Empennage device for adaptive adjustment of aerodynamic center of aircraft and aircraft

Abstract

The invention relates to an empennage device for adaptive adjustment of a pneumatic center of an aircraft and the aircraft, and the empennage device comprises a sliding support, an empennage and an empennage driver which are arranged on two sides of the sliding support, and a support driver and reset assembly which is connected with the sliding support; the empennage drive is connected with the empennage and used for adjusting the posture of the empennage; the support driving and resetting assembly is connected with the two opposite ends of the sliding support in the sliding direction of the sliding support. The support drive comprises a driver and a controller electrically connected with the driver. The resetting assembly comprises a restorer and a tension sensor connected with the restorer; and the controller is electrically connected with the tension sensor so as to control the sliding driving force of the driver to the sliding support based on an output signal of the tension sensor.

Description

Technical Field

[0001] The invention relates to the field of aerospace, and in particular to a tail device for adaptively adjusting the aerodynamic center of an aircraft and an aircraft. Background Art

[0002] During the flight of a rocket, the position of the combined force point of the aerodynamic force is dynamically changing, and its change is affected by many factors, such as attitude, Mach number, atmospheric conditions, etc. The change of the aerodynamic center will cause the static stability and dynamic stability of the rocket to change. If the position of the aerodynamic center does not match the position of the center of mass, it may cause the rocket to have unstable attitude changes during flight. In addition, fuel consumption will also cause the change of the center of mass, which will have an adverse effect on the stability of the rocket. In order to prevent the mismatch between the center of mass and the aerodynamic center, the traditional solution is to reasonably design the mass distribution of the rocket, so that the position of the center of mass is as forward as possible, and a certain degree of redundancy is retained, so that the aerodynamic center of the rocket can be ensured to be behind the center of mass at all stages of the flight, ensuring the stability of the rocket during flight. However, if the aerodynamic center is too far back, it will have an adverse effect on the maneuverability of the rocket.

[0003] In order to solve the above problems and take into account the stability and maneuverability of the rocket, this patent designs a rocket aerodynamic center adaptive intelligent adjustment device and control method based on thermo-deformed shape memory alloy wire, on the premise of fully studying the characteristics of shape memory alloy materials. It can realize the overall movement of the rocket tail and adaptively adjust the position of the aerodynamic center in real time. The structure has the characteristics of large deformation range, light weight, simple structure, etc., and has strong practical significance and good application prospects. The device is driven by thermo-deformed shape memory alloy wire, and the temperature of the alloy wire is controlled by electric current. A displacement feedback device is set up to control the axial position of the tail in real time according to demand. At the same time, since the four sets of tail devices are relatively independent, the device can also realize the independent axial displacement control of the rocket tail in four different positions according to needs, providing an additional control torque for the aircraft. Summary of the invention

[0004] The object of the present invention is to provide a tail device for adaptively adjusting the aerodynamic center of an aircraft and an aircraft.

[0005] To achieve the above-mentioned invention object, the present invention provides a tail device for adaptively adjusting the aerodynamic center of an aircraft, comprising: a sliding support, tails and tail drives arranged on both sides of the sliding support, and a support drive and reset assembly connected to the sliding support; The tail drive is connected to the tail to adjust the attitude of the tail; Along the sliding direction of the sliding support, the support driving and resetting components are respectively connected to opposite ends of the sliding support; The support drive comprises: a driver, a controller electrically connected to the driver; The reset assembly comprises: a resetter, and a tension sensor connected to the resetter; The controller is electrically connected to the tension sensor to control the magnitude of the sliding driving force of the driver on the sliding support based on the output signal of the tension sensor.

[0006] According to one aspect of the present invention, the actuator is a shape memory alloy wire.

[0007] According to one aspect of the present invention, the support drive further comprises: a first clamp, a second clamp, a pulley support and a pulley; The pulley is rotatably connected to the lower end of the pulley support; The pulley is an insulating roller; Along the sliding direction of the sliding support from the front initial position to the rear end position, the first clamp, the second clamp and the pulley support are arranged in sequence and spaced apart; The second clamp is fixedly supported on the lower side of the sliding support, and the second clamp is adjacent to the rear end of the sliding support; The driver is bendably supported on the pulley, and two ends of the driver are fixedly connected to the first clamp and the second clamp respectively; The first clamp and the second clamp respectively use insulating members to fix the ends of the driver.

[0008] According to one aspect of the present invention, the resetter comprises: a return spring and a spring support; The spring support is fixedly supported on the lower side of the sliding support, and the spring support is adjacent to the front end of the sliding support; When the front end of the sliding support is in the initial position, the return spring is in an extended state; The tension sensor is located in front of the spring support, and the return spring is connected to the spring support and the tension sensor respectively.

[0009] According to one aspect of the present invention, the sliding support is in the shape of a long strip as a whole, and sliding grooves are respectively provided at both ends of the sliding support in the width direction.

[0010] According to one aspect of the present invention, an annular limiting groove is provided on the outer side surface of the pulley; The driver is located in the annular limiting groove.

