 21 inner wing root joint; 211 central cylindrical hole; 212 annular groove; 22 basic wing surface; 221 shell; 222 carbon tube beam; 223 foam core; 224 flexible hinge piece; 23 trailing edge rudder surface; 24 rudder surface actuation system; 241 servo; 242 rocker arm; 243 angular ear piece; 31 outer wing root joint; 311 annular tube. DETAILED DESCRIPTION

[0024] The technical solution of the present invention is described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. All other embodiments improved or adjusted by ordinary technicians in the field based on the embodiments of the present invention belong to the protection scope of the present invention.

[0025] This embodiment provides a stacked folding wing of a patrol drone with a trailing edge control surface, and the stacked folding wing comprises a fuselage connection structure 1, an inner half wing 2, an outer half wing 3, a clamping nut 4, a torsion spring 6 and a locker 5. When folding, the two half wings are stacked up and down and stored in the lower or upper part of the fuselage to achieve a folded state of the whole machine, at which time the cross-sectional size is the smallest; when unfolding, the two half wings rotate around the axis to a specific angle (generally about 90°, depending on the designed wing leading edge sweep angle), and the locker 5 locks the two half wings in the unfolded position. Figure 1 shown.

[0026] like Figure 2As shown, the fuselage connection structure 1 is a hollow cylinder, which is used to fix the entire stacked folding wing to the main fuselage. A platform is symmetrically arranged at the bottom or top of the fuselage connection structure 1 according to the central symmetry plane of the fuselage as a horizontal bottom plate. A cylindrical protruding mounting pipe shaft 11 is formed at the center of the horizontal bottom plate. The inner wall of the mounting pipe shaft 11 is threaded for mating with the thread of the clamping nut 4. The mounting pipe shaft 11 serves as the mounting connection bearing structure of the two half wings and the folding and unfolding central rotation axis, and has sufficient strength and rigidity, and strict shape, position and matching size tolerances; the side wall of the mounting pipe shaft 11 and its bottom An opening is formed on the horizontal bottom plate as a line passage 14, which serves as a passage for the lines and plugs of the rudder surfaces 23 and the steering gear 241 on the trailing edges of the two half-wings; a small height concentric ring is formed on the horizontal bottom plate outside the installation tube shaft 11, and the plane of the ring serves as an annular positioning surface 12, which is used to fit with the outer surface of the wing root joint of the inner half-wing 2, and is used as the high-direction positioning surface and bearing surface of the wing surface. When the wing surface is unfolded and folded, the annular positioning surface 12 and the wing root joint plane have relative movement, and a lubricant is used to reduce the friction between the two; a long strip fixed stopper 13 is arranged along the central symmetry plane at the rear end of the fuselage connection mechanism.

[0027] like Figure 3 As shown, the inner half-wing 2 includes a basic wing surface 22, a trailing edge control surface 23, an inner wing root joint and a control surface actuation system 24. The outer shape of the basic wing surface 22 is an aerodynamic outer shape, and the cross-sectional shape is a standard airfoil; the structure of the basic wing surface 22 includes a main wing surface, a metal wing tip and a flexible hinge 224, and the main wing surface and the metal wing tip are connected by fitting; the main wing surface includes a core and a shell 221 wrapped outside the core, and the shell 221 is a carbon fiber panel, and the core includes a carbon tube beam 222, a filling material and a foam core 223, and the inner root of the carbon tube beam 222 is inserted into the wing surface connection structure of the wing root joint located at the root of the main wing surface, and is fixedly connected by an adhesive, and the carbon tube beam 222 is filled with a filling material The filling material is twisted strips or resin, etc. There are two foam cores 223 arranged on both sides of the carbon tube beam 222; the metal wing tip includes an end plate and a connecting block, the connecting block is sleeved in the shell 221 of the main wing, and the end plate and the connecting block are connected by fasteners or integral machining. The flexible hinge piece 224 is located at the trailing edge of the main wing and is used to connect the trailing edge rudder surface 23. The flexible hinge piece 224 is a Kevlar fiber cloth of a certain thickness (thickness is about 0.20mm, 0.30mm, etc.), and the front and rear of the flexible hinge piece 224 are respectively connected to the inside of the trailing edge of the main wing and the inside of the leading edge of the trailing edge rudder surface 23

[0028] The trailing edge control surface 23 includes a rigid foam core 223 and a carbon fiber panel wrapped thereon.

