A deformable wing applicable to medium- and high-speed flight with an elastic support self-locking function

Abstract

The present invention relates to a variable wing with an elastic support self-locking function suitable for medium and high-speed flight; it includes a main wing, an extended wing, an extension mechanism, a fixed frame, an elastic support mechanism, a first locking mechanism and a second locking mechanism. The extended wing includes an upper wing plate and a lower wing plate, a leading edge skin, a trailing edge skin, a front wing edge fairing strip and a rear wing edge fairing strip. The front wing edge fairing strip is provided with a front guide groove, and the inner walls of the upper wing plate and the lower wing plate are provided with front guide strips. The rear wing edge fairing strip is provided with a rear guide groove, and the inner walls of the upper wing plate and the lower wing plate are provided with rear guide strips; the outer end of the front wing edge fairing strip is fixedly connected to the leading edge skin; the outer end of the rear wing edge fairing strip is fixedly connected to the trailing edge skin, and the front wing edge fairing strip and the rear wing edge fairing strip are movably connected to the upper wing plate and the lower wing plate; through the above structural design, it is to solve the problem that the existing wing edge is made of flexible materials and can only be suitable for low-speed flight. After exceeding 100 m / s, during the flight, the wing edge is prone to deformation and cannot meet the requirements of medium and high-speed flight.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft components, and particularly to a variable wing with an elastic support self-locking function suitable for medium and high-speed flight. Background Art

[0002] The wing is a main component of an aircraft during flight. Changing the wing shape during flight (such as wing sweep, changing the wingspan and camber, etc.) can effectively increase the efficiency of the wing. Among them, the effects of changing the wingspan and wing area are the most prominent. For example, an aircraft usually requires a wing with a high aspect ratio and a large wing area during cruise to provide more lift for the aircraft.

[0003] Currently, the common method to increase the aspect ratio is to increase the wingspan length. The common method to increase the wingspan length is to add extended wings to the main wing part, and the extended wings can be pushed out. However, after the extended wings are pushed out in the prior art, there will be a step between the extended wings and the main wing. The existence of the step will have an adverse impact on the aerodynamics of the aircraft. Secondly, the extended wings of the variable wing require a stable locking structure after being extended. The current locking structure is designed separately, which increases the complexity of the overall design. Moreover, the flexible wing surface of the variable wing does not have enough support structure, and the flexible wing edge will deform during use, which is not conducive to flight.

[0004] A variable wing with an elastic support self-locking function solves the problem of the step between the extended wings and the main wing through the design of the elastic support self-locking structure, the main wing and the extended wings. At the same time, the elastic support self-locking structure can lock the upper and lower ends of the extended wings, providing sufficient support for the flexible wing surface of the variable wing. However, during the test process, it is found that since the wing edge is made of a flexible material, it is only applicable to low-speed flight. After exceeding 100 m / s, during the flight process, the wing edge is prone to deformation and cannot meet the requirements of medium and high-speed flight.

[0005] Therefore, in view of the above problems, the present invention urgently needs to provide a variable wing with an elastic support self-locking function suitable for medium and high-speed flight. Summary of the Invention

[0006] The purpose of the present invention is to provide a variable wing with an elastic support self-locking function suitable for medium and high-speed flight. By designing the structure of the variable wing with an elastic support self-locking function suitable for medium and high-speed flight, the problems existing in the prior art are solved, that is, since the wing edge is made of a flexible material, it is only applicable to low-speed flight. After exceeding 100 m / s, during the flight process, the wing edge is prone to deformation and cannot meet the requirements of medium and high-speed flight.

[0007] A deformable wing applicable to medium and high-speed flight with an elastic support self-locking function provided by the present invention includes a main wing and a protruding wing. The protruding wing is inserted into the main wing. An extending mechanism is fixed in the inner cavity of the main wing. A fixing frame is arranged in the inner cavity of the protruding wing. Elastic support mechanisms for supporting the upper and lower end faces of the protruding wing are installed at intervals along the length on the fixing frame. The elastic support mechanisms are detachably connected to the protruding wing, and the fixing frame is detachably connected to the extending mechanism. One end of the fixing frame extends outside the protruding wing, and a front support seat is installed at the end of the fixing frame extending outside the protruding wing. A main wing inner support frame that can move horizontally inside the main wing is fixedly sleeved outside the front support seat. First locking mechanisms and second locking mechanisms corresponding to each elastic support mechanism are also installed on the fixing frame. One end of the first locking mechanism is connected to a pull rope for pulling the first locking mechanism out of the elastic support mechanism, and one end of the pull rope is fixedly connected to the main wing. Among them, when the protruding wing is not extended, the first locking mechanism is used to lock the elastic support mechanism to ensure that the elastic support mechanism is in a compressed state. After the protruding wing is fully extended, the first locking mechanism disengages from the elastic support mechanism, and the second locking mechanism is used to lock the elastic support mechanism to prevent the elastic support mechanism from rebounding.