[0011] To achieve the above-mentioned purpose, the present invention provides an aircraft using the above-mentioned tail device, comprising: an aircraft body and a plurality of tail devices arranged on the aircraft body; The aircraft body comprises: an aircraft shell and a heat insulation structure arranged in the aircraft shell; The thermal insulation structure is coaxial with the aircraft shell and is spaced apart; A plurality of tail wing devices are arranged at equal intervals along the circumference of the aircraft shell, and the tail wing devices are located between the heat insulation structure and the aircraft shell; The tail device comprises: a sliding support, tail wings and tail wing drive arranged on both sides of the sliding support, and a support drive and reset assembly connected to the sliding support; The tail drive is connected to the tail to adjust the attitude of the tail; Along the sliding direction of the sliding support, the support driving and resetting components are respectively connected to opposite ends of the sliding support; The support drive comprises: a driver, a controller electrically connected to the driver; The reset assembly comprises: a resetter, and a tension sensor connected to the resetter; The controller and the tension sensor are fixedly supported on the inner side of the aircraft shell; The controller is electrically connected to the tension sensor to control the magnitude of the sliding driving force of the driver on the sliding support based on the output signal of the tension sensor; The aircraft shell is provided with a guide groove for the sliding support to slide.

[0012] According to one aspect of the present invention, the support drive further comprises: a first clamp, a second clamp, a pulley support and a pulley; The pulley is rotatably connected to the lower end of the pulley support; The pulley is an insulating roller; Along the sliding direction of the sliding support from the front initial position to the rear end position, the first clamp, the second clamp and the pulley support are arranged in sequence and spaced apart; The first fixture and the pulley support are fixedly supported on the inner side of the aircraft shell, and the pulley support is adjacent to the tail end of the aircraft shell; The second clamp is fixedly supported on the lower side of the sliding support, and the second clamp is adjacent to the rear end of the sliding support; The driver is bendably supported on the pulley, and two ends of the driver are fixedly connected to the first clamp and the second clamp respectively; The first clamp and the second clamp respectively use insulating members to fix the ends of the driver.

[0013] According to one aspect of the present invention, the resetter comprises: a return spring and a spring support; The spring support is fixedly supported on the lower side of the pulley support, and the spring support is adjacent to the front end of the pulley support; When the front end of the sliding support is in the initial position, the return spring is in an extended state; The tension sensor is located in front of the spring support, and the return spring is connected to the spring support and the tension sensor respectively; The tension sensor is fixedly connected to the inner side of the aircraft shell.

[0014] According to one aspect of the present invention, sliding guide rails are respectively provided on opposite sides of the guide groove; The sliding support is in the shape of a long strip as a whole, and sliding grooves are respectively provided at both ends of the sliding support in the width direction; The sliding groove is slidably connected to match the sliding guide rail.

[0015] According to one scheme of the present invention, the present invention effectively solves the problem that the aerodynamic center of existing aircraft (such as rockets or missiles) cannot be adjusted. On the one hand, it relaxes the allowable position of the center of mass during the rocket structural design, and improves the freedom and flexibility of the structural design; during the flight, by adjusting the position of the aerodynamic center in real time, the changes in the rocket's aerodynamic center caused by fuel consumption, changes in the flight Mach number, sudden changes in atmospheric conditions, etc. can be offset, so that the rocket has both stability and maneuverability.

[0016] According to one solution of the present invention, the actuator used in the present invention is a shape memory alloy wire, which has the advantages of simple structure, high power-to-weight ratio, large driving force, etc., greatly improving the reliability and lightweight level of the structure; by increasing the diameter of the shape memory alloy wire, sufficient driving force can be generated, and the structure can withstand sufficient load. In addition, the shape memory alloy wire can be replaced at any time, realizing the reuse of the structure.

[0017] According to one solution of the present invention, the shape memory alloy wire in the present invention is heated by electric current, and the heating method is simple; the control method does not have high requirements on the axial movement response speed of the tail wing, and the filamentary shape memory alloy has a large heat dissipation area, and can meet the heat dissipation requirements through thermal radiation and thermal convection, without the need for additional active heat dissipation devices, and the device is simple and reliable.

[0018] According to one solution of the present invention, the total length of the deployable shape memory alloy wire is lengthened by using a pulley mechanism, thereby increasing the total momentum of the shape memory alloy wire and thus increasing the adjustable range of the rocket's aerodynamic center.

[0019] According to one solution of the present invention, the structure of the present invention is relatively simple, easy to install, and easy to prepare before the test and maintain after the test, and has the advantages of low use and maintenance costs.

[0020] According to one scheme of the present invention, the tail wing device designed based on the thermally deformable shape memory alloy wire can realize the overall movement of the tail wing and adaptively adjust the position of the aerodynamic center in real time. In addition, the structure has the characteristics of large deformation range, light weight, simple structure, etc., and has strong practical significance and good application prospects.