[0029] The inner wing root joint 21 is an integrally machined aluminum alloy part. The basic structure of the inner wing root joint 21 is a disc with a central cylindrical hole 211. The disc extends outwardly to form a front and rear juxtaposed wing surface connection structure and a steering gear installation structure, which are respectively used for sleeve connection with the basic wing surface 22 and fixed connection with the rudder surface actuation system 24; the wing surface connection structure at the front accounts for about 60% of the chord length, and the steering gear installation structure at the rear accounts for about 40% of the chord length. The cross section of the inner wing root joint 21 along the chord direction is the same as that of the basic wing surface 22, and its outer shape surface is similar to the shell 22 of the basic wing surface 22. 1, the inner surface of the wing root joint 21 is adapted, and the two are connected by co-bonding / co-curing. The surface of the inner wing root joint 21 is provided with longitudinal and transverse grooves to achieve high bonding strength. Holes are formed in the wing surface connection structure for inserting the carbon tube beam 222 in the basic wing surface 22. In order to further improve the connection strength, the inner wing root joint 21 and the shell 221 can also be connected by fasteners or by sewing holes + fiber bundles; the steering gear mounting structure is adapted to the steering gear 241 in the rudder surface actuation system 24, and its bottom plate is provided with 3 mounting bosses with threaded holes The threaded hole positions correspond to the center positions of the three mounting lugs of the servo 241 respectively; the diameter of the central cylindrical hole 211 of the inner wing root joint 21 disk matches the mounting tube shaft 11 on the fuselage connection structure 1 to enable the mounting tube shaft 11 to be inserted, and the central cylindrical hole 211 is processed away from the fuselage connection structure 1 to form a cylindrical depression for mounting the torsion spring 6, and a mounting hole is formed on the bottom surface of the cylindrical depression, and the distance between the mounting hole and the center of the circle is the same as the radius of the middle diameter of the torsion spring 6, and a concave annular groove 212 is provided on the surface of the wing root joint outside the cylindrical depression; the inner wing root joint A movable stopper is arranged at the rear of the head (the position of the straight line trailing edge adjacent to the semicircular outer surface), and its inner end face cooperates with the end face of the side face of the fixed stopper 13 on the fuselage connection structure 1. When the inner half-wing 2 is unfolded, the movable stopper rotates with the inner half-wing 2. At the end of the unfolding stroke, the movable stopper collides with the fixed stopper 13, and the impact absorbs the rotation energy of the inner half-wing 2, playing the role of a limiting and damping device. A tapered hole is formed on the inner end face of the movable stopper, and a guide groove is formed on the inner side of the tapered hole. The slope surface at the bottom of the guide groove has a specific slope angle, which is used to cooperate with the locker 5 to achieve unfolded position locking.

[0030] The control surface actuation system 24 comprises a steering gear 241, a rocker arm 242 and an angular ear piece 243. The steering gear 241 is mounted on the steering gear mounting structure of the inner wing root joint 21. The output shaft of the steering gear 241 is parallel to the rotating shaft of the trailing edge control surface 23. A certain distance is left between the two along the longitudinal direction and the height direction of the aircraft. A gear is arranged on the output shaft of the steering gear 241. A multi-tooth sleeve is arranged at the root of the rocker arm 242. The gear and the multi-tooth sleeve are sleeved and connected into one by standard screws. A pin is installed, and the pin and the rocker arm 242 are connected by an interference fit of a pin hole or a threaded connection; an angular ear piece 243 is installed on the inner end of the trailing edge rudder surface 23, and a slot is opened at its end to cooperate with the pin on the rocker arm 242. The output shaft of the servo 241 drives the rocker arm 242 to rotate, and the pin on the rocker arm 242 cooperates with the slot on the angular ear piece 243 to drive the trailing edge rudder surface 23 to rotate; the servo 241 adopts a relatively open installation and connection design, which is convenient for maintenance and guarantee.