[0008] The inner edge of one end of the main wing adjacent to the protruding wing is circumferentially provided with a main wing inner lining plate, and the inner wall of one end of the protruding wing adjacent to the main wing is circumferentially provided with a protruding wing inner lining plate. One end of the protruding wing inner lining plate extends outside the protruding wing and abuts against the side end face of the main wing inner support frame. The protruding wing inner lining plate includes a lining section located inside the protruding wing and an outer edge section located outside the protruding wing. A step is provided at the connection between the outer edge section and the lining section. After the protruding wing extends, the lower end face of the main wing inner lining plate is closely attached to the upper end face of the outer edge section, and the side end face of the main wing inner support frame is attached to the side end face of the main wing inner lining plate. The thickness of the main wing inner lining plate is equal to the height of the step, and the thickness of the main wing is equal to the thickness of the protruding wing. The protruding wing includes an upper wing plate and a lower wing plate, a leading edge skin connecting the leading edges of the upper wing plate and the lower wing plate, and a trailing edge skin connecting the trailing edges of the upper wing plate and the lower wing plate. It also includes a leading edge profile protection strip located inside the protruding wing for strengthening the leading edge of the protruding wing and a trailing edge profile protection strip for strengthening the trailing edge. A plurality of front guide grooves are arranged at intervals along the length on the upper and lower surfaces of the leading edge profile protection strip, and front guide strips corresponding to each front guide groove are provided on the inner walls of the upper wing plate and the lower wing plate. A plurality of rear guide grooves are arranged at intervals along the length on the upper and lower surfaces of the trailing edge profile protection strip, and rear guide strips corresponding to each rear guide groove are provided on the inner walls of the upper wing plate and the lower wing plate. The outer end of the leading edge profile protection strip is fixedly connected to the leading edge skin; the outer end of the trailing edge profile protection strip is fixedly connected to the trailing edge skin, and the leading edge profile protection strip and the trailing edge profile protection strip are movably connected to the upper wing plate and the lower wing plate.

[0009] Preferably, it includes two fixing frames arranged at intervals. The two fixing frames are connected by a connecting rod, and the extending mechanism is detachably connected to the connecting rod; the main wing inner support frame is fixedly connected to the front support seat by screws; one end of the extending mechanism is fixed inside the main wing through a mounting seat.

[0010] Preferably, the mounting base includes a lower module and an upper module, a fixing groove is provided at the top of the lower module, the fixing groove is connected to the side wall of the lower module on two opposite sides, a fixing hole is provided at the bottom of the fixing groove, and a fixing through hole corresponding to the fixing hole is provided on the upper module, and the positioning pin is inserted into the fixing hole from the fixing through hole.

[0011] Preferably, rear support seats for supporting the rear end of the main wing are provided on both sides of the mounting seat; and a plurality of weight-reducing holes are provided at intervals along the length of the long plate.

[0012] Preferably, the elastic support mechanism includes a lower support plate and an upper support plate, the lower support plate is provided with a lower sleeve extending upward, the upper support plate is provided with an upper sleeve extending into the lower sleeve, the inner wall of the lower sleeve is circumferentially provided with a stop protrusion, the stop protrusion is tightly fitted with the outer wall of the upper sleeve, the outer wall of one end of the upper sleeve extending into the lower sleeve is circumferentially provided with a flange, the outer end surface of the flange is tightly fitted with the inner wall of the lower sleeve; a first compression spring is installed in the lower sleeve, and the top of the first compression spring extends into the interior of the upper sleeve; the outer wall of the lower sleeve is provided with a first socket and a second socket connected to the interior of the lower sleeve.

[0013] Preferably, a first slot corresponding to the first plug hole is provided on the side wall of the fixing frame, and a first through-hole is provided at the bottom of the first slot and passes through the first plug hole; the first locking mechanism includes a guide seat screwed with the first slot slot notch, the guide seat is provided with a guide hole connected to the inside of the first slot, and an unlocking rod is inserted in the guide hole, one end of the unlocking rod extends into the first slot and passes through the first through-hole, and the other end extends out of the guide seat, and a pressure plate is circumferentially provided on the outer wall of the unlocking rod located in the first slot, and a connecting hole is provided at one end of the unlocking rod located outside the guide seat, and a pull rope is passed through the connecting hole, and the other end of the pull rope is connected to the main wing of the deformable wing; a second compression spring sleeved on the unlocking rod is provided between the pressure plate and the guide seat; when the extended wing is not extended from the main wing, one end of the unlocking rod penetrates into the first plug hole from the first through-hole and is inserted into the lower sleeve, and the lower end surface of the unlocking rod in the lower sleeve abuts against the upper end surface of the flange; after the extended wing is fully extended from the main wing, one end of the unlocking rod is pulled out from the first plug hole into the first through-hole.

[0014] Preferably, second slots corresponding to the second plug hole are provided on the opposite side walls of the fixing frame, and a second through hole which passes through the second plug hole is provided at the bottom of the second slot; the second locking mechanism includes a limit seat screwed with the notch of the second slot, a limit groove is provided at one end of the limit seat located in the second slot, a limit plate which can slide in the second slot is provided in the second slot, a locking pin is provided at one end of the limit plate, one end of the locking pin is inserted into the second through hole, a third compression spring is provided in the limiting groove, and one end of the third compression spring abuts against the limit plate; when the extended wing has not extended from the main wing, one end of the locking pin abuts against the outer wall of the lower sleeve; after the extended wing is fully extended from the main wing, one end of the locking pin extends from the second plug hole into the lower sleeve, and the upper end surface of the locking pin overlaps with the flange.

[0015] Preferably, the fixing frame includes a long board, and a plurality of mounting grooves matching the outer wall of the lower sleeve are arranged at intervals along the length on one side of the long board; it further includes single pressing blocks corresponding to each mounting groove one by one. A docking groove matching the outer wall of the lower sleeve is provided on one side of the single pressing block, and the single pressing block is detachably connected to the long board.

[0016] Preferably, second slots are respectively provided oppositely on the single pressing block and the long board; the first slot is provided on the side wall of the long board.

[0017] Preferably, a drawstring perforation through which a drawstring passes is provided on the connecting rod.