[0021] According to one solution of the present invention, the present invention is based on the fact that after heating, the heat-induced deformation shape wing alloy wire transforms from the non-twinned martensite phase to the austenite phase, during which a contraction of about 8% will be generated, thereby driving the movement of the rocket tail fin, thereby adjusting the position of the rocket's aerodynamic center; when the temperature of the alloy wire drops to a certain level, the alloy wire will be transformed into the non-twinned martensite phase under the tension of the return spring, and the contraction is restored. The total length of the shape memory alloy wire is large, and a sufficiently large driving stroke can be generated. The heat-driven shape memory alloy wire uses electric current heating and natural convection cooling to achieve rapid back and forth deformation, which can provide sufficient driving force and driving stroke, and can withstand a certain load. The device can adjust the position of the tail fin in real time according to the external flight conditions and the changes in its own internal state parameters, taking into account the aerodynamic stability and maneuverability of the rocket. By relaxing the allowable position of the rocket's center of mass distribution, the device can also improve the freedom of rocket structural design to a certain extent.

[0022] According to one solution of the present invention, the first clamp and the second clamp provided by the present invention can clamp the shape memory alloy wire by means of screw connection. The shape memory alloy wire is easy to disassemble and can be disassembled and replaced at any time, which effectively improves the maintainability of the present invention.

[0023] According to one scheme of the present invention, the present invention realizes the axial displacement control of the tail wing through four sets of relatively independent tail wing devices, which can realize the overall movement of the rocket tail wing and adaptively adjust the position of the aerodynamic center in real time, and can also realize the independent axial movement of the rocket tail wing at four different positions, providing an additional control torque for the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a perspective view of an aircraft schematically showing a tail device according to an embodiment of the present invention; Figure 2is a cross-sectional view of an aircraft schematically showing a tail device according to one embodiment of the present invention; Figure 3 is a rear view of an aircraft schematically showing a tail device according to one embodiment of the present invention; Figure 4 is a rear perspective view of an aircraft schematically showing a tail device according to an embodiment of the present invention; Figure 5 is a perspective view schematically showing a first clamp or a second clamp according to an embodiment of the present invention; Figure 6 is a perspective view schematically showing a reset assembly according to an embodiment of the present invention; Figure 7 is a perspective view schematically showing a length controller according to an embodiment of the present invention; Figure 8 is a cross-sectional view schematically showing a length controller according to an embodiment of the present invention; Fig. 9 Schematically shows a control flow chart of a tail wing device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0026] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or positional relationship shown in the relevant drawings and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operate in a specific orientation. Therefore, the above terms should not be understood as limiting the present invention.

[0027] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not therefore limited to the following embodiments.

[0028] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, according to one embodiment of the present invention, a tail device for adaptively adjusting the aerodynamic center of an aircraft comprises: a sliding support 11, tail 12 and a tail drive 13 arranged on both sides of the sliding support 11, a support drive 14 and a reset assembly 15 connected to the sliding support 11; in this embodiment, the sliding support 11 is the supporting body of the tail 12 and the tail drive 13, which realizes the overall movement of the tail 12 and the tail drive 13 through the sliding support 11, so as to realize the function of flexibly adjusting the positions of the tail 12 and the tail drive 13 along the sliding direction.

[0029] In this embodiment, the tail drive 13 is connected to the tail 12 to adjust the attitude of the tail 12. The tail drive 13 can be set as a rotary drive, and its shaft passes through the sliding support 11 to achieve connection with the tail 12, so as to achieve the rotation of the tail 12, thereby achieving the adjustment of the attitude of the tail 12.

[0030] In this embodiment, along the sliding direction of the sliding support 11, the support drive 14 and the reset assembly 15 are respectively connected to the opposite ends of the sliding support 11; wherein, the connection position of the reset assembly 15 and the sliding support 11 is located before the connection position of the support drive 14 and the sliding support 11, thereby being able to generate a pulling effect in the sliding direction of the sliding support 11, so as to achieve flexible adjustment of the position of the sliding support 11.

[0031] In this embodiment, the support drive 14 includes: a driver 141, and a controller 142 electrically connected to the driver 141; the reset component 15 includes: a resetter 151, and a tension sensor 152 connected to the resetter 151; wherein the controller 142 is electrically connected to the tension sensor 152 to control the magnitude of the sliding driving force of the driver 141 on the sliding support 11 based on the output signal of the tension sensor 152.

[0032] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the driver 141 is a shape memory alloy wire. In this embodiment, the driver 141 is a thermally deformable shape memory alloy, which is connected to the controller 142 by a wire. In this embodiment, the initial state of the driver 141 is a non-twinned martensite phase. When the temperature is higher than the austenite phase transformation start temperature, the driver 141 is in a non-twinned martensite phase. A s When the temperature is higher than the austenite phase transformation end temperature A fWhen the martensite phase is completely transformed into the austenite phase, a shrinkage of about 8% will occur during the process. The ratio of the twinned martensite phase and the austenite phase is controlled by temperature to obtain the desired shrinkage. The process of lowering the temperature is similar. When the temperature starts from the martensite phase transformation temperature M s Lower to the martensite finish temperature M f When the shape memory alloy wire is gradually transformed from the austenite phase to the austenite phase. Based on this, the controller 142 adopts the method of electrically heating the driver 141 to control the contraction amount of the driver 141, wherein the controller 142 can adopt an output voltage controller, which is directly connected to the driver 141 to control the magnitude of the output voltage and realize the electrical heating effect on the driver 141, thereby keeping the contraction amount of the driver 141 stable and controllable.