[0031] The outer half wing 3 and the inner half wing 2 are symmetrical structures, and the outer shapes and structures of the two are basically the same. The difference is that the cylindrical depression on the outer wing root joint 31 of the outer half wing 3 is located on the side facing the fuselage connection structure 1, and a convex annular tube 311 is provided on the surface of the outer wing root joint 31 outside the cylindrical depression, such as Figure 4 and Figure 5 As shown; the inner half wing 2 and the outer half wing 3 are sequentially sleeved on the mounting tube shaft 11 of the fuselage connection structure 1 through the central cylindrical hole 211 on the wing root joint, and then the clamping nut 4 is tightened on the end of the mounting tube shaft 11, so that the clamping nut 4 is tightly attached to the outer half wing 3, so that the two half wings are fixed on the mounting tube shaft 11 and can rotate freely, and bear its gravity and load along the vertical axis direction. After installation, the annular tube 311 and the annular groove 212 on the wing root joints of the two half wings are tightly fitted to transfer the load, and the two cylindrical depressions form an approximately closed space for installing the torsion spring 6, as shown in FIG. Figure 6 and Figure 7 The wing root joints of the two half wings and the installation pipe axis 11 of the fuselage connection structure 1 form an organic overall efficient load-bearing structure through pipe-to-pipe matching, hole-to-axis matching, and surface-to-surface matching, which can achieve symmetrical and complete load balance of the two half wings, and transmit asymmetric bending loads and vertical loads to the fuselage.

[0032] The torsion spring 6 is installed in the space formed between the cylindrical recesses on the wing root joints of the two half wings. It is sleeved on the mounting tube axis 11 of the fuselage connection structure 1, and the two ends are fixedly connected by matching the central arm of the torsion spring 6 with the mounting hole on the bottom surface of the cylindrical recess.

[0033] The locking device 5 is a long strip leaf spring and two tapered pins. The two ends of the long strip leaf spring are connected with holes. The lower parts of the two tapered pins are small-sized cylinders, which are respectively connected with the two connecting holes through interference fit and are fixedly connected to form a whole by welding or screwing. The long strip leaf spring is fixed on the fixed stopper 13 of the fuselage connection structure 1, which is horizontally symmetrically arranged along the symmetry center plane. The two tapered pins are respectively matched with the tapered holes on the inner end faces of the movable stoppers on the two half wings to achieve the locking of the two half wings in the deployed position. At the end of the half-wing deployment stroke, the tapered pin enters the entrance section of the slope surface at the bottom of the guide groove inside the tapered hole, the end face of the tapered pin contacts the slope surface of the guide groove and slides upward along the slope to generate an extrusion force, the leaf spring deforms backward under the action of the extrusion force, and the two half-wings continue to rotate until the tapered pin passes the top of the slope surface and is inserted into the tapered hole under the elastic force of the leaf spring. The tapered pin cooperates with the tapered hole to lock the two wings in the deployed position. At this time, the end faces of the movable blocks of the wing root joints of the two half-wings contact the fixed blocks 13 of the fuselage connection structure 1, as shown in FIG. Figure 5 shown.