[0018] Compared with the prior art, a variable wing with an elastic support self-locking function applicable to medium and high-speed flight provided by the present invention has the following improvements:

[0019] 1. The deformable wing with elastic support and self-locking function suitable for medium and high-speed flight provided by the present invention has an initial state in which the extended wing is inside the main wing, and the first locking mechanism locks the elastic support mechanism. The locking of the elastic support mechanism can ensure the relative stillness of the upper and lower wing surfaces of the extended wing, reduce the friction between the extended wing and the main wing, ensure the wing surface and ensure that the deformable wing is easier to push out; when it is necessary to unfold, the extension mechanism is started, and the extension mechanism pushes out the extended wing. During the extension process, since one end of the pull rope is fixedly connected to the main wing and the other end of the pull rope is connected to the first locking mechanism, the pull rope will The first locking mechanism is pulled out from the elastic supporting mechanism, and the elastic supporting mechanism is released. After the extended wing is fully pushed out, the first locking mechanism is completely disengaged, and the elastic supporting mechanism pops up and extends in the longitudinal direction to support the upper end surface and the lower end surface of the extended wing. Under the action of the elastic supporting mechanism, the upper end surface and the lower end surface of the extended wing will also move in the longitudinal direction, so that the upper end surface and the lower end surface of the extended wing are flush with the upper end surface and the lower end surface of the main wing. The second locking mechanism locks the elastic supporting mechanism, and the elastic supporting mechanism is locked in the longitudinal direction without rebounding, and then the extended wing inner lining plate and the inner lining section are used to lock the extended wing. , the outer edge section and the inner support frame of the main wing limit each other. When the extended wing is fully extended, there is no step at the connection between the extended wing and the main wing, and the outer end surface of the extended wing is flush with the outer end surface of the main wing, which solves the technical problem that the starting shape of the wing surface of the existing deformable wing with elastic support and self-locking function is not smooth and discontinuous after deformation; the extended wing and the main wing are locked together to form a rigid body, and the two do not have the conditions for axial or radial relative movement. The upper wing panel, lower wing panel, leading edge skin, trailing edge panel skin, front wing conformal strip and rear wing conformal strip of the deformable wing are designed separately for easy assembly; after assembly, When the wing is extended, the upper wing panel and the lower wing panel move upward and downward in the longitudinal direction respectively, driving the leading edge skin and the trailing edge panel skin to move toward the center in the transverse direction, driving the front flange conformal strip and the rear flange conformal strip to move toward the center respectively, the front guide groove and the front guide strip cooperate with each other, and the rear guide groove and the rear guide strip cooperate with each other to ensure the linearity of the movement of the front flange conformal strip and the rear flange conformal strip, thereby ensuring the stability of the shape of the flexible flange under working conditions and the overall rounded integration with the deformation; it is suitable for medium and high speed flight, with a flight speed of 100-270m / s, and the flange does not deform.

[0020] 2. The deformable wing with elastic support and self-locking function provided by the present invention is designed with a first locking mechanism and a second locking mechanism. The first locking mechanism ensures that the upper wing surface and the lower wing surface are relatively still before the extended wing is extended, sufficiently reducing the friction between the upper wing and the main wing, thereby protecting the wing surface and ensuring that the extended wing is easier to push out. The second locking mechanism ensures that after the extended wing is extended, the upper wing surface and the lower wing surface will not recover, thereby ensuring the stability of the extended wing.

[0021] 3. The deformable wing with elastic support and self-locking function provided by the present invention has an extended wing inner lining plate combined with a main wing inner support frame at one end of the extended wing to ensure the accuracy of guidance.

[0022] 4. The variable wing with elastic support and self-locking function provided by the present invention can meet the actuation requirements, has high integration, small size, light weight, simple structure, high working stability and high reliability. The invention has the characteristics of extremely low part manufacturing cost, excellent assembly processability and extremely low comprehensive cost. Description of the Drawings

[0023] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0024] Figure 1 It is a schematic structural diagram of the variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to the present invention (the extended wing is not shown);

[0025] Figure 2 It is a schematic structural diagram of the variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to the present invention (part of the extended wing is shown);

[0026] Figure 3 It is a schematic structural diagram of the variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to the present invention (the extended wing is fully shown);

[0027] Figure 4 It is a schematic structural diagram of the variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to the present invention (partial internal view);

[0028] Figure 5 It is a schematic structural diagram of the variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to the present invention (partial internal view);

[0029] Figure 6 It is a schematic structural diagram of the variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to the present invention (cross-sectional view, the extended wing does not extend);

[0030] Figure 7 It is Figure 6 The enlarged view at position E in

[0031] Figure 8 It is Figure 6 The enlarged view at position F in

[0032] Figure 9Schematic structural diagram of the deformable wing with elastic support self-locking function applicable to medium and high-speed flight in the present invention (cross-sectional view, all extended wings extended);

[0033] Figure 10 is Figure 9 Enlarged view of part G;

[0034] Figure 11 Assembly drawing of the fixing frame, elastic support mechanism, first locking mechanism and second locking mechanism in the present invention (partial top view, extended wing not released);

[0035] Figure 12 is Figure 11 Sectional view B-B of;

[0036] Figure 13 is Figure 11 Sectional view A-A of;

[0037] Figure 14 Assembly drawing of the fixing frame, elastic support mechanism, first locking mechanism and second locking mechanism in the present invention (partial top view, extended wing fully released);

[0038] Figure 15 is Figure 14 Sectional view C-C of;

[0039] Figure 16 is Figure 14 Sectional view D-D of;

[0040] Figure 17 Schematic structural diagram of the fixing frame in the present invention (partial view);

[0041] Figure 18 Schematic structural diagram of the fixing frame in the present invention (partial view);

[0042] Figure 19 Schematic diagram of the deformable wing with elastic support self-locking function applicable to medium and high-speed flight in the present invention (internal view);

[0043] Figure 20 Schematic structural diagram of the mounting seat in the present invention.