[0033] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the support drive 14 also includes: a first clamp 143, a second clamp 144, a pulley support 145 and a pulley 146; in this embodiment, the pulley 146 is rotatably connected to the lower end of the pulley support 145; wherein the pulley 146 is an insulating roller, and specifically, the pulley 146 can be a ceramic roller. The pulley 146 provided as above has excellent insulation performance, which can effectively avoid the short circuit between the driver 141 and the pulley support 145, so as to effectively ensure the reliable and stable operation of the driver 141. In addition, by adopting a ceramic roller, the position where the pulley 146 is connected to the driver 141 can be conveniently set to a smooth surface, thereby sufficiently reducing the wear on the driver 141, which is beneficial to ensuring the long-term stable operation of the driver 141.

[0034] In this embodiment, along the direction of the sliding support 11 sliding from the front initial position to the rear terminal position, the first clamp 143, the second clamp 144 and the pulley support 145 are arranged in sequence and spaced apart; wherein the second clamp 144 is fixedly supported on the lower side of the sliding support 11, and the second clamp 144 is adjacent to the tail end of the sliding support 11. In this embodiment, the driver 141 can be supported on the pulley 146 in a bendable manner, and the two ends of the driver 141 are respectively fixedly connected to the first clamp 143 and the second clamp 144. Among them, since the driver 141 can be set as a shape memory alloy wire, the steering control of the driver 141 can be achieved through the action of the pulley 146, so that the two ends of the driver 141 can be conveniently connected to the first clamp 143 and the second clamp 144 located in front of the pulley support 145. Among them, the opposite ends of the driver 141 use alligator clips or other connection structures to achieve point connection with the controller 142, thereby exciting the driver 141 with current through the controller 142.

[0035] like Figure 5 As shown, in this embodiment, the structures of the first clamp 143 and the second clamp 144 are consistent, which specifically include: a clamp column A and a clamp plate B; wherein the clamp column A is a rectangular column as a whole, and the clamp plate B is a rectangular plate as a whole. In this embodiment, the clamp plate B is connected to the clamp column A by a threaded connector to achieve clamping and fixing of the end of the driver 141. In order to effectively ensure the insulation between the first clamp 143 and the second clamp 144 and the driver 141, an insulating member can be further provided between the first clamp 143 and the end of the driver 141 and between the second clamp 144 and the end of the driver 141; wherein the insulating member can be provided as two opposite insulating sheets, wherein a part of the insulating sheet is fixedly connected to the end face of the clamp column A, and the other part of the insulating sheet is fixedly connected to the end face of the clamp plate B, thereby, the end of the driver 141 can be insulated and fixed by fixing the clamp column A and the clamp plate B, thereby ensuring the reliability of the connection position and long-term stable operation. In this embodiment, the insulating sheet may be a polytetrafluoroethylene gasket.

[0036] In this embodiment, a fixed connecting plate C is further provided at one end of the clamp column A away from the clamp plate B, and a reinforcing connecting plate D can be further arranged between the clamp column A and the fixed connecting plate C. Thus, the connection strength between the clamp column A and the fixed connecting plate C can be effectively guaranteed, thereby ensuring the structural reliability of the entire device.

[0037] In this embodiment, the pulley support 145 includes: a support connecting plate 1451, two pulley connecting plates 1452 vertically supported on the support connecting plate 1451, and a reinforcing rib 1453 for connecting the support connecting plate 1451 and the pulley connecting plate 1452. In this embodiment, the support connecting plate 1451 is a rectangular plate, wherein the two pulley connecting plates 1452 are arranged relative to each other with a gap along the length direction of the support connecting plate 1451. In this embodiment, the reinforcing rib 1453 is a right-angled triangular plate, which is fixedly connected to the support connecting plate 1451 and the pulley connecting plate 1452 to achieve the stability and reliability of the entire pulley support 145 structure.

[0038] In this embodiment, the pulley 146 is disposed between two pulley connecting plates 1452 , and is rotatably connected to the ends of the pulley connecting plates 1452 via a rotating shaft.

[0039] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6 As shown, according to an embodiment of the present invention, the resetter 151 includes: a return spring 151a and a spring support 151b; in this embodiment, the spring support 151b is fixedly supported on the lower side of the sliding support 11, and the spring support 151b is adjacent to the front end of the sliding support 11. In this embodiment, when the front end of the sliding support 11 is in the initial position, the return spring 151a is in an elongated state; thus, the pre-tension provided by the return spring 151a enables the tail 12 of the aircraft to withstand a certain axial aerodynamic load during the flight, so as to ensure stable control of the flight.

