Spanwise and chordwise double adaptive intelligent morphing wing and control method

Abstract

This invention relates to a spanwise and chordwise dual adaptive intelligent deformable wing and its control method. The deformable wings are respectively arranged on opposite sides of an aircraft body, and a control unit for controlling the deformable wings is disposed in the aircraft body. The deformable wing includes: a wing body connected to the aircraft body, and a first deformable device and a second deformable device disposed within the wing body; the first deformable device and the second deformable device are arranged sequentially along a direction away from the aircraft body; the first deformable device is used to change the chordwise shape of the leading and trailing edges of the wing body, and the second deformable device is used to change the spanwise shape of the wingtip of the wing body; the control unit is electrically connected to the first deformable device and the second deformable device respectively. This invention can achieve continuous deformation of the wing surface in both the spanwise and chordwise directions, and has the characteristics of large deformation range, light weight, and simple structure.

Description

Technical Field

[0001] This invention relates to the aerospace field, and more particularly to a spanwise and chordwise dual adaptive intelligent deformable wing and control method. Background Technology

[0002] Deformable wings are a key issue in the development of intelligent deformable aircraft technology and represent the most promising research direction for engineering applications. They can effectively improve aircraft flight performance or increase the flight envelope. Currently used deformable wings typically employ multi-segment wing structures, but their mechanical structures are bulky and difficult to achieve continuous deformation. Furthermore, most current research is limited to designing deformable structures for wing camber, airfoil, span, or leading and trailing edges individually, lacking an overall structural deformation scheme that allows deformation in both the spanwise and chordwise directions.

[0003] Shape memory alloys are a new type of smart material whose microstructure undergoes significant changes under external stimuli, thus exhibiting special properties such as shape memory effect and superelasticity, as well as a high power-to-weight ratio. Furthermore, they are simple to drive and easy to control. Therefore, shape memory alloys have been used in multi-segment wing structures to achieve continuous deformation. However, due to the structural limitations of multi-segment wing structures, it remains difficult to overcome their structural complexity and lack of deformability in both the spanwise and chordwise directions. For example, Chinese patent CN 113602476A discloses a continuous deformation structure and method for the trailing edge of a wing, comprising a wing, skin, trailing edge frame, and control circuitry. The beams, ribs, and stringers form the trailing edge frame, which is wrapped by the skin. Multiple ribs are arranged parallel to each other on the trailing edge frame, dividing each rib into multiple segments. The trailing edge frame is fixed to the trailing edge of the wing. The control circuitry is connected to a drive assembly located on each rib segment. The drive ropes and connection points in the drive assembly are made of NiTi shape memory alloy. It is evident that although it uses shape memory alloy to achieve continuous driving, its structure remains complex and the deformation direction is singular. Summary of the Invention

[0004] The purpose of this invention is to provide a spanwise and chordwise dual adaptive intelligent deformable wing and control method.

[0005] To achieve the above-mentioned objectives, the present invention provides a dual adaptive intelligent deformable wing in spanwise and chordwise directions. The deformable wings are respectively arranged on opposite sides of the aircraft body, and a control unit for controlling the deformable wings is provided in the aircraft body.

[0006] The deformable wing includes: a wing body connected to the main body of the aircraft, and a first deformable device and a second deformable device disposed within the wing body;

[0007] The first deformation device and the second deformation device are arranged sequentially along a direction away from the main body of the aircraft.

[0008] The first deformation device is used to change the chordal shape of the leading and trailing edges of the wing body, and the second deformation device is used to change the spanwise shape of the wingtip of the wing body; wherein, the chordal shape includes at least one of camber, size, and shape, and the spanwise shape includes at least one of deflection angle, size, and shape;

[0009] The control unit is electrically connected to the first deformation device and the second deformation device, respectively.

[0010] According to one aspect of the invention, a plurality of the first deformation devices are provided at intervals along the spanwise direction of the wing body.

[0011] According to one aspect of the invention, the first deformation device comprises: two symmetrical deformation units;

[0012] The two deformable units are respectively connected to the leading edge and trailing edge of the wing body;

[0013] The deformation unit includes: a first intermediate heat-insulating plate, a first upper deformation component located above the first intermediate heat-insulating plate, a first lower deformation component located below the first intermediate heat-insulating plate, and a first conductive member for transmitting the movement of the first upper deformation component and the first lower deformation component to the wing body.

[0014] The first upper deformable component and the first lower deformable component are electrically connected to the control unit, and the control unit is used to control the independent or joint extension and retraction of the first upper deformable component and the first lower deformable component.

[0015] According to one aspect of the invention, along the spanwise direction of the deformable wing, each of the deformable units has a plurality of first upper deformable components arranged side by side, and each of the deformable units has a plurality of first lower deformable components arranged side by side.

[0016] According to one aspect of the present invention, the first upper deformable component includes: a first upper temperature control and a first upper shape memory alloy wire;

[0017] The first upper shape memory alloy wire has a semi-ring structure;

[0018] The first upper temperature control is disposed on the inner side of the first upper shape memory alloy wire and distributed along the first upper shape memory alloy wire;

[0019] The first upper temperature control and the first upper shape memory alloy wire are electrically connected to the control unit, respectively;

[0020] The first lower deformation component includes: a first lower temperature control element and a first lower shape memory alloy wire;

[0021] The first lower shape memory alloy wire has a semi-ring structure;

[0022] The first lower temperature control is disposed inside the first lower shape memory alloy wire and distributed along the first lower shape memory alloy wire;

[0023] The first lower temperature control and the first lower shape memory alloy wire are electrically connected to the control unit.

[0024] According to one aspect of the invention, the first upper temperature control is configured to contact at least a portion of the first upper shape memory alloy wire;

[0025] The first lower temperature control is configured to contact at least a portion of the first lower shape memory alloy wire.

[0026] According to one aspect of the present invention, the second deformation device includes: a second intermediate heat-insulating plate, a second upper deformation assembly located above the second intermediate heat-insulating plate, a second lower deformation assembly located below the second intermediate heat-insulating plate, and a second conductive member for transmitting the movement of the second upper deformation assembly and the second lower deformation assembly to the wing body;

[0027] The second upper deformable component and the second lower deformable component are electrically connected to the control unit, and the control unit is used to control the independent or joint extension and retraction of the second upper deformable component and the second lower deformable component.

[0028] According to one aspect of the present invention, the second upper deformation component includes: a second upper temperature control and a second upper shape memory alloy wire;

[0029] The second upper shape memory alloy wire has a semi-ring structure;

[0030] The second upper temperature control is disposed on the inner side of the second upper shape memory alloy wire and distributed along the second upper shape memory alloy wire;

[0031] The second upper temperature control and the second upper shape memory alloy wire are electrically connected to the control unit, respectively;

[0032] The second lower deformation component includes: a second lower temperature control and a second lower shape memory alloy wire;

[0033] The second lower shape memory alloy wire has a semi-ring structure;

[0034] The second lower temperature control is disposed inside the second lower shape memory alloy wire and distributed along the second lower shape memory alloy wire;

[0035] The second lower temperature control and the second lower shape memory alloy wire are electrically connected to the control unit, respectively;

[0036] The second upper temperature control is configured to at least partially contact the second upper shape memory alloy wire;

[0037] The second lower temperature control is configured to at least partially contact the second lower shape memory alloy wire.