[0044] Explanation of reference numerals:

[0045] 1. Main wing; 2. Extended wing; 21. Upper wing plate; 22. Lower wing plate; 23. Leading edge skin; 24. Trailing edge plate skin; 3. Extension mechanism; 4. Fixed frame; 41. First slot; 411. First perforation; 42. Second slot; 43. Long plate; 44. Single pressure block; 421. Second perforation; 431. Weight reduction hole; 5. Elastic support mechanism; 51. Lower support plate; 52. Upper support plate; 53. Lower sleeve; 54. Upper sleeve; 55. Flange; 56. First compression spring; 57. First jack; 58. Second jack; 512. Stop projection; 6. First locking mechanism; 61. Guide seat; 611. Guide hole; 62. Unlock rod; 621. Pressure plate; 63. Second compression spring; 7. Second locking mechanism; 71. Limit seat; 72. Limit plate; 73. Lock pin; 74. Third compression spring; 711. Limit groove; 8. Main wing inner lining plate; 9. Extended wing inner lining plate; 91. Inner lining section; 92. Outer edge section; 10. Main wing inner support frame; 11. Front wing edge shaping strip; 111. Front guide groove; 12. Rear wing edge shaping strip; 121. Rear guide groove; 13. Front guide strip; 14. Rear guide strip; 15. Connecting rod; 16. Front support seat; 17. Mounting seat; 171. Lower module; 172. Upper module; 173. Positioning pin; 1711. Fixed groove; 1721. Fixed perforation; 18. Rear support seat. Detailed implementation mode

[0046] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0047] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0048] In the description of the present invention, it should be noted that, unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0049] Such as Figures 1 to 10As shown in the figure, a deformable wing with an elastic support self-locking function suitable for medium and high-speed flight provided in this embodiment includes a main wing 1 and an extended wing 2. The extended wing 2 is inserted into the main wing 1. An extension mechanism 3 is fixed in the inner cavity of the main wing 1. A fixing frame 4 is provided in the inner cavity of the extended wing 2. Elastic support mechanisms 5 for supporting the upper and lower end faces of the extended wing 2 are installed at intervals along the length on the fixing frame 4. The elastic support mechanisms 5 are detachably connected to the extended wing 2, and the fixing frame 4 is detachably connected to the extension mechanism 3. One end of the fixing frame 4 extends outside the extended wing 2. A front support seat 16 is installed at the end of the fixing frame 4 extending outside the extended wing 2. A main wing inner support frame 10 that can move horizontally inside the main wing 1 is fixedly sleeved outside the front support seat 16. First locking mechanisms 6 and second locking mechanisms 7 corresponding to each elastic support mechanism 5 are also installed on the fixing frame 4. One end of the first locking mechanism 6 is connected to a pull rope for pulling the first locking mechanism 6 out of the elastic support mechanism 5, and one end of the pull rope is fixedly connected to the main wing 1. Among them, when the extended wing 2 is not extended, the first locking mechanism 6 is used to lock the elastic support mechanism 5 to ensure that the elastic support mechanism 5 is in a compressed state. After the extended wing 2 is fully extended, the first locking mechanism 6 disengages from the elastic support mechanism 5, and the second locking mechanism 7 is used to lock the elastic support mechanism 5 to prevent the elastic support mechanism 5 from rebounding. The inner edge of one end of the main wing 1 adjacent to the extended wing 2 is circumferentially provided with a main wing inner lining plate 8. The inner wall of one end of the extended wing 2 adjacent to the main wing 1 is circumferentially provided with an extended wing inner lining plate 9. One end of the extended wing inner lining plate 9 extends outside the extended wing 2 and abuts against the side end face of the main wing inner support frame 10. The extended wing inner lining plate 9 includes a lining section 91 located inside the extended wing 2 and an outer edge section 92 located outside the extended wing 2. A step is provided at the connection between the outer edge section 92 and the lining section 91. After the extended wing 2 extends, the lower end face of the main wing inner lining plate 8 is closely attached to the upper end face of the outer edge section 92, and the side end face of the main wing inner support frame 10 is attached to the side end face of the main wing inner lining plate 8. The thickness of the main wing inner lining plate 8 is equal to the height of the step, and the thickness of the main wing 1 is equal to the thickness of the extended wing 2. The extended wing 2 includes an upper wing plate 21 and a lower wing plate 22, a leading edge skin 23 connecting the leading edges of the upper wing plate 21 and the lower wing plate 22, and a trailing edge skin 24 connecting the trailing edges of the upper wing plate 21 and the lower wing plate 22. It also includes a leading edge shape-preserving strip 11 located inside the extended wing 2 for strengthening the leading edge of the extended wing 2 and a trailing edge shape-preserving strip 12 for strengthening the trailing edge. A plurality of front guiding grooves 111 are arranged at intervals along the length on the upper and lower surfaces of the leading edge shape-preserving strip 11. Front guiding strips 13 corresponding to each front guiding groove 111 are provided on the inner walls of the upper wing plate 21 and the lower wing plate 22. A plurality of rear guiding grooves 121 are arranged at intervals along the length on the upper and lower surfaces of the trailing edge shape-preserving strip 12. Rear guiding strips 14 corresponding to each rear guiding groove 121 are provided on the inner walls of the upper wing plate 21 and the lower wing plate 22. The outer end of the leading edge shape-preserving strip 11 is fixedly connected to the leading edge skin 23. The outer end of the trailing edge shape-preserving strip 12 is fixedly connected to the trailing edge skin 24. The leading edge shape-preserving strip 11 and the trailing edge shape-preserving strip 12 are movably connected to the upper wing plate 21 and the lower wing plate 22.