[0040] Further, the tension sensor 152 is located in front of the spring support 151b, and the return spring 151a is respectively connected to the spring support 151b and the tension sensor 152. In this embodiment, the spring support 151b can be set as a column of regular shape, which can be set as a cylinder or a rectangular column, wherein a through hole penetrating the body of the spring support 151b can be set to achieve connection with the return spring 151a, so as to ensure stable and reliable connection.

[0041] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the sliding support 11 is in the shape of a long strip as a whole, and sliding grooves 11a are respectively provided at both ends in the width direction of the sliding support 11. In this embodiment, the sliding groove 11a is provided as a rectangular groove with a rectangular cross section, which runs through both ends in the length direction of the sliding support 11 along the length direction of the sliding support 11 to facilitate the stable sliding of the sliding support 11.

[0042] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, an annular limiting groove is provided on the outer side surface of the pulley 146; in this embodiment, the driver 141 is in the annular limiting groove to achieve stable limitation on the position of the driver 141, so that the driver 141 can be accurately limited and the accurate control of the position of the tail wing 12 is ensured.

[0043] Combination Figure 7 and Figure 8 As shown, according to one embodiment of the present invention, the driver 141 is provided with a length controller 141a; wherein the length controller 141a comprises: a mounting seat 141a1, and a telescopic control component 141a2 mounted on the mounting seat 141a1; wherein the telescopic control component 141a2 is slidably connected to the mounting seat 141a1, and the sliding direction of the telescopic control component 141a2 on the mounting seat 141a1 is consistent with the length direction of the driver 141. In this embodiment, the driver 141 is partially wound around the telescopic control component 141a2, so as to control the rapid change of the length of the driver 141 through the telescopic action of the telescopic control component 141a2.

[0044] In this embodiment, the mounting seat 141a1 includes: a top plate 141a11, and side plates 141a12 arranged at opposite ends of the top plate 141a11, wherein the two top plates 141a11 are located on the same side of the top plate 141a11. In this embodiment, a limited sliding groove 141a121 is arranged on the side of the side plate 141a12 away from the top plate 141a11, wherein the limited sliding groove 141a121 is located on the inner side of the side plate 141a12, so that the limited sliding grooves 141a121 on the two side plates 141a12 are opposite to each other, so as to achieve sliding connection with the telescopic control component 141a2. In this embodiment, the limited sliding groove 141a121 can be set as a T-shaped groove, so that the telescopic control component 141a2 can slide along the limited sliding groove 141a121, effectively preventing the telescopic control component 141a2 from coming out in a direction perpendicular to the limited sliding groove 141a121. Through the above arrangement, the actuator 141 can be thermally contracted to synchronously move the telescopic control assembly 141a2, effectively ensuring the reliability and accuracy of the movement of the actuator 141. In addition, the mounting seat 141a1 can also effectively ensure the support of the telescopic control assembly 141a2 on the actuator 141, so as to effectively avoid the influence of the gravity of the actuator 141 on its size. In addition, the shaking of the actuator 141 during the actuation process can also be effectively avoided, which is further beneficial to ensuring the stable operation of the actuator 141.

[0045] In this embodiment, the telescopic control component 141a2 includes: arc portions 141a21 arranged relatively to each other, a middle connector 141a22 arranged between the two arc portions 141a21, an elastic connector 141a23 and a telescopic limiting member 141a24; wherein, a guide tube 141a211 is arranged on the inner side of the arc portion 141a21, and the guide tube 141a211 has a corresponding opening on the arc portion 141a21, thereby, the elastic connector 141a23 can be installed in the guide tube 141a211, and a threaded member is arranged at the opening position on the arc portion 141a21 to limit the elastic connector 141a23 in the guide tube 141a211. Furthermore, the middle piece connecting piece 141a22 is slidably connected to the guide tube 141a211, and under the pressure of the elastic connecting piece 141a23, the middle piece connecting piece 141a22 is elastically restricted, thereby realizing the telescopic movement of the two relative arc parts 141a21.

[0046] In this embodiment, the arc portion 141a21 can be set to a semicircular arc or a sector-shaped arc with a central angle less than 180°. The quality of the arc portion 141a21 can be controlled by setting the arc portion 141a21 in different states. Of course, in order to further reduce its weight, it can also be made of a material with light density and high strength, such as aluminum alloy material, etc. Of course, the arc portion 141a21 can also be made into a hollow structure by 3D printing to reduce its weight.

[0047] In this embodiment, the guide tube 141a211 is arranged along the radial direction of the arc portion 141a21, and is located in the middle position of the arc portion 141a21 in the circumferential direction of the arc portion 141a21, wherein along the axial direction of the arc portion 141a21, the guide tube 141a211 can be set to one, or can be set to multiple (such as two, three, etc.) at intervals.