[0038] According to one aspect of the invention, the wing body comprises: a wing frame and a wing skin;

[0039] The wing frame is used to connect the first deformation device and the second deformation device.

[0040] The wing frame includes: a main support, support ribs spaced along the main support, and auxiliary supports supported on the support ribs and parallel to the main support.

[0041] The main support is a tubular structure, and multiple heat dissipation holes are provided along the axial direction of the main support.

[0042] The wing skin is used to cover the first deformation device, the second deformation device, and the wing frame; wherein the first conductive member and the second conductive member are respectively connected to the wing frame and the wing skin;

[0043] The wing skin is a flexible skin;

[0044] The first conductive element and the second conductive element are both flexible fillers.

[0045] To achieve the aforementioned objectives, this invention provides a control method for the aforementioned spanwise and chordwise dual adaptive intelligent deformable wing, comprising:

[0046] S1. Establish an electrical connection between the deformable wing and the control unit, wherein the first and second deformation devices in the deformable wing are respectively connected to the control unit; the control unit includes: a power supply and a control device;

[0047] S2. Develop a control scheme for the deformable wing according to the flight plan, and import the control scheme into the control device;

[0048] S3. The control device controls the power supply to the first deformation device and the second deformation device in the deformable wing based on the control scheme.

[0049] According to one aspect of the present invention, the present invention can realize continuous deformation of the spanwise and chordwise directions of the missile wing surface, and has the characteristics of large deformation range, light weight and simple structure, which has strong practical significance and good application prospects.

[0050] According to one aspect of the present invention, the present invention can be applied to rockets or missiles that require wing deformation, and with appropriate modifications, it can also be applied to the wings of many deformable aircraft, thus having a wide range of applications.

[0051] According to one aspect of the present invention, compared with existing deformable wing technology, the present invention can simultaneously achieve changes in spanwise and chordal wing shape, and has advantages such as rich functionality, continuous variation, and light weight.

[0052] According to one aspect of the present invention, the actuating components in the first deformation device and the second deformation device have the same structural composition and can be interchanged, which effectively improves the maintainability and maintenance efficiency of the entire mechanism.

[0053] According to one aspect of the present invention, the shape memory alloy wire is provided with a corresponding semiconductor cooling element. After the semiconductor cooling element is activated, it can greatly increase the extension and retraction speed of the shape memory alloy wire, thereby improving the mechanism's response speed. Furthermore, the upper and lower layers are separated by a heat insulation plate, which effectively reduces mutual interference caused by temperature differences between the upper and lower layers during operation, thus improving energy efficiency.

[0054] According to one aspect of the present invention, the wing frame components with large volume and mass have been designed to reduce weight, effectively reducing their structural mass.

[0055] According to one aspect of the present invention, the structure designed by the present invention is relatively simple, easy to install, and easy to prepare for and maintain before and after the test, and has the advantages of low use and maintenance costs. Attached Figure Description

[0056] Figure 1 This is a structural diagram of an aircraft according to one embodiment of the present invention;

[0057] Figure 2 This is a front view of an aircraft according to one embodiment of the present invention;

[0058] Figure 3 This is a structural diagram of the connection between the deformable projectile wing and the control unit according to one embodiment of the present invention;

[0059] Figure 4 This is a structural diagram of a deformable projectile wing according to one embodiment of the present invention;

[0060] Figure 5 This is a structural diagram of a first deformable device according to an embodiment of the present invention;

[0061] Figure 6 This is a structural diagram of a second deformable device according to an embodiment of the present invention. Detailed Implementation

[0062] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0063] In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" express orientations or positional relationships based on the orientations or positional relationships shown in the relevant drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as limitations on the present invention.

[0064] Combination Figure 1 , Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the present invention provides a spanwise and chordwise dual adaptive intelligent deformable wing, wherein deformable wings 2 are respectively arranged on opposite sides of the aircraft body 1, and a control unit 3 for controlling the deformable wings 2 is provided in the aircraft body 1; in addition, a power unit 4 and a tail fin 5 are provided at the tail end of the aircraft body 1, and the deformable wings 2 are arranged in front of the tail fin 5 to provide lift. In this embodiment, the deformable wings 2 include: a wing body 21 connected to the aircraft body 1, a first deformable device 22 and a second deformable device 23 disposed in the wing body 21; wherein the first deformable device 22 is respectively connected to the front and rear sides of the wing body 21 to realize the chordwise deformation of the wing body 21. In this embodiment, a first deformation device 22 and a second deformation device 23 are sequentially arranged along a direction away from the aircraft body 1. The first deformation device 22 is used to change the chordal shape of the leading and trailing edges of the wing body 21, and the second deformation device 23 is used to change the spanwise shape of the wingtip of the wing body 21. The chordal shape includes at least one of camber, size, and shape, and the spanwise shape includes at least one of deflection angle, size, and shape. In this embodiment, the control unit 3 is connected to both the first deformation device 22 and the second deformation device 23. Alternatively, in another embodiment, the control unit 3 may also be electrically connected to the power unit 4.

[0065] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, multiple first deformation devices 22 are arranged at intervals along the spanwise direction of the wing body 21. In this embodiment, the number of first deformation devices 22 is set according to the structural dimensions of the wing body 21. For example, two first deformation devices 22 are arranged side by side along the spanwise direction in the wing body 21. Of course, three, four, etc., can also be arranged. By setting multiple first deformation devices 22, a wide range of chordal shape control of the wing body 21 is achieved, effectively ensuring the overall deformation effect of the deformable wing 2. In addition, by setting multiple first deformation devices 22, the operation of each first deformation device 22 can be independently controlled to achieve flexible control of different positions of the deformable wing 2, which is more conducive to flexibly adjusting the shape of the deformable wing 2 at different positions, so that the deformable wing 2 has a better aerodynamic effect.

[0066] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the first deformation device 22 includes two symmetrical deformation units 22a; wherein the two deformation units 22a are respectively connected to the leading edge and the trailing edge of the wing body 21. By providing two deformation units 22a, the first deformation device 22 can control the deformation of the leading edge and the trailing edge of the wing body 21 respectively, thus more effectively ensuring the deformation effect of the present invention and improving the maneuverability of the aircraft.

[0067] Combination Figure 4 and Figure 5 As shown, in this embodiment, the deformation unit 22a includes: a first intermediate heat-insulating plate 221, a first upper deformation component 222 located above the first intermediate heat-insulating plate 221, a first lower deformation component 223 located below the first intermediate heat-insulating plate 221, and a first conductive member 224 for transmitting the movement of the first upper deformation component 222 and the first lower deformation component 223 to the wing body 21. In this embodiment, the first upper deformation component 222 and the first lower deformation component 223 are electrically connected to the control unit 3, and the control unit 3 is used to control the independent extension and retraction or joint extension and retraction of the first upper deformation component 222 and the first lower deformation component 223.

[0068] In this embodiment, the first upper deformable component 222 and the first lower deformable component 223 achieve their movement through extension and retraction. When the first conductor 224 transmits the movement of the first upper deformable component 222 and the first lower deformable component 223 to the wing body 21, the first conductor 224 needs to be connected to the first upper deformable component 222 and the first lower deformable component 223 so that it can generate corresponding deformation based on the extension and retraction of the first upper deformable component 222 and the first lower deformable component 223 to change the shape of the wing body 21. Therefore, in this embodiment, the first conductor 224 comprehensively transmits the movement generated by the first upper deformable component 222 and the first lower deformable component 223 by covering the first upper deformable component 222 and the first lower deformable component 223.