[0050] The variable wing provided by the present invention has an initial state where the extended wing 2 is inside the main wing 1, and the first locking mechanism 6 locks the elastic support mechanism 5. At this time, the elastic support mechanism 5 will not exert longitudinal pressure on the upper and lower end faces of the variable wing. When deployment is required, the extension mechanism 3 is activated, and the extension mechanism 3 pushes out the extended wing 2. During the extension process, since one end of the pull rope is fixedly connected to the main wing 1 and the other end of the pull rope is connected to the first locking mechanism, the pull rope pulls the first locking mechanism 6 out of the elastic support mechanism 5, and the elastic support mechanism 5 is released. After the extended wing 2 is fully pushed out, the first locking mechanism 6 completely disengages, and the elastic support mechanism 5 pops out and extends longitudinally to support the upper and lower end faces of the extended wing 2. Since the extended wing 2 is made of a flexible material, under the action of the elastic support mechanism 5, the upper and lower end faces of the extended wing 2 are flush with the upper and lower end faces of the main wing. The second locking mechanism 7 locks the elastic support mechanism 5, and the elastic support mechanism 5 is locked longitudinally and does not rebound. Then, through the mutual limitation of the inner lining plate 9 of the extended wing, the inner lining section 91, the outer edge section 92, and the inner support frame 10 of the main wing, after the extended wing 2 is fully extended, there is no step at the connection between the extended wing 2 and the main wing, and the outer end face of the extended wing 2 is flush with the outer end face of the main wing 1, solving the technical problem that the surface of the existing variable wing is not smooth and continuous after deformation; the extended wing and the main wing are locked together to form a rigid body, and they do not have the conditions for relative axial or radial movement.

[0051] The upper wing plate 21, the lower wing plate 22, the leading edge skin 23, the trailing edge skin 24, the leading edge fairing strip 11, and the trailing edge fairing strip 12 of the present invention are designed separately, which is convenient for assembly; after assembly, during the extension process of the extended wing, the upper wing plate 21 and the lower wing plate 22 move upward and downward longitudinally respectively, driving the leading edge skin 23 and the trailing edge skin 24 to move towards the center direction transversely, and respectively driving the leading edge fairing strip 11 and the trailing edge fairing strip 12 to move towards the center direction. The front guiding groove 111 cooperates with the front guiding strip 13, and the rear guiding groove 121 cooperates with the rear guiding strip 14 to ensure the linear movement of the leading edge fairing strip 11 and the trailing edge fairing strip 12, thereby ensuring the morphological stability of the flexible wing edge under working conditions and integrating smoothly with the deformation as a whole. The design of the above structure is applicable to medium and high-speed flight, with a flight speed reaching 100 - 270 m / s, and the wing edge does not deform.

[0052] The first locking mechanism 6 of the present invention locks the elastic support mechanism 5. The elastic support mechanism 5 is in a compressed state. The pull rope pulls the first locking mechanism 6 out of the elastic support mechanism 5. The elastic support mechanism 5 is released, and the first locking mechanism 6 is completely disengaged. The elastic support mechanism 5 pops out and extends longitudinally. The second locking mechanism 7 locks the elastic support mechanism 5. The elastic support mechanism 5 is locked longitudinally and does not rebound. The above structural design can be used for the elastic support of the upper wing surface and the lower wing surface of the extended wing of the deformable wing, and can realize the longitudinal movement of the upper wing surface and the lower wing surface of the extended wing, so as to achieve the parallelism of the wing surface of the extended wing and the main wing surface after the extended wing extends, and no step is generated at the connection between the extended wing and the main wing, solving the technical problem that the outer shape of the wing surface is not smooth and continuous after the existing deformable wing is deformed; when the extended wing does not extend, the first locking mechanism 6 locks the elastic support mechanism 5. The locking of the elastic support mechanism 5 can ensure the relative static state of the upper wing surface and the lower wing surface of the extended wing, reduce the friction force between the extended wing and the main wing, and ensure the wing surface while ensuring that the deformable wing is easier to push out; after the extended wing is completely extended, the second locking mechanism 7 locks the elastic support mechanism 5. The elastic support mechanism 5 is locked longitudinally and does not rebound, ensuring the longitudinal fixation of the second locking mechanism 7, thereby realizing the longitudinal fixation of the upper wing surface and the lower wing surface of the extended wing.

[0053] The extension mechanism of the present invention is an electric push rod.

[0054] The inner lining plate of the extended wing of the present invention is designed in a split manner, including an upper inner lining plate of the extended wing and a lower inner lining plate of the extended wing. The upper inner lining plate of the extended wing is connected to the upper wing plate of the extended wing, and the lower inner lining plate of the extended wing is connected to the lower wing plate of the extended wing.

[0055] The inner lining plate 8 of the main wing of the present invention can be connected to the main wing 1 by adhesive bonding or can be prepared by a mold and integrally formed, and one of the above methods is selected according to needs.

[0056] As Figure 17 、 Figure 18 、 Figure 19 As shown, this embodiment includes two fixing frames 4 arranged at intervals. The two fixing frames 4 are connected by a connecting rod 15. The extension mechanism 3 is detachably connected to the connecting rod 15;

[0057] The inner support frame 10 of the main wing is fixedly connected to the front support seat 16 by screws;

[0058] One end of the extension mechanism 3 is fixed inside the main wing 1 through a mounting seat 17.