[0048] In this embodiment, the middle connector 141a22 includes: a central support column 141a221, and guide columns 141a222 arranged on opposite sides of the central support column 141a221; wherein the guide columns 141a222 are arranged one-to-one with the guide tubes 141a211, and the guide columns 141a222 extend into the guide tubes 141a211 and are slidably connected to the guide tubes 141a211, thereby, the ends of the guide columns 141a222 are abutted against the elastic connector 141a23; wherein the elastic connector 141a23 is configured as a compression spring, whereby, in an initial state, the two relative arc portions 141a21 are arranged to be far away from each other, wherein, in order to prevent the guide column 141a222 from escaping from the guide tube 141a211, a radially enlarged protrusion may be configured at the end of the guide column 141a222, whereby a limiting ring abutting against the end of the guide column 141a222 is configured on the inner side of the end of the guide tube 141a211, thereby allowing the end of the guide column 141a222 to reliably slide in the guide tube 141a211.

[0049] In this embodiment, a movable connection structure is provided at opposite ends of the central support column 141a221, wherein the movable connection structure includes: a rotation limiting portion and a sliding connection portion, wherein the rotation limiting portion and the sliding connection portion are sequentially arranged in a direction away from the central support column 141a221, wherein the area of ​​the sliding connection portion is larger than the area of ​​the rotation limiting portion, and the size of the rotation limiting portion matches the small opening portion of the limited sliding groove 141a121, and the sliding connection portion is connected to the large opening portion of the limited sliding groove 141a121; wherein the rotation limiting portion can be set as a rectangular body, and the sliding connection portion can be set as a rectangular column or a cylinder. Of course, in another embodiment, the sliding connection portion can be set to be rotatable so as to reduce friction during movement.

[0050] In this embodiment, an insulating layer (for example, an insulating plastic layer, a ceramic layer, etc.) is provided on the outer arc surface of the circular arc portion 141a21; further, a first mounting groove for mounting the telescopic limiting member 141a24 is provided on the outer arc surface of the circular arc portion 141a21, wherein the telescopic limiting member 141a24 can be made of shape memory alloy wire, for example, thermally deformable shape memory alloy, which is connected to the telescopic controller by a wire. In the present embodiment, the telescopic limiting member 141a24 is wound around two opposite arc portions 141a21, and the telescopic limiting member 141a24 is wound around when the two arc portions 141a21 are in an initial state (a state where the two opposite arc portions 141a21 are away from each other), thereby, when the telescopic limiting member 141a24 is energized and heated, the two arc portions 141a21 are moved toward each other, thereby, the portion of the driver 141 wound around the two arc portions 141a21 is loosened, thereby increasing the effective length of the driver 141, thereby enabling the resetter 151 to quickly reset the sliding support 11, thereby effectively increasing the flexible control over the reset of the sliding support 11.

[0051] In this embodiment, a second mounting groove for winding the driver 141 is provided on the outer arc surface of the arc portion 141a21, wherein the second mounting groove is provided at the middle position of the arc portion 141a21 along the axial direction of the arc portion 141a21, and the first mounting groove can be provided on opposite sides of the second mounting groove, thereby, the telescopic limiting member 141a24 can be respectively installed on both sides of the second mounting groove to achieve a fast response of the telescopic control. In this embodiment, the radial depth of the first mounting groove on the arc portion 141a21 is less than the radial depth of the second mounting groove, thereby, the length of the telescopic limiting member 141a24 can be effectively increased, so as to facilitate the increase of the range of motion between the two arc portions 141a21.

[0052] In this embodiment, in order to prevent the driver 141 from compressing the two arc parts 141a21 in the telescopic control component 141a2 during the thermal contraction process, the insulating layer of the outer arc surface of the arc part 141a21 can be set to a smooth surface to reduce the friction between the driver 141 and the arc part 141a21, and the performance of the elastic connecting member 141a23 is set to offset the compression effect of the driver 141 on the two arc parts 141a21, so as to effectively ensure the accuracy of the driver 141 during the operation process. In addition, in order to ensure the rapid compression of the two arc parts 141a21 by the telescopic limiting member 141a24, the wire diameter and the number of windings of the telescopic limiting member 141a24 can be flexibly arranged to ensure the effectiveness of the operation of the telescopic limiting member 141a24.

[0053] In this embodiment, in order to restore the winding length of the driver 141 on the arc portion 141a21, the telescopic limiting member 141a24 can be powered off, and the two relative arc portions 141a21 can be restored to their initial positions under the action of the elastic connecting member 141a23 to achieve the recovery of the driver 141.

[0054] It should be noted that an insulating member is provided between each turn of the telescopic limiting member 141a24 wound on the arc portion 141a21 and between each turn of the driver 141 to effectively avoid short circuits between each other and ensure the effectiveness of the actuation.

[0055] Through the above arrangement, based on the arranged length controller 141a, by controlling the power-on timing and time of the telescopic limiting member 141a24 thereon, combined control with the driver 141 can also be achieved to flexibly adjust the movement flexibility of the sliding support 11.