[0069] In this embodiment, the first conductive member 224 can be configured as a "U"-shaped structure, with its two free ends connected to the first upper deformable component 222 and the first lower deformable component 223, which are positioned vertically, respectively. That is, the two free ends of the first conductive member 224 cover the first upper deformable component 222 and the first lower deformable component 223, respectively. Accordingly, to ensure accurate control of the shape of the wing body 21, the outer surface of the first conductive member 224 needs to match the front or rear shape of the wing body 21 (as determined by the installation position). In this embodiment, since the first conductive member 224 is simultaneously connected to the first upper deformable component 222 and the first lower deformable component 223 at the upper and lower positions, the hollow position of the first conductive member 224 can be connected to or not connected to the first intermediate heat insulation plate 221. At the same time, the first intermediate heat insulation plate 221 can be made of a soft material, which can effectively avoid interference with the operation of the first upper deformable component 222, the first lower deformable component 223 and the first conductive member 224, which is beneficial to ensuring the accurate and stable operation of the present invention.

[0070] By configuring the first conductive member 224 to be connected simultaneously with the first upper deformable component 222 and the first lower deformable component 223, the combined action of the first upper deformable component 222 and the first lower deformable component 223 can be transmitted to the wing body 21 more accurately, making the shape control of the present invention more accurate.

[0071] In another embodiment, corresponding first conductive members 224 can be provided for the first upper deformable component 222 and the first lower deformable component 223 respectively. That is, there can be two first conductive members 224, one above the other. The upper first conductive member 224 is used to cover the first upper deformable component 222, and the lower first conductive member 224 is used to cover the first lower deformable component 223. At the same time, in order to achieve the support connection of the wing body 21, the outer surfaces of the two first conductive members 224 are matched with the shape of the corresponding wing body 21. In this embodiment, by independently setting the first conductive member 224 for the first upper deformation component 222 and the first lower deformation component 223, the corresponding actions can be transmitted to the wing body 21 through the corresponding first conductive member 224, so as to realize independent actions at different positions of the wing body 21. This simplifies the control action of the deformation of the wing body 21, reduces the control difficulty of the first upper deformation component 222 and the first lower deformation component 223, and reduces the structural complexity of the first conductive member 224. Correspondingly, the two first conductive members 224 and the first intermediate heat shield 221 can also be set independently, thereby avoiding interference from the first intermediate heat shield 221. The first intermediate heat shield 221 can be set to be soft to avoid affecting the deformation of the wing body 21. Furthermore, the first conductive element 224 and the first intermediate heat-insulating plate 221 can be connected as needed, which can also achieve the effect of combined action and simplify the function of the first conductive element 224. The first intermediate heat-insulating plate 221 also needs to be set as a soft plate to realize its function of combined transmission of the actions of the two first conductive elements 224.

[0072] It should be noted that since the first deformation device 22 uses two deformation units 22a to achieve separate control of the leading edge and trailing edge of the wing body 21, they all need to be connected to the wing body 21 through the first transmission member 224 to achieve the effect of motion transmission. Therefore, the setting form of the first transmission member 224 (such as the upper and lower integrated setting or the upper and lower independent setting) can be selected according to the difficulty and combination method of the actual action, which will not be elaborated here.

[0073] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, according to one embodiment of the present invention, along the spanwise direction of the deformable wing 2, each deformable unit 22a has a plurality of first upper deformable components 222 arranged side by side, and each deformable unit 22a has a plurality of first lower deformable components 223 arranged side by side. In this embodiment, a deformable unit 22a has two first upper deformable components 222 and two first lower deformable components 223 arranged side by side. The first upper deformable components 222 and the first lower deformable components 223 are separated vertically by a first intermediate heat-insulating plate 221 to isolate their mutual influence, which is beneficial to ensuring the accuracy of the operation of the present invention. By arranging a plurality of first upper deformable components 222 and a plurality of first lower deformable components 223 side by side on the upper and lower sides of each deformable unit 22a, the operation of the deformable unit 22a can be realized by the combination of deformable components 222 and 223, which makes the deformation operation more precise and accurate, and improves the accuracy and controllability of wing deformation.

[0074] In this embodiment, the first conductive member 224 can be connected to multiple first upper deformable components 222 and multiple first lower deformable components 223 simultaneously. Alternatively, the first conductive member 224 can be independently provided for each first upper deformable component 222 and each first lower deformable component 223. Of course, according to the actual deformation control requirements, the first upper deformable components 222 and the first lower deformable components 223 that need to be connected to the same first conductive member 224 can be selected in combination. For example, two first conductive members 224 can be provided, wherein two adjacent first upper deformable components 222 and the first lower deformable components 223 can be connected to the same first conductive member 224. The side deformation component 222 is connected to the same first conductor 224, and two adjacent first lower side deformation components 223 are connected to another first conductor 224; or, for example, there are two first conductors 224, in which the first upper side deformation components 222 and the first lower side deformation components 223 that are opposite each other are connected to the same first conductor 224, and another set of first upper side deformation components 222 and the first lower side deformation components 223 that are opposite each other are connected to another first conductor 224. Of course, other connection methods can also be used, which will not be described in detail here.

[0075] By setting up multiple first upper deformation components 222 and multiple first lower deformation components 223 in each deformation unit 22a, the range of motion of each deformation unit 22a can be made wider. Furthermore, by controlling the actions of different first upper deformation components 222 and first lower deformation components 223, the action combinations between different components in the deformation unit 22a can be realized, thereby achieving more flexible control over the shape of the wing body 21.

[0076] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 Hehe Figure 5 As shown, according to one embodiment of the present invention, the first upper deformable component 222 includes: a first upper temperature control 2221 and a first upper shape memory alloy wire 2222. In this embodiment, the first upper shape memory alloy wire 2222 has a semi-ring structure, such as a rectangular semi-ring, a trapezoidal semi-ring, a combination of a rectangle and an arc, etc., which can be set as needed.

[0077] In this embodiment, the first upper temperature control 2221 is disposed inside the first upper shape memory alloy wire 2222 and distributed along the first upper shape memory alloy wire 2222. In this embodiment, the first upper temperature control 2221 and the first upper shape memory alloy wire 2222 are electrically connected to the control unit 3. In this embodiment, the first upper temperature control 2221 is a semiconductor cooling device.

[0078] With the above settings, by connecting the first upper shape memory alloy wire 2222 to the control unit 3, the control unit 3 can control the power supply of the first upper shape memory alloy wire 2222 to make its temperature rise and produce a retraction action. By energizing the first upper temperature control unit 2221 to cool down the first upper shape memory alloy wire 2222, it can produce an elongation action. Of course, when cooling the first upper shape memory alloy wire 2222, the power supply of the first upper shape memory alloy wire 2222 needs to be cut off.

[0079] In this embodiment, the first lower deformable component 223 includes a first lower temperature control element 2231 and a first lower shape memory alloy wire 2232. In this embodiment, the first lower shape memory alloy wire 2232 has a semi-ring structure; for example, a rectangular semi-ring, a trapezoidal semi-ring, or a combination of a rectangle and an arc, etc., which can be configured as needed. In this embodiment, the first lower temperature control element 2231 is disposed inside the first lower shape memory alloy wire 2232 and distributed along the first lower shape memory alloy wire 2232. In this embodiment, the first lower temperature control element 2231 and the first lower shape memory alloy wire 2232 are electrically connected to the control unit 3. In this embodiment, the first lower temperature control element 2231 is a semiconductor cooling device.