[0059] As Figure 20As shown in the figure, the mounting base 17 of this embodiment includes a lower module 171 and an upper module 172. A fixing groove 1711 is provided at the top end of the lower module 171. The two opposite sides of the fixing groove 1711 communicate with the side wall of the lower module 171. A fixing hole is provided at the bottom of the fixing groove 1711. A fixing through hole 1721 corresponding to the fixing hole is provided on the upper module 172. The positioning pin 173 penetrates from the fixing through hole 1721 into the fixing hole. Through the design of the above structure, the connection between the extending mechanism 3 and the mounting base 17 and the connection between the mounting base 17 and the main wing 1 are facilitated. Through the design of the above structure, the connection between the extending mechanism 3 and the mounting base 17 and the connection between the mounting base 17 and the main wing 1 are facilitated.

[0060] As Figure 19 shown, rear support seats 18 for supporting the rear end of the main wing 1 are provided on both sides of the mounting base 17; screw holes are provided on the upper and lower end faces of the rear support seats 18. Through bolts, the rear support seats 18 are fixedly connected to the main wing to realize the support of the rear end of the main wing and ensure the flatness of the main wing surface.

[0061] A plurality of weight reduction holes 431 are arranged at intervals along the length of the long board 43 in this embodiment, without excessively increasing the weight of the deformable wing.

[0062] As Figure 11 、 Figure 12 、 Figure 13 、 Figure 14 、 Figure 15 、 Figure 16As shown in the figure, on the opposite side walls of the fixing bracket 4 of this embodiment, there are second slots 42 corresponding to the second jacks 58. At the bottom of the second slot 42, there is a second through hole 421 communicating with the second jack 58. The second locking mechanism 7 includes a limit seat 71 screwed to the notch of the second slot 42. At one end of the limit seat 71 located in the second slot 42, there is a limit groove 711. In the second slot 42, there is a limit plate 72 that can slide in the second slot 42. At one end of the limit plate 72, there is a locking pin 73. One end of the locking pin 73 penetrates into the second through hole 421. In the limit groove 711, there is a third compression spring 74. One end of the third compression spring 74 abuts against the limit plate 72. When the extending wing does not extend from the main wing, one end of the locking pin 73 abuts against the outer wall of the lower sleeve 53. After the extending wing completely extends from the main wing, one end of the locking pin 73 extends from the second jack 58 into the lower sleeve 53, and the upper end surface of the locking pin 73 overlaps with the flanging 55. Through the above structural design, after the extending wing 2 completely extends, the elastic support mechanism 5 can be locked and fixed, that is, the lower support plate 51 and the upper support plate 52 will not rebound and will not return to their original state, ensuring the stability of the wing surface after deformation. That is, after the extending wing 2 completely extends, the second jack 58 communicates with the second through hole 421. Under the action of the third compression spring 74, the limit plate 72 moves towards the second jack 58. The locking pin 73 sequentially penetrates from the second through hole 421 and the second jack 58 into the lower sleeve 53, and the upper end surface of the locking pin 73 overlaps with the flanging 55, restricting the longitudinal movement of the upper sleeve 54. The cooperation of the limit plate 72, the third compression spring 74 and the limit seat 71 restricts the lateral movement of the locking pin 73, thereby realizing the locking and fixing of the elastic support mechanism 5.

[0063] On the upper end surface and the lower end surface of the elastic support mechanism 5 of this embodiment, there are respectively screw holes for connecting with the upper end surface and the lower end surface of the extending wing.

[0064] The fixing bracket 4 of this embodiment includes a long plate 43. On one side of the long plate 43, a plurality of installation grooves matching the outer wall of the lower sleeve 53 are arranged at intervals along the length. It also includes single pressure blocks 44 corresponding to each installation groove one by one. On one side of the single pressure block 44, there is a docking groove matching the outer wall of the lower sleeve 53. The single pressure block 44 is detachably connected to the long plate 43. The second slots 42 are respectively and oppositely arranged on the single pressure block 44 and the long plate 43. The first slot 41 is arranged on the side wall of the long plate 43. Through the design of the above structure, the installation and fixation of the elastic support mechanism 5 are convenient.

[0065] In some specific embodiments, three elastic support mechanisms 5 are installed on the long plate 43 at intervals, and they can also be arranged at intervals according to the length of the extending wing 2.

[0066] The second slots 42 are respectively and oppositely arranged on the single pressure block 44 and the long plate 43 of this embodiment. The first slot 41 is arranged on the side wall of the long plate 43.

[0067] The main wing 1 of the present invention is prepared from composite materials, and the upper wing plate, lower wing plate, front flange profile strip 11 and rear flange profile strip 12 of the extending wing 2 are prepared from composite materials.

[0068] A drawstring perforation 151 through which a drawstring passes is provided on the connecting rod 15 of the present invention, and the drawstring can pass through the drawstring perforation 151 and be fixedly connected to the rear support seat 18 inside the main wing 1.

[0069] The assembly process of the variable wing in this embodiment is as follows:

[0070] 1) Assemble the fixing frame 4, elastic support self-locking mechanism 5, first locking mechanism 6, second locking mechanism 7, extending mechanism 3, mounting seat 17, drawstring and front support seat 16 as Figure 1 shown. One end of the extending mechanism 3 is fixedly connected to the fixing frame 4 through a mounting plate, the first locking mechanism 6 locks the elastic support self-locking mechanism 5, and the drawstring passes through the drawstring perforation 151;

[0071] 2) Assemble the extending wing 2. The upper wing plate of the extending wing and the upper extending wing inner lining plate are assembled into an upper wing plate assembly, the lower wing plate of the extending wing and the lower extending wing inner lining plate are assembled into a lower wing plate assembly, and then the upper wing plate assembly, lower wing plate assembly, front flange skin, rear flange skin, front flange profile strip, rear flange profile strip, and main wing inner support frame are assembled. Install the fixing frame assembled in step 1 inside the extending wing 2, and the elastic support self-locking mechanism 5 is detachably connected to the extending wing through bolts;

[0072] 3) Install the main wing 1 inner lining plate inside the main wing, assemble the extending wing assembled in step 2 with the main wing, put the main wing inner support frame 10 outside the front support seat 16 and fix it with bolts; connect the extending mechanism 3 to the main wing 1 through the mounting seat 17 and bolts;

[0073] 4) Fix the rear support seat 18 inside the main wing 1 with bolts, fix the drawstrings on both sides to the corresponding rear support seats 18 respectively, and the two rear support seats 18 are arranged on both sides of the mounting seat 17.