[0056] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the present invention provides an aircraft using the above-mentioned tail device, comprising: an aircraft body a and a plurality of tail devices b arranged on the aircraft body a. In this embodiment, the aircraft body a comprises: an aircraft shell a1 and a heat insulation structure a2 arranged in the aircraft shell a1; wherein the heat insulation structure a2 is coaxial with the aircraft shell a1 and has a spacing arrangement; wherein the aircraft shell a1 can be set in a cylindrical shape, and the corresponding heat insulation structure a2 can also be set in a cylindrical shape, and then through the coaxial arrangement, an annular space for installing the tail device b can be formed between the heat insulation structure a2 and the aircraft shell a1, thereby facilitating the installation of the tail device b. In addition, through the provided heat insulation structure a2, it is also possible to install the aircraft engine, nozzle, combustion chamber and other structures in the heat insulation structure a2, so as to separate it from the tail device b through the heat insulation structure a2, so as to avoid the influence of the heat generated by the aircraft engine, nozzle, combustion chamber and other structures on the tail device b, so as to ensure the reliable and stable operation of the tail device b.

[0057] In this embodiment, a plurality of tail devices b are arranged at equal intervals along the circumference of the aircraft shell a1, and the tail devices b are located between the heat insulation structure a2 and the aircraft shell a1; for example, if four tail devices b are arranged, the four tail devices b can be distributed in a cross shape along the circumference of the aircraft shell a1. In this embodiment, the tail device b includes: a sliding support 11, a tail 12 and a tail drive 13 arranged on both sides of the sliding support 11, a support drive 14 and a reset assembly 15 connected to the sliding support 11; in this embodiment, the sliding support 11 is the supporting body of the tail 12 and the tail drive 13, which realizes the overall movement of the tail 12 and the tail drive 13 through the sliding support 11, so as to realize the function of flexibly adjusting the positions of the tail 12 and the tail drive 13 along the sliding direction.

[0058] In this embodiment, the tail drive 13 is connected to the tail 12 to adjust the attitude of the tail 12. The tail drive 13 can be set as a rotary drive, and its shaft passes through the sliding support 11 to achieve connection with the tail 12, so as to achieve the rotation of the tail 12, thereby achieving the adjustment of the attitude of the tail 12.

[0059] In this embodiment, along the sliding direction of the sliding support 11, the support drive 14 and the reset assembly 15 are respectively connected to the opposite ends of the sliding support 11; wherein, the connection position of the reset assembly 15 and the sliding support 11 is located before the connection position of the support drive 14 and the sliding support 11, thereby being able to generate a pulling effect in the sliding direction of the sliding support 11, so as to achieve flexible adjustment of the position of the sliding support 11.

[0060] In this embodiment, the support drive 14 includes: a driver 141, a controller 142 electrically connected to the driver 141; the reset assembly 15 includes: a resetter 151, a tension sensor 152 connected to the resetter 151; wherein the controller 142 and the tension sensor 152 are fixedly supported on the inner side of the aircraft shell a1, and the controller 142 is electrically connected to the tension sensor 152, so as to control the magnitude of the sliding driving force of the driver 141 on the sliding support 11 based on the output signal of the tension sensor 152. In this embodiment, the aircraft shell a1 is provided with a guide groove a11 for the sliding support 11 to slide, and the guide groove a11 is provided to achieve directional and stable sliding of the sliding support 11, wherein the extension direction of the guide groove a11 is consistent with the axial direction of the aircraft shell a1.

[0061] In this embodiment, the driver 141 is a shape memory alloy wire; wherein the driver 141 is a thermally deformable shape memory alloy, and is connected to the controller 142 by a wire.

[0062] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, according to one embodiment of the present invention, the support drive 14 also includes: a first clamp 143, a second clamp 144, a pulley support 145 and a pulley 146; in this embodiment, the pulley 146 is rotatably connected to the lower end of the pulley support 145; wherein the pulley 146 is an insulating roller, and specifically, the pulley 146 can be a ceramic roller. The pulley 146 provided as above has excellent insulation performance, which can effectively avoid the short circuit between the driver 141 and the pulley support 145, so as to effectively ensure the reliable and stable operation of the driver 141. In addition, by adopting a ceramic roller, the position where the pulley 146 is connected to the driver 141 can be conveniently set to a smooth surface, thereby sufficiently reducing the wear on the driver 141, which is beneficial to ensuring the long-term stable operation of the driver 141.

[0063] In the present embodiment, along the direction in which the sliding support 11 slides from the front initial position to the rear terminal position, the first clamp 143, the second clamp 144 and the pulley support 145 are arranged in sequence and spaced apart; wherein, the first clamp 143 and the pulley support 145 are fixedly supported on the inner side of the aircraft shell a1, and the pulley support 145 is adjacent to the rear end of the aircraft shell a1; in the present embodiment, the installation position of the pulley support 145 corresponds to the guide groove a11, so as to ensure that the extension and retraction direction of the driver 141 is consistent with the moving direction of the sliding support 11, and in addition, the rear end of the guide groove a11 can also be closed by the set pulley support 145 to prevent the sliding support 11 from falling out, thereby ensuring the stable and reliable installation of the sliding support 11.

[0064] In this embodiment, the second clamp 144 is fixedly supported on the lower side of the sliding support 11, and the second clamp 144 is adjacent to the rear end of the sliding support 11; wherein the first clamp 143, the second clamp 144 and the pulley support 145 are in the same straight line direction, and then the driver 141 can be bent and supported on the pulley 146, and the two ends of the driver 141 are respectively fixedly connected with the first clamp 143 and the second clamp 144. wherein, since the driver 141 can be set as a shape memory alloy wire, and then, the steering control of the driver 141 can be achieved through the action of the pulley 146, so that the two ends of the driver 141 can be conveniently connected with the first clamp 143 and the second clamp 144 located in front of the pulley support 145.