[0080] With the above settings, by connecting the first lower side memory alloy wire 2232 to the control unit 3, the control unit 3 can control the power supply of the first lower side memory alloy wire 2232 to make its temperature rise and produce a retraction action. By energizing the first lower side temperature control 2231 to cool down the first lower side memory alloy wire 2232, it can produce an elongation action. Of course, when cooling the first lower side memory alloy wire 2232, the power supply of the first lower side memory alloy wire 2232 needs to be cut off.

[0081] It should be noted that since the total deformation of the shape memory alloy wire is related to its total length, the length of the shape memory alloy wire should be increased accordingly according to the direction of deformation. For example, the first upper shape memory alloy wire 2222 and the first lower shape memory alloy wire 2232 should have a straight structure along the chord direction, such as a rectangle, and their length along the chord direction should be increased as much as possible to improve the deformation efficiency.

[0082] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the structures of the first upper deformable component 222 and the first lower deformable component 223 can be configured to be identical.

[0083] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, according to one embodiment of the present invention, the first upper temperature control 2221 is configured to contact at least a portion of the first upper shape memory alloy wire 2222. By making the first upper temperature control 2221 contact the first upper shape memory alloy wire 2222, the temperature of the first upper shape memory alloy wire 2222 can be effectively and quickly controlled, effectively improving the response speed of the present invention. In this embodiment, the first upper shape memory alloy wire 2222 is described as a combination of a rectangle and an arc, wherein the first upper shape memory alloy wire 2222 includes: a first spanning portion and two first chordal portions, wherein the first chordal portions are vertically arranged at both ends of the first spanning portion, and the first spanning portion and the first chordal portions are connected by an arc. In this embodiment, the first upper temperature control element 2221 is also arranged in a ring along the ring of the first upper shape memory alloy wire 2222. The first upper temperature control element 2221 can be configured as multiple independent temperature control structures, with intervals between adjacent temperature control structures. Each temperature control structure is slidably connected to the first upper shape memory alloy wire 2222, thus preventing interference from the expansion and contraction of the first upper shape memory alloy wire 2222 even when the first upper temperature control element 2221 is in contact with the first upper shape memory alloy wire 2222. In this embodiment, all multiple temperature control structures can be connected to the first chordal portion, or all can be connected to the first spanwise portion, or they can be respectively arranged on the first chordal portion and the first spanwise portion. In this embodiment, the contact point between the first upper temperature control element 2221 and the first upper shape memory alloy wire 2222 can be provided with a groove matching the surface of the first upper shape memory alloy wire 2222, thereby further increasing the contact area between the first upper temperature control element 2221 and the first upper shape memory alloy wire 2222, resulting in better temperature control. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thus producing different temperature control effects at different positions of the first upper shape memory alloy wire 2222, which is beneficial for suppressing non-chordal deformation and further improving control accuracy. Of course, when non-chordal deformation is required, it is not necessary to independently control the corresponding temperature control structure.

[0084] In another embodiment, the first upper temperature control unit 2221 can be configured as multiple independent temperature control structures, and is provided with a soft semi-annular support adapted to the first upper shape memory alloy wire 2222. Multiple temperature control structures are installed on the soft annular support at intervals. Contact is further achieved by the temperature control structures abutting against the first upper shape memory alloy wire 2222. Thus, when the first upper shape memory alloy wire 2222 contracts and elongates, the elastic deformation of the soft annular support maintains the contact between the temperature control structures and the first upper shape memory alloy wire 2222. In this embodiment, the contact position between the first upper temperature control unit 2221 and the first upper shape memory alloy wire 2222 can be provided with a groove matching the surface of the first upper shape memory alloy wire 2222, further increasing the contact area between the first upper temperature control unit 2221 and the first upper shape memory alloy wire 2222, thereby achieving a better temperature control effect. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby generating different temperature control effects at different positions of the first upper shape memory alloy wire 2222. This is beneficial for suppressing non-chordal deformation and further improving control accuracy. Of course, when non-chordal deformation is required, it is not necessary to independently control the corresponding temperature control structure.

[0085] In this embodiment, the first lower temperature control 2231 is configured to contact at least a portion of the first lower shape memory alloy wire 2232. By making the first lower temperature control 2231 contact the first lower shape memory alloy wire 2232, the temperature of the first lower shape memory alloy wire 2232 can be effectively and quickly controlled, effectively improving the response speed of the present invention. In this embodiment, the first lower shape memory alloy wire 2232 is described as a combination of a rectangle and an arc, wherein the first lower shape memory alloy wire 2232 includes: a second spanning portion and two second chordal portions, wherein the second chordal portions are perpendicularly arranged at both ends of the second spanning portion, and the second spanning portion and the second chordal portions are connected by an arc. In this embodiment, the first lower temperature control element 2231 is also arranged in a ring along the ring of the first lower shape memory alloy wire 2232. The first lower temperature control element 2231 can be configured as multiple independent temperature control structures, with adjacent temperature control structures spaced apart. Each temperature control structure is slidably connected to the first lower shape memory alloy wire 2232, thus preventing interference from the first lower temperature control element 2231 on the extension and retraction of the first lower shape memory alloy wire 2232 even when the first lower temperature control element 2231 is in contact with the first lower shape memory alloy wire 2232. In this embodiment, all multiple temperature control structures can be connected to the second chordal portion, or all can be connected to the second spanning portion, or they can be respectively arranged on the second chordal portion and the second spanning portion. In this embodiment, the contact point between the first lower temperature control element 2231 and the first lower shape memory alloy wire 2232 can be provided with a groove matching the surface of the first lower shape memory alloy wire 2232, thereby further increasing the contact area between the first lower temperature control element 2231 and the first lower shape memory alloy wire 2232, resulting in better temperature control. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby producing different temperature control effects at different positions of the first lower shape memory alloy wire 2232, which is beneficial for suppressing non-chordal deformation and further improving control accuracy. Of course, when non-chordal deformation is required, it is not necessary to independently control the corresponding temperature control structure.

[0086] In another embodiment, the first lower temperature control unit 2231 can be configured as multiple independent temperature control structures, and is provided with a soft semi-annular support adapted to the first lower shape memory alloy wire 2232. Multiple temperature control structures are installed on the soft annular support at intervals. Contact is further achieved by the temperature control structures abutting against the first lower shape memory alloy wire 2232. Thus, when the first lower shape memory alloy wire 2232 contracts and elongates, the elastic deformation of the soft annular support maintains the contact between the temperature control structures and the first lower shape memory alloy wire 2232. In this embodiment, the contact position between the first lower temperature control unit 2231 and the first lower shape memory alloy wire 2232 can be provided with a groove matching the surface of the first lower shape memory alloy wire 2232 to further increase the contact area between the first lower temperature control unit 2231 and the first lower shape memory alloy wire 2232, thereby achieving a better temperature control effect. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby generating different temperature control effects at different positions of the first lower shape memory alloy wire 2232. This is beneficial for suppressing non-chordal deformation and further improving control accuracy. Of course, when non-chordal deformation is required, it is not necessary to independently control the corresponding temperature control structures.