[0074] The process of the variable wing extending:

[0075] 1) Start the extending mechanism 3, and the extending mechanism 3 pushes the fixing frame 4 to extend towards the outer end of the main wing 1.

[0076] 2) When the fixing frame 4 moves outward, it drives the elastic support self-locking mechanism 5 to move outward, and then drives the extended wing 2 to extend outward. Immediately before it is fully extended, the pull rope pulls the first locking mechanism 6 to release the elastic support self-locking mechanism 5. Under the action of the first spring, the upper wing plate and the lower wing plate of the extended wing 2 move upward and downward respectively. After the extended wing is fully extended, the second locking mechanism 7 will lock the extended wing to ensure the positioning of the upper wing plate and the lower wing plate of the extended wing. Under the combined action of the main wing inner lining plate 8, the extended wing inner lining plate 9, and the main wing inner support frame 10, the movement of the extended wing 2 in the length direction is restricted. Considering that the airfoil has a non-circular cross-section, its axial rotation is restricted.

[0077] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A deformable wing applicable to medium and high-speed flight with an elastic support self-locking function, characterized in that: It includes a main wing (1) and a protruding wing (2). The protruding wing (2) is inserted into the main wing (1). An extending mechanism (3) is fixed in the inner cavity of the main wing (1). A fixing frame (4) is arranged in the inner cavity of the protruding wing (2). Elastic support mechanisms (5) for supporting the upper and lower end faces of the protruding wing (2) are installed at intervals along the length on the fixing frame (4). The elastic support mechanisms (5) are detachably connected to the protruding wing (2). The fixing frame (4) is detachably connected to the extending mechanism (3). One end of the fixing frame (4) extends outside the protruding wing (2). A front support seat (16) is installed at one end of the fixing frame (4) extending outside the protruding wing (2). A main-wing inner support frame (10) that can move horizontally inside the main wing (1) is fixedly sleeved outside the front support seat (16). First locking mechanisms (6) and second locking mechanisms (7) corresponding to each elastic support mechanism (5) are also installed on the fixing frame (4). One end of the first locking mechanism (6) is connected to a pull rope for pulling the first locking mechanism (6) out of the elastic support mechanism (5). One end of the pull rope is fixedly connected to the main wing (1); wherein, when the protruding wing (2) is not extended, the first locking mechanism (6) is used to lock the elastic support mechanism (5) to ensure that the elastic support mechanism (5) is in a compressed state. After the protruding wing (2) is fully extended, the first locking mechanism (6) disengages from the elastic support mechanism (5), and the second locking mechanism (7) is used to lock the elastic support mechanism (5) to prevent the elastic support mechanism (5) from rebounding; A main-wing inner lining plate (8) is circumferentially arranged on the inner edge of one end of the main wing (1) adjacent to the protruding wing (2). A protruding-wing inner lining plate (9) is circumferentially arranged on the inner wall of one end of the protruding wing (2) adjacent to the main wing (1). One end of the protruding-wing inner lining plate (9) extends outside the protruding wing (2) and abuts against the side end face of the main-wing inner support frame (10). The protruding-wing inner lining plate (9) includes a lining section (91) located inside the protruding wing (2) and an outer edge section (92) located outside the protruding wing (2). A step is arranged at the connection between the outer edge section (92) and the lining section (91). After the protruding wing (2) extends, the lower end face of the main-wing inner lining plate (8) is closely attached to the upper end face of the outer edge section (92), and the side end face of the main-wing inner support frame (10) is attached to the side end face of the main-wing inner lining plate (8). The thickness of the main-wing inner lining plate (8) is equal to the height of the step, and the thickness of the main wing (1) is equal to the thickness of the protruding wing (2); The extended wing (2) includes an upper wing panel (21) and a lower wing panel (22), a leading edge skin (23) connecting the leading edges of the upper wing panel (21) and the lower wing panel (22), and a trailing edge skin (24) connecting the trailing edges of the upper wing panel (21) and the lower wing panel (22); it also includes a leading edge fairing strip (11) located inside the extended wing (2) for strengthening the leading edge of the extended wing (2) and a trailing edge fairing strip (12) for strengthening the trailing edge. A plurality of front guide grooves (111) are arranged at intervals along the length on the upper and lower surfaces of the leading edge fairing strip (11), and front guide strips (13) corresponding to each of the front guide grooves (111) are provided on the inner walls of the upper wing panel (21) and the lower wing panel (22). A plurality of rear guide grooves (121) are arranged at intervals along the length on the upper and lower surfaces of the trailing edge fairing strip (12), and rear guide strips (14) corresponding to each of the rear guide grooves (121) are provided on the inner walls of the upper wing panel (21) and the lower wing panel (22); the outer end of the leading edge fairing strip (11) is fixedly connected to the leading edge skin (23); the outer end of the trailing edge fairing strip (12) is fixedly connected to the trailing edge skin (24), and the leading edge fairing strip (11) and the trailing edge fairing strip (12) are movably connected to the upper wing panel (21) and the lower wing panel (22).