[0034] The above-described embodiments merely express the implementation methods of the present invention, but they should not be understood as limiting the scope of the present invention. It should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

Claims

1. A patrol UAV with stacked folding wings with trailing edge control surfaces, characterized in that: The stacked folding wing comprises a fuselage connection structure (1), an inner half wing (2), an outer half wing (3), a clamping nut (4), a torsion spring (6) and a locker (5). The inner half wing (2) and the outer half wing (3) are sequentially sleeved and connected to the fuselage connection structure (1). The two half wings are coaxially stacked and connected to the fuselage connection structure (1) through the clamping nut (4). The half wing closer to the fuselage is the inner half wing (2), and the other is the outer half wing (3). A torsion spring (6) is installed between the two half wings to provide a rotational force, and the unfolded position is locked through the locker (5); when folding, the two half wings are stacked one above the other and stored in the lower part or the upper part of the fuselage to achieve a folded state of the entire aircraft; when unfolding, the two half wings are rotated around the axis to a specific angle on both sides, and the locker (5) locks the two half wings in the unfolded position.

2. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 1, characterized in that: The specific structure of the stacked folding wing is as follows: The fuselage connection structure (1) is a hollow cylinder, which is used to fix the entire stacked folding wing to the main fuselage. A horizontal bottom plate is symmetrically arranged at the bottom or top of the fuselage connection structure (1) according to the central symmetry plane of the fuselage. A cylindrical protruding installation pipe shaft (11) is formed at the center of the horizontal bottom plate, and the inner wall of the installation pipe shaft (11) is formed with a thread. A small height concentric ring is formed on the horizontal bottom plate outside the installation pipe shaft (11), and the plane of the ring serves as an annular positioning surface (12) for fitting with the outer surface of the inner half wing (2); a fixed stopper (13) is arranged at the rear end of the fuselage connection mechanism along the central symmetry plane. The inner half wing (2) and the outer half wing (3) are symmetrical structures, and the two have basically the same appearance structure, and both include a basic wing surface (22), a trailing edge control surface (23), a wing root joint and a control surface actuation system (24); The basic wing surface (22) is an aerodynamic shape, and its cross-section is a standard wing profile; the basic wing surface (22) is connected to the wing root joint at its root by a sleeve fit, and the basic wing surface (22) is connected to the trailing edge rudder surface (23) by a flexible hinge sheet (224); The basic structure of the wing root joint is a disk with a central cylindrical hole (211), and the disk extends outward to form a front and rear parallel wing surface connection structure and a steering gear (241) installation structure, which are respectively used for sleeve connection with the basic wing surface (22) and fixed connection with the rudder surface actuation system (24); the aperture of the central cylindrical hole (211) matches the installation tube shaft (11) on the fuselage connection structure (1) to achieve the insertion of the installation tube shaft (11), the inner half wing (2) and the outer half wing (3) are sequentially sleeved on the installation tube shaft (11) through the central cylindrical hole (211) on the wing root joint, and then the clamping nut (4) is tightened on the end of the installation tube shaft (11), so that the two half wings are fixed on the installation tube shaft (11) and can be wound around the installation tube shaft (11). The tube-mounting shaft (11) is freely rotatable; a cylindrical depression is formed on one side opposite to the central cylindrical holes (211) of the two wing root joints; an annular groove (212) and an annular tube (311) are respectively provided on the surfaces of the wing root joints outside the two cylindrical depressions; the annular tube (311) and the annular groove (212) are tightly fitted to transfer the load; after the annular tube (311) and the annular groove (212) are fitted together, the space formed by the two cylindrical depressions is used to install the torsion spring (6); movable blocks are arranged at the rear of the two wing root joints; the inner end faces of the two movable blocks are respectively matched with the end faces on both sides of the fixed block (13) on the fuselage connection structure (1); and tapered holes are formed on the inner end faces of the movable blocks for matching with the locker (5) to achieve deployment position locking; The control surface actuation system (24) comprises a steering gear (241), a rocker arm (242) and an angular ear piece (243). The steering gear (241) is mounted on the steering gear (241) mounting structure of the wing root joint. The output shaft of the steering gear (241) is parallel to the rotating shaft of the trailing edge control surface (23). A certain distance is left between the two along the longitudinal direction and the height direction of the aircraft. A gear is arranged on the output shaft of the steering gear (241). A multi-tooth sleeve is arranged at the root of the rocker arm (242). The gear and the multi-tooth sleeve are sleeved and connected into one body. A pin is mounted on the rocker arm (242). The angular ear piece (243) is mounted on the inner end of the trailing edge control surface (23). A notch is opened at the end of the rocker arm (242) to match with the pin. The output shaft of the steering gear (241) drives the rocker arm (242) to rotate. The pin on the rocker arm (242) matches with the notch on the angular ear piece (243) to drive the trailing edge control surface (23) to rotate. The torsion spring (6) is fixedly mounted in the space formed between the cylindrical recesses on the wing root joints of the two half-wings, and is sleeved on the mounting tube shaft (11) of the fuselage connection structure (1); The locking device (5) comprises a long strip leaf spring and tapered pins fixed at both ends thereof. The long strip leaf spring is fixed on a fixed stopper (13) of the fuselage connection structure (1) and is arranged horizontally symmetrically along the symmetry center plane. The two tapered pins respectively cooperate with tapered holes on the inner end surfaces of the movable stops on the two half wings to achieve locking of the two half wings in the unfolded position.

3. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: The side wall of the installation tube shaft (11) and the horizontal bottom plate at the bottom thereof are provided with openings as line passages (14) for the lines and plugs of the steering gear (241) on the trailing edge rudder surface (23) to pass through.

4. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: Lubricant is used between the annular positioning surface (12) and the wing root joint to reduce friction.

5. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: The wing root joint is an integral machined part of aluminum alloy.

6. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: A guide groove is formed on the inner side of the tapered hole of the movable stopper, and the slope surface at the bottom of the guide groove has a specific slope angle. At the end of the half-wing unfolding stroke, the tapered pin of the locker (5) enters the entrance section of the slope surface at the bottom of the guide groove inside the tapered hole, and the end face of the tapered pin contacts the slope surface of the guide groove and slides upward along the slope to generate an extrusion force. The leaf spring deforms backward under the action of the extrusion force, and the two half-wings continue to rotate until the tapered pin passes the top of the slope surface and is inserted into the tapered hole under the action of the elastic force of the leaf spring. The tapered pin cooperates with the tapered hole to lock the two wings in the unfolded position. At this time, the end face of the movable stopper of the wing root joint of the two half-wings contacts the fixed stopper (13) of the fuselage connection structure (1).

7. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: The basic wing surface (22) structure comprises a main wing surface and a metal wing tip, which are connected by a sleeve fit; the main wing surface comprises a core and a shell (221) wrapped around the core, the core comprises a carbon tube beam (222), a filling material and a foam core (223), the inner root of the carbon tube beam (222) is inserted into the wing root joint and fixedly connected, the carbon tube beam (222) is filled with the filling material, and there are two foam cores (223) arranged on both sides of the carbon tube beam (222); the inner surface of the shell (221) is adapted to the outer surface of the wing root joint, and the two are connected by a sleeve fit; the metal wing tip comprises an end plate and a connection block, the connection block is sleeved in the shell (221), and the end plate and the connection block are connected by fasteners or integral machining.

8. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: The flexible hinge piece (224) is a Kevlar fiber cloth of a certain thickness, and the front and rear parts of the flexible hinge piece (224) are respectively connected to the inside of the trailing edge of the basic wing surface (22) and the inside of the leading edge of the trailing edge control surface (23).

9. The stackable folding wing of a patrol drone with a trailing edge control surface according to claim 2, characterized in that: The flexible hinge piece (224) is made of Kevlar fiber cloth, and the front and rear parts of the flexible hinge piece (224) are respectively connected to the inside of the trailing edge of the basic wing surface (22) and the inside of the leading edge of the trailing edge control surface (23).

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