[0087] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6 As shown, according to one embodiment of the present invention, the second deformation device 23 includes: a second intermediate heat-insulating plate 231, a second upper deformation component 232 located on the upper side of the second intermediate heat-insulating plate 231, a second lower deformation component 233 located on the lower side of the second intermediate heat-insulating plate 231, and a second conductive member 234 for transmitting the movement of the second upper deformation component 232 and the second lower deformation component 233 to the wing body 21; in this embodiment, the second upper deformation component 232 and the second lower deformation component 233 are electrically connected to the control unit 3, and the control unit 3 is used to control the independent extension and retraction movement or the joint extension and retraction movement of the second upper deformation component 232 and the second lower deformation component 233.

[0088] In this embodiment, the second upper deformable component 232 and the second lower deformable component 233 achieve their movement through extension and retraction. When the second conductor 234 transmits the movement of the second upper deformable component 232 and the second lower deformable component 233 to the wing body 21, the second conductor 234 needs to be connected to the second upper deformable component 232 and the second lower deformable component 233 to generate corresponding deformations based on their extension and retraction, thereby changing the shape of the wing body 21. Therefore, in this embodiment, the second conductor 234 comprehensively transmits the movement generated by the second upper deformable component 232 and the second lower deformable component 233 by enclosing them within the conductor.

[0089] In this embodiment, the second conductive member 234 can be configured as a "U"-shaped structure, with its two free ends connected to the second upper deformable component 232 and the second lower deformable component 233 located at opposite positions. That is, the two free ends of the second conductive member 234 cover the second upper deformable component 232 and the second lower deformable component 233 respectively. Correspondingly, to ensure accurate control of the wing body 21's shape, the outer surface of the second conductive member 234 needs to match the spanwise end (i.e., wingtip) of the wing body 21. In this embodiment, since the second conductive member 234 is simultaneously connected to the second upper deformable component 232 and the second lower deformable component 233 located at opposite positions, the hollow portion of the second conductive member 234 can be connected to or not connected to the second intermediate heat-insulating plate 231 (e.g., spaced apart). Simultaneously, the second intermediate heat-insulating plate 231 can be made of a soft material, effectively avoiding interference with the operation of the second upper deformable component 232, the second lower deformable component 233, and the second conductive member 234, which is beneficial for ensuring the accurate and stable operation of the present invention.

[0090] By configuring the second conductor 234 to be connected simultaneously with the second upper deformable component 232 and the second lower deformable component 233, the combined action of the second upper deformable component 232 and the second lower deformable component 233 can be transmitted to the wing body 21 more accurately, making the shape control of the present invention more accurate.

[0091] In another embodiment, corresponding second conductive members 234 can be provided for the second upper deformable component 232 and the second lower deformable component 233 respectively. That is, there can be two second conductive members 234, one above the other. The upper second conductive member 234 is used to cover the second upper deformable component 232, and the lower second conductive member 234 is used to cover the second lower deformable component 233. At the same time, in order to achieve the support connection of the wing body 21, the outer surfaces of the two second conductive members 234 are matched with the shape of the corresponding wing body 21. In this embodiment, by independently setting the second conductive member 2344 for the second upper deformable component 232 and the second lower deformable component 233, the corresponding actions can be transmitted to the wing body 21 through the corresponding second conductive member 234, so as to realize independent actions at different positions of the wing body 21. This simplifies the control action of deforming the wing body 21, reduces the control difficulty of the second upper deformable component 232 and the second lower deformable component 233, and reduces the structural complexity of the second conductive member 234. Correspondingly, the two second conductive members 234 and the second intermediate heat shield 231 can also be set independently, thereby avoiding interference from the second intermediate heat shield 231. The second intermediate heat shield 231 can be set to be soft to avoid affecting the deformation of the wing body 21. Furthermore, the second conductive element 234 and the second intermediate heat-insulating plate 231 can be connected as needed to achieve the same combined action effect and simplify the function of the second conductive element 234. The second intermediate heat-insulating plate 231 also needs to be set as a soft plate to realize its function of combined conduction of the actions of the two second conductive elements 234.

[0092] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6 As shown, according to one embodiment of the present invention, the second upper deformable component 232 includes: a second upper temperature control 2321 and a second upper shape memory alloy wire 2322. In this embodiment, the second upper shape memory alloy wire 2322 has a semi-ring structure; for example, a rectangular semi-ring, a trapezoidal semi-ring, a combination of a rectangle and an arc, etc., which can be set as needed. In this embodiment, the second upper temperature control 2321 is disposed on the inner side of the second upper shape memory alloy wire 2322 and distributed along the second upper shape memory alloy wire 2322. In this embodiment, the second upper temperature control 2321 and the second upper shape memory alloy wire 2322 are electrically connected to the control unit 3 respectively. In this embodiment, the second upper temperature control 2321 is a semiconductor cooling element.

[0093] With the above configuration, by connecting the second upper shape memory alloy wire 2322 to the control unit 3, the control unit 3 can control the power supply of the second upper shape memory alloy wire 2322 to raise its temperature and cause it to retract. The second upper temperature control 2321 is powered on to cool down the second upper shape memory alloy wire 2322 and cause it to extend. Of course, when cooling the second upper shape memory alloy wire 2322, the power supply to the second upper shape memory alloy wire 2322 needs to be turned off.

[0094] In this embodiment, the second lower deformable component 233 includes a second lower temperature control 2331 and a second lower shape memory alloy wire 2332. In this embodiment, the second lower shape memory alloy wire 2332 has a semi-ring structure; for example, a rectangular semi-ring, a trapezoidal semi-ring, or a combination of a rectangle and an arc, etc., which can be configured as needed. In this embodiment, the second lower temperature control 2331 is disposed inside the second lower shape memory alloy wire 2332 and distributed along the second lower shape memory alloy wire 2332. In this embodiment, the second lower temperature control 2331 and the second lower shape memory alloy wire 2332 are electrically connected to the control unit 3. In this embodiment, the second lower temperature control 2331 uses a semiconductor cooling element.

[0095] With the above settings, by connecting the second lower side memory alloy wire 2332 to the control unit 3, the control unit 3 can control the power supply of the second lower side memory alloy wire 2332 to make its temperature rise and produce a retraction action. The second lower side temperature control 2331 is powered on to cool down the second lower side memory alloy wire 2332 and produce an elongation action. Of course, when cooling the second lower side memory alloy wire 2332, the power supply to the second lower side memory alloy wire 2332 needs to be turned off.

[0096] It should be noted that since the total deformation of the shape memory alloy wire is related to its total length, the length of the shape memory alloy wire should be extended accordingly according to the direction of deformation. For example, the second upper shape memory alloy wire 2322 and the second lower shape memory alloy wire 2332 should have a straight structure along the stretching direction, such as a rectangle, and their stretching length should be increased as much as possible to improve the deformation efficiency.

[0097] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6 As shown, according to one embodiment of the present invention, the structures of the second upper deformable component 232 and the second lower deformable component 233 can be configured to be identical.