2. The deformable wing with elastic support self-locking function applicable to medium and high-speed flight according to claim 1, wherein: It includes two fixed frames (4) arranged at intervals, the two fixed frames (4) are connected by a connecting rod (15), and the extending mechanism (3) is detachably connected to the connecting rod (15); The main wing inner support frame (10) is fixedly connected to the front support seat (16) by screws; One end of the extending mechanism (3) is fixed inside the main wing (1) through a mounting seat (17).

3. The variable wing with elastic support self-locking function applicable to medium and high-speed flight according to claim 2, characterized in that: The mounting seat (17) includes a lower module (171) and an upper module (172). A fixing groove (1711) is provided at the top of the lower module (171), and the opposite sides of the fixing groove (1711) communicate with the side wall of the lower module (171). A fixing hole is provided at the bottom of the fixing groove (1711), a fixing through hole (1721) corresponding to the fixing hole is provided on the upper module (172), and a positioning pin (173) penetrates from the fixing through hole (1721) into the fixing hole.

4. The deformable wing applicable to medium- and high-speed flight with an elastic support self-locking function according to claim 3, characterized in that: Rear support seats (18) for supporting the rear end of the main wing (1) are provided on both sides of the mounting seat (17); a plurality of weight reduction holes (431) are arranged at intervals along the length of the long plate (43).

5. The variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to claim 4, characterized in that: The elastic support mechanism (5) includes a lower support plate (51) and an upper support plate (52). An upwardly extending lower sleeve (53) is provided on the lower support plate (51), and an upper sleeve (54) extending into the interior of the lower sleeve (53) is provided on the upper support plate (52). A stop projection (512) is circumferentially provided on the inner wall of the lower sleeve (53), and the stop projection (512) is in close fit with the outer wall of the upper sleeve (54). A flange (55) is circumferentially provided on the outer wall of one end of the upper sleeve (54) extending into the lower sleeve (53), and the outer end face of the flange (55) is in close fit with the inner wall of the lower sleeve (53); A first compression spring (56) is installed inside the lower sleeve (53), and the top of the first compression spring (56) extends into the interior of the upper sleeve (54); The outer wall of the lower sleeve (53) is provided with a first jack (57) and a second jack (58) that communicate with its interior.

6. The deformable wing applicable to medium- and high-speed flight with an elastic support self-locking function according to claim 5, wherein: On the side wall of the fixing frame (4), there is a first slot (41) corresponding to the first jack (57). At the bottom of the first slot (41), there is a first through hole (411) that penetrates through the first jack (57). The first locking mechanism (6) includes a guide seat (61) screwed to the notch of the first slot (41). The guide seat (61) is provided with a guide hole (611) that communicates with the interior of the first slot (41). An unlocking rod (62) is inserted into the guide hole (611). One end of the unlocking rod (62) extends into the first slot (41) and passes through the first through hole (411), and the other end extends outside the guide seat (61). On the outer wall of the unlocking rod (62) located in the first slot (41), there is a pressing plate (621) circumferentially. At one end of the unlocking rod (62) located outside the guide seat (61), there is a connection hole, and a pull rope is inserted into the connection hole. The other end of the pull rope is connected to the main wing of the deformable wing. A second compression spring (63) sleeved on the unlocking rod (62) is provided between the pressing plate (621) and the guide seat (61). When the extending wing does not extend from the main wing, one end of the unlocking rod (62) extends from the first through hole (411) into the first jack (57) and is inserted into the lower sleeve (53). The lower end surface of the unlocking rod (62) located in the lower sleeve (53) abuts against the upper end surface of the flanging (55). After the extending wing completely extends from the main wing, one end of the unlocking rod (62) is pulled out from the first jack (57) into the first through hole (411).

7. The deformable wing applicable to medium- and high-speed flight with elastic support self-locking function according to claim 6, characterized in that: On the opposite side walls of the fixing frame (4), there are second slots (42) corresponding to the second jacks (58). At the bottom of the second slots (42), there are second through holes (421) that penetrate through the second jacks (58). The second locking mechanism (7) includes a limit seat (71) screwed to the notch of the second slot (42). One end of the limit seat (71) located in the second slot (42) is provided with a limit groove (711). A limit plate (72) that can slide in the second slot (42) is provided in the second slot (42). One end of the limit plate (72) is provided with a locking pin (73). One end of the locking pin (73) penetrates into the second through hole (421). A third compression spring (74) is provided in the limit groove (711), and one end of the third compression spring (74) abuts against the limit plate (72). When the extending wing does not extend from the main wing, one end of the locking pin (73) abuts against the outer wall of the lower sleeve (53). After the extending wing completely extends from the main wing, one end of the locking pin (73) extends from the second jack (58) into the lower sleeve (53), and the upper end surface of the locking pin (73) overlaps with the flanging (55).

8. The variable wing applicable to medium- and high-speed flight and having an elastic support self-locking function according to claim 7, wherein: The fixing frame (4) includes a long plate (43). On one side of the long plate (43), a plurality of installation grooves matching the outer wall of the lower sleeve (53) are arranged at intervals along the length. It also includes single pressing blocks (44) corresponding to each installation groove one by one. One side of the single pressing block (44) is provided with a docking groove matching the outer wall of the lower sleeve (53). The single pressing block (44) is detachably connected to the long plate (43).

9. The deformable wing with elastic support self-locking function applicable to medium and high-speed flight according to claim 8, characterized in that: The second slots (42) are respectively provided oppositely on the single pressing block (44) and the long board (43); the first slot (41) is provided on the side wall of the long board (43).

10. The variable wing with elastic support and self-locking function applicable to medium and high-speed flight according to claim 8, characterized in that: The connecting rod (15) is provided with a drawstring perforation (151) through which a drawstring passes.

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