[0065] In this embodiment, the structures of the first clamp 143 and the second clamp 144 are consistent, and specifically include: a clamp column A and a clamp plate B; wherein the clamp column A is a rectangular column as a whole, and the clamp plate B is a rectangular plate as a whole. In this embodiment, the clamp plate B is connected to the clamp column A by a threaded connector to achieve clamping and fixing of the end of the driver 141. In order to effectively ensure the insulation between the first clamp 143 and the second clamp 144 and the driver 141, an insulating member can be further provided between the first clamp 143 and the end of the driver 141 and between the second clamp 144 and the end of the driver 141; wherein the insulating member can be provided as two opposite insulating sheets, wherein a part of the insulating sheet is fixedly connected to the end face of the clamp column A, and the other part of the insulating sheet is fixedly connected to the end face of the clamp plate B, thereby, the end of the driver 141 can be insulated and fixed by fixing the clamp column A and the clamp plate B, thereby ensuring the reliability of the connection position and long-term stable operation. In this embodiment, the insulating sheet can be a polytetrafluoroethylene gasket.

[0066] In this embodiment, a fixed connecting plate C is further provided at one end of the clamp column A away from the clamp plate B, and a reinforcing connecting plate D can be further arranged between the clamp column A and the fixed connecting plate C. Thus, the connection strength between the clamp column A and the fixed connecting plate C can be effectively guaranteed, thereby ensuring the structural reliability of the entire device.

[0067] In this embodiment, the pulley support 145 includes: a support connecting plate 1451, two pulley connecting plates 1452 vertically supported on the support connecting plate 1451, and a reinforcing rib 1453 for connecting the support connecting plate 1451 and the pulley connecting plate 1452. In this embodiment, the support connecting plate 1451 is a rectangular plate, wherein the two pulley connecting plates 1452 are arranged relative to each other with a gap along the length direction of the support connecting plate 1451. In this embodiment, the reinforcing rib 1453 is a right-angled triangular plate, which is fixedly connected to the support connecting plate 1451 and the pulley connecting plate 1452 to achieve the stability and reliability of the entire pulley support 145 structure.

[0068] In this embodiment, the pulley 146 is disposed between two pulley connecting plates 1452 , and is rotatably connected to the ends of the pulley connecting plates 1452 via a rotating shaft.

[0069] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 6As shown, according to an embodiment of the present invention, the resetter 151 includes: a return spring 151a and a spring support 151b; in this embodiment, the spring support 151b is fixedly supported on the lower side of the sliding support 11, and the spring support 151b is adjacent to the front end of the sliding support 11. In this embodiment, the return spring 151a, the spring support 151b, the tension sensor 152, the first clamp 143, the second clamp 144 and the pulley support 145 are also in the same straight line direction, so that the reset assembly 15 and the support drive 14 produce a pulling effect on the sliding support 11 in the same direction, so that the control of the position of the sliding support 11 is more accurate and flexible.

[0070] Furthermore, when the front end of the sliding support 11 is in the initial position, the return spring 151a is in an extended state; thus, the pre-tension provided by the return spring 151a enables the tail wing 12 of the aircraft to withstand a certain axial aerodynamic load during the flight, so as to ensure stable control of the flight.

[0071] In this embodiment, the tension sensor 152 is located in front of the spring support 151b, and the return spring 151a is connected to the spring support 151b and the tension sensor 152 respectively; wherein the tension sensor 152 is fixedly connected to the inner side of the aircraft shell a1, so as to achieve stable installation of the return spring 151a and conveniently measure the tension of the return spring 151a accurately through the tension sensor 152. In this embodiment, the spring support 151b can be set as a column of regular shape, which can be set as a cylinder or a rectangular column, wherein a through hole penetrating the body of the spring support 151b can be set to achieve connection with the return spring 151a, so as to ensure stable and reliable connection.

[0072] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, according to an embodiment of the present invention, two opposite sides of the guide groove a11 are respectively provided with sliding rails a111; in this embodiment, the sliding support 11 is in the shape of a long strip plate as a whole, and two ends of the sliding support 11 in the width direction are respectively provided with sliding grooves 11a, and the sliding grooves 11a are slidably connected to the sliding rails a111 in a matching manner. In this embodiment, the sliding rails a111 are made of a long strip plate, and their cross-sectional shape is matched with the cross-sectional shape of the sliding grooves 11a, so as to achieve stable and reliable installation of the sliding support 11.

[0073] Combination Figure 1 , Figure 2 , Figure 3 and Figure 4As shown, according to one embodiment of the present invention, an annular limiting groove is provided on the outer side surface of the pulley 146; in this embodiment, the driver 141 is in the annular limiting groove to achieve stable limitation on the position of the driver 141, so that the driver 141