[0098] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6 As shown, according to one embodiment of the present invention, the second upper temperature control 2321 is configured to contact at least a portion of the second upper shape memory alloy wire 2322. By making the second upper temperature control 2321 contact the second upper shape memory alloy wire 2322, the temperature of the second upper shape memory alloy wire 2322 can be effectively and quickly controlled, effectively improving the response speed of the present invention. In this embodiment, the second upper shape memory alloy wire 2322 is described as a combination of a rectangle and an arc, wherein the second upper shape memory alloy wire 2322 includes: a third chordal portion, two third spanning portions, and two arcuate portions, wherein the third spanning portions are vertically arranged at both ends of the third chordal portion, and the third spanning portions are connected to the third chordal portion by arcuate portions. In this embodiment, the second upper temperature control element 2321 is also arranged in a ring along the ring of the second upper shape memory alloy wire 2322. The second upper temperature control element 2321 can be configured as multiple independent temperature control structures, with intervals between adjacent temperature control structures. Each temperature control structure is slidably connected to the second upper shape memory alloy wire 2322, thus preventing interference from the second upper temperature control element 2321 on the extension and retraction of the second upper shape memory alloy wire 2322 even when the second upper temperature control element 2321 is in contact with the second upper shape memory alloy wire 2322. In this embodiment, all multiple temperature control structures can be connected to the third chordal portion, or all connected to the third spanning portion, or respectively disposed on the third chordal portion, the third spanning portion, and the arc portion. In this embodiment, the contact point between the second upper temperature control element 2321 and the second upper shape memory alloy wire 2322 can be provided with a groove matching the surface of the second upper shape memory alloy wire 2322, thereby further increasing the contact area between the second upper temperature control element 2321 and the second upper shape memory alloy wire 2322, resulting in better temperature control. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby producing different temperature control effects at different positions of the second upper shape memory alloy wire 2322, which is beneficial for suppressing non-stretching deformation and further improving control accuracy. Of course, when non-stretching deformation is required, it is not necessary to independently control the corresponding temperature control structure.

[0099] In another embodiment, the second upper temperature control unit 2321 can be configured as multiple independent temperature control structures, and is provided with a soft semi-annular support adapted to the second upper shape memory alloy wire 2322. Multiple temperature control structures are installed on the soft annular support at intervals. Contact is further achieved by the temperature control structures abutting against the second upper shape memory alloy wire 2322. Thus, when the second upper shape memory alloy wire 2322 contracts and elongates, the elastic deformation of the soft annular support maintains the contact between the temperature control structures and the second upper shape memory alloy wire 2322. In this embodiment, the contact position between the second upper temperature control unit 2321 and the second upper shape memory alloy wire 2322 can be provided with a groove matching the surface of the second upper shape memory alloy wire 2322, further increasing the contact area between the second upper temperature control unit 2321 and the second upper shape memory alloy wire 2322, thereby achieving a better temperature control effect. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby generating different temperature control effects at different positions of the second upper shape memory alloy wire 2322. This is beneficial for suppressing non-stretching deformation and further improving control accuracy. Of course, when non-stretching deformation is required, it is not necessary to independently control the corresponding temperature control structure.

[0100] In this embodiment, the second lower temperature control 2331 is configured to contact at least a portion of the second lower shape memory alloy wire 2332. By making the second lower temperature control 2331 contact the second lower shape memory alloy wire 2332, the temperature of the second lower shape memory alloy wire 2332 can be effectively and quickly controlled, effectively improving the response speed of the present invention. In this embodiment, the second lower shape memory alloy wire 2332 is described as a combination of a rectangle and an arc, wherein the second lower shape memory alloy wire 2332 includes: a fourth chordal portion, two fourth spanning portions, and two arc portions, wherein the fourth spanning portions are vertically arranged at both ends of the fourth chordal portion, and the fourth spanning portions are connected to the fourth chordal portion by the arc portions. In this embodiment, the second lower temperature control element 2331 is also arranged in a ring along the ring of the second lower shape memory alloy wire 2332. The second lower temperature control element 2331 can be configured as multiple independent temperature control structures, with intervals between adjacent temperature control structures. Each temperature control structure is slidably connected to the second lower shape memory alloy wire 2332, thus preventing interference from the second lower temperature control element 2331 on the extension and retraction of the second lower shape memory alloy wire 2332 even when the second lower temperature control element 2331 is in contact with the second lower shape memory alloy wire 2332. In this embodiment, all multiple temperature control structures can be connected to the fourth chordal portion, or all connected to the fourth spanning portion, or respectively disposed on the fourth chordal portion, the fourth spanning portion, and the arc portion. In this embodiment, the contact point between the second lower temperature control element 2331 and the second lower shape memory alloy wire 2332 can be provided with a groove matching the surface of the second lower shape memory alloy wire 2332, thereby further increasing the contact area between the second lower temperature control element 2331 and the second lower shape memory alloy wire 2332, resulting in better temperature control. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby producing different temperature control effects at different positions of the second lower shape memory alloy wire 2332, which is beneficial for suppressing non-stretching deformation and further improving control accuracy. Of course, when non-stretching deformation is required, it is not necessary to independently control the corresponding temperature control structure.

[0101] In another embodiment, the second lower temperature control unit 2331 can be configured as multiple independent temperature control structures, and is provided with a soft semi-annular support adapted to the second lower shape memory alloy wire 2332. Multiple temperature control structures are installed on the soft annular support at intervals. Contact is further achieved by the temperature control structures abutting against the second lower shape memory alloy wire 2332. Thus, when the second lower shape memory alloy wire 2332 contracts and elongates, the elastic deformation of the soft annular support maintains the contact between the temperature control structures and the second lower shape memory alloy wire 2332. In this embodiment, the contact position between the second lower temperature control unit 2331 and the second lower shape memory alloy wire 2332 can be provided with a groove matching the surface of the second lower shape memory alloy wire 2332 to further increase the contact area between the second lower temperature control unit 2331 and the second lower shape memory alloy wire 2332, thereby achieving a better temperature control effect. In this embodiment, multiple temperature control structures can be controlled individually or in combination, thereby generating different temperature control effects at different positions of the second lower side shape memory alloy wire 2332. This is beneficial for suppressing non-stretching deformation and further improving control accuracy. Of course, when non-stretching deformation is required, it is not necessary to independently control the corresponding temperature control structures.

[0102] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the wing body 21 includes: a wing frame 211 and a wing skin 212. In this embodiment, the wing frame 211 is used to connect the first deformation device 22 and the second deformation device 23. In this embodiment, the wing frame 211 includes: a main support 2111, support ribs 2112 spaced apart along the main support 2111, and an auxiliary support 2113 supported on the support ribs 2112 and parallel to the main support 2111; in this embodiment, the main support 2111 is a tubular structure and has a plurality of heat dissipation holes 2111a opened along the axial direction of the main support 2111; in this embodiment, the wing skin 212 is used to cover the first deformation device 22, the second deformation device 23 and the wing frame 211; wherein, the first conductive member 224 and the second conductive member 234 are respectively connected to the wing frame 211 and the wing skin 212.

[0103] In this embodiment, the wing frame 211 constitutes a frame structure. The main support 2111 can be supported by carbon fiber tubing, which not only offers high structural strength but also achieves weight reduction. Furthermore, the support ribs 2112 are made of aluminum alloy plates, and the auxiliary supports 2113 are made of aluminum alloy rods. The use of aluminum alloy for the support ribs 2112 and auxiliary supports 2113 also achieves the advantages of high structural strength and light weight. In this embodiment, to further reduce the weight of the wing frame 211, weight-reducing holes can be further provided on the support ribs 2112.

[0104] In this embodiment, the support ribs 2112 are installed on the main support 2111 in a sleeved manner at intervals. This arrangement not only ensures that the support ribs 2112 are reliably fixed, but also further reduces weight, which is more beneficial to the lightweighting of the wing frame 211.

[0105] In this embodiment, four auxiliary supports 2113 are provided, and they are spaced apart along the axial direction of the support rib 2112.

[0106] In this embodiment, the deformation unit 22a in the first deformation device 22 can be installed on the side of the main support 2111 through the first intermediate heat insulation plate 221. Correspondingly, one end of the first conductive member 224 is connected to the wing body 21, and the other end covers the first deformation device 22 and is connected to the end face of the support rib 2112, thereby achieving the function of fixing and supporting the wing skin 212.

[0107] In this embodiment, the second deformation device 23 is connected to the side of the support rib 2112 closest to the wingtip via the second intermediate heat insulation plate 231. Correspondingly, one end of the second conductive member 234 is connected to the wing body 21, and the other end covers the second deformation device 23 while being connected to the side of the support rib 2112, thereby achieving the function of fixing and supporting the wing skin 212.

[0108] In this embodiment, the first conductive member 224 and the second conductive member 234 may be integrated, or the first conductive member 224 and the second conductive member 234 may be connected by means of bonding or the like, or the first conductive member 224 and the second conductive member 234 may be set independently of each other.

[0109] In this embodiment, the combined support structure of the wing frame 211, the first conductive member 224 and the second conductive member 234 forms a cavity in the middle of the wing body 21. Furthermore, combined with the heat dissipation holes 2111a on the main support 2111, it is more conducive to the heat generated by the first deformation device 22 and the second deformation device 23 being transferred out, which is beneficial to the overall heat dissipation.

[0110] Combination Figure 1, Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the wing skin 212 is a flexible skin.

[0111] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the first conductive member 224 and the second conductive member 234 are flexible fillers. In this embodiment, the first conductive member 224 and the second conductive member 234 can be made of TPU flexible filler material, which is a polymer material with excellent high tensile strength, high tensile strength, toughness and aging resistance. Filling the interior of the wing skin 212 can greatly enhance the load-bearing capacity of the wing body 21 and improve the thermal insulation performance, while not affecting the deformation function of the wing body 21.

[0112] Combination Figure 1 , Figure 2 and Figure 3 As shown, according to one embodiment of the present invention, the control unit 3 includes a power supply 31 and a control device 32. In this embodiment, the control unit 3 is located inside the aircraft body 1. The power supply 31 primarily provides power to the control device 32 and the deformation of the shape memory alloy wires within the mechanism, achieving this function through power lines and signal lines. In this embodiment, the control device 32 includes sensors and a control computer, etc., and calculates corresponding control signals output to the power supply 31 based on signals input from the flight control program, thereby controlling the deformation of the first deformation device 22 and the second deformation device 23 in the deformable wing 2.

[0113] To further illustrate the working principle of this solution, it will be further explained in conjunction with the accompanying drawings.

[0114] The first deformation device 22 is used to change the chordal shape of the leading and trailing edges of the wing body 21, which is achieved by deformation units 22a arranged front and rear. Specifically, different electrical excitations can be applied to the upper and lower deformation components (i.e., the first upper deformation component 222 and the first lower deformation component 223) to cause different deformation amounts of the first upper shape memory alloy wire 2222 and the first lower shape memory alloy wire 2232, thereby achieving the deflection of the deformable wing 2. For example, if it is necessary to deflect the trailing edge of the deformable wing 2 downward to increase the camber, the control unit 3 can send a control signal to cool the first upper deformable component 222 in the upper layer of the deformable unit 22a of the trailing edge, while heating the first lower deformable component 223 in the lower layer of the deformable unit 22a of the trailing edge. At this time, the first lower deformable component 223 shortens under the action of temperature, while the first upper deformable component 222 remains unchanged or stretches. As a result, under the action of the first conductive member 224, the trailing edge of the wing skin 212 on the lower side is stretched and undergoes contraction deformation, so that the trailing edge of the deformable wing 2 as a whole exhibits a downward deflection state.

[0115] When the second deformation device 23 is used to change the spanwise shape of the wingtip of the wing body 21, it achieves its function by controlling the heating or cooling of the upper and lower second deformation components 232 and 233. For example, if it is necessary to deflect the wingtip upward to reduce drag, the upper second upper shape memory alloy wire 2322 can be heated to shorten it, and the lower second lower shape memory alloy wire 2332 can be cooled. Then the wingtip will deflect upward under the action of the second deformation device 23.

[0116] According to one embodiment of the present invention, a control method for a spanwise and chordwise dual adaptive intelligent deformable wing includes:

[0117] S1. Establish an electrical connection between the deformable wing 2 and the control unit 3, wherein the first deformation device 22 and the second deformation device 23 in the deformable wing 2 are respectively connected to the control unit 3; the control unit 3 includes a power supply 31 and a control device 32. In this embodiment, the power supply 31 and the control device 32 are installed in a suitable position inside the aircraft body 1, and the power lines or signal lines between the control device 32 and the power supply 31, between the power supply 31 and the shape memory alloy wires of each part (i.e., the first upper shape memory alloy wire 2222, the first lower shape memory alloy wire 2232, the second upper shape memory alloy wire 2322, and the second lower shape memory alloy wire 2332), and between the power supply 31 and the temperature control components of each part (i.e., the first upper temperature control component 2221, the first lower temperature control component 2231, the second upper temperature control component 2321, and the second lower temperature control component 2331) are connected in a reasonable manner.

[0118] Assembly and assembly of the deformable wing 2. First, the main support 2111 passes through the support rib 2112. Four auxiliary supports 2113 are then assembled with the support rib 2112, and the second intermediate heat-insulating plate 231 is fixed to the outer support rib 2112. The first intermediate heat-insulating plate 221 is then installed and connected to the corresponding position on the main support 2111, completing the wing frame 211 of the deformable wing 2. The first upper deformable assembly 222 and the first lower deformable assembly 223 are sequentially installed on the upper and lower sides of the first intermediate heat-insulating plate 221. Similarly, the second upper deformable assembly 232 and the second lower deformable assembly 233 are installed on the upper and lower sides of the second intermediate heat-insulating plate 231.

[0119] S2. Develop a control scheme for the deformable wing 2 based on the flight plan, and import the control scheme into the control device 32; In this embodiment, after the deformable wing 2 and the control unit 3 are assembled, the control scheme is designed and the control program is written based on the mission flight profile or test plan, and then imported into the control device 32.

[0120] S3. The control device 32 energizes and controls the first deformation device 22 and the second deformation device 23 in the deformable wing 2 based on the control scheme. In this embodiment, the attitude is changed on the ground using a hardware-in-the-loop simulation system or related devices to observe whether the deformable wing 2 produces the required deformation as expected. If there is an abnormality, the aforementioned steps need to be returned to find the problem. Furthermore, during actual flight, the control device 32 executes a predetermined flight program, and the deformable wing 2 will undergo deformations such as wing camber, span, and wingtip deflection according to the corresponding scheme. The test process records and related data are saved for subsequent processing and analysis. Furthermore, after the test is completed, the integrity of the entire device is evaluated to determine whether it is necessary to repair or replace some easily damaged structures and electronic components.

[0121] The above description is merely an example of a specific solution of the present invention. For any devices and structures not described in detail herein, it should be understood that they are implemented using common devices and methods already available in the art.

[0122] The above description is merely one embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the invention by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A dual adaptive intelligent deformable wing in both spanwise and chordwise directions, characterized in that, The deformable wings (2) are respectively provided on opposite sides of the aircraft body (1), and a control unit (3) for controlling the deformable wings (2) is provided in the aircraft body (1). The deformable wing (2) includes: a wing body (21) connected to the main body of the aircraft (1), a first deformable device (22) and a second deformable device (23) disposed in the wing body (21); Along a direction away from the main body (1) of the aircraft, the first deformation device (22) and the second deformation device (23) are arranged in sequence; The first deformation device (22) is used to change the chordal shape of the leading edge and trailing edge of the wing body (21), and the second deformation device (23) is used to change the spanwise shape of the wingtip of the wing body (21); wherein the chordal shape includes at least one of camber, size and shape, and the spanwise shape includes at least one of deflection angle, size and shape; The control unit (3) is electrically connected to the first deformation device (22) and the second deformation device (23) respectively; The first deformation device (22) includes: two symmetrical deformation units (22a); The two deformable units (22a) are respectively connected to the leading edge and trailing edge of the wing body (21); The deformation unit (22a) includes: a first intermediate heat-insulating plate (221), a first upper deformation component (222) located on the upper side of the first intermediate heat-insulating plate (221), a first lower deformation component (223) located on the lower side of the first intermediate heat-insulating plate (221), and a first conductive member (224) for transmitting the first upper deformation component (222) and the first lower deformation component (223) to the wing body (21). The first upper deformable component (222) includes: a first upper temperature control (2221) and a first upper shape memory alloy wire (2222); The first upper temperature control (2221) is distributed along the first upper shape memory alloy wire (2222); The first upper temperature control (2221) is configured as multiple independent temperature control structures, and there is a gap between adjacent temperature control structures; The position where the first upper temperature control (2221) contacts the first upper memory alloy wire (2222) is provided with a groove that matches the surface of the first upper memory alloy wire (2222); The first lower deformable component (223) includes: a first lower temperature control (2231) and a first lower shape memory alloy wire (2232); The first lower temperature control element (2231) is distributed along the first lower shape memory alloy wire (2232); The first lower temperature control (2231) is configured as multiple independent temperature control structures, and there is a gap between adjacent temperature control structures; The position where the first lower temperature control (2231) contacts the first lower memory alloy wire (2232) is provided with a groove that matches the surface of the first lower memory alloy wire (2232).

2. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 1, characterized in that, Along the span of the wing body (21), multiple first deformation devices (22) are provided at intervals.

3. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 2, characterized in that, The first upper deformable component (222) and the first lower deformable component (223) are electrically connected to the control unit (3), and the control unit (3) is used to control the independent or joint extension and retraction of the first upper deformable component (222) and the first lower deformable component (223).

4. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 3, characterized in that, Along the spanwise direction of the deformable wing (2), each of the deformable units (22a) has a plurality of first upper deformable components (222) arranged side by side, and each of the deformable units (22a) has a plurality of first lower deformable components (223) arranged side by side.

5. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 4, characterized in that, The first upper shape memory alloy wire (2222) has a semi-ring structure; The first upper temperature control (2221) is disposed inside the first upper shape memory alloy wire (2222); the first upper temperature control (2221) and the first upper shape memory alloy wire (2222) are electrically connected to the control unit (3); The first lower shape memory alloy wire (2232) has a semi-ring structure; The first lower temperature control (2231) is disposed inside the first lower shape memory alloy wire (2232); the first lower temperature control (2231) and the first lower shape memory alloy wire (2232) are electrically connected to the control unit (3).

6. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 5, characterized in that, The first upper temperature control (2221) is configured to contact at least a portion of the first upper shape memory alloy wire (2222); The first lower temperature control (2231) is configured to contact at least a portion of the first lower shape memory alloy wire (2232).

7. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 6, characterized in that, The second deformation device (23) includes: a second intermediate heat-insulating plate (231), a second upper deformation component (232) located on the upper side of the second intermediate heat-insulating plate (231), a second lower deformation component (233) located on the lower side of the second intermediate heat-insulating plate (231), and a second conductive member (234) for transmitting the movement of the second upper deformation component (232) and the second lower deformation component (233) to the wing body (21); The second upper deformable component (232) and the second lower deformable component (233) are electrically connected to the control unit (3), and the control unit (3) is used to control the independent or joint extension and retraction of the second upper deformable component (232) and the second lower deformable component (233).

8. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 7, characterized in that, The second upper deformable component (232) includes: a second upper temperature control (2321) and a second upper shape memory alloy wire (2322); The second upper shape memory alloy wire (2322) has a semi-ring structure; The second upper temperature control (2321) is disposed inside the second upper shape memory alloy wire (2322) and distributed along the second upper shape memory alloy wire (2322); The second upper temperature control (2321) and the second upper shape memory alloy wire (2322) are electrically connected to the control unit (3), respectively; The second lower deformable component (233) includes: a second lower temperature control (2331) and a second lower shape memory alloy wire (2332); The second lower shape memory alloy wire (2332) has a semi-ring structure; The second lower temperature control (2331) is disposed inside the second lower shape memory alloy wire (2332) and distributed along the second lower shape memory alloy wire (2332); The second lower temperature control (2331) and the second lower shape memory alloy wire (2332) are electrically connected to the control unit (3), respectively; The second upper temperature control (2321) is configured to at least partially contact the second upper shape memory alloy wire (2322); The second lower temperature control (2331) is configured to at least partially contact the second lower shape memory alloy wire (2332).

9. The spanwise and chordwise dual adaptive intelligent deformable wing according to claim 8, characterized in that, The main body of the wing (21) includes: wing frame (211) and wing skin (212); The wing frame (211) is used to connect the first deformation device (22) and the second deformation device (23). The wing frame (211) includes: a main support (2111), support ribs (2112) spaced apart along the main support (2111), and an auxiliary support (2113) supported on the support ribs (2112) and parallel to the main support (2111). The main support (2111) is a tubular structure, and multiple heat dissipation holes (2111a) are provided along the axial direction of the main support (2111). The wing skin (212) is used to cover the first deformation device (22), the second deformation device (23) and the wing frame (211); wherein the first conductive member (224) and the second conductive member (234) are respectively connected to the wing frame (211) and the wing skin (212); The wing skin (212) is a flexible skin; The first conductive element (224) and the second conductive element (234) are flexible fillers, respectively.

10. A control method for a dual adaptive intelligent deformable wing in both spanwise and chordwise directions as described in any one of claims 1 to 9, characterized in that, include: S1. Establish an electrical connection between the deformable wing (2) and the control unit (3), wherein the first deformation device (22) and the second deformation device (23) in the deformable wing (2) are respectively connected to the control unit (3); the control unit (3) includes: a power supply (31) and a control device (32). S2. Develop a control scheme for the deformable wing (2) based on the flight plan, and import the control scheme into the control device (32). S3. The control device (32) controls the first deformation device (22) and the second deformation device (23) in the deformable wing (2) to be powered on based on the control scheme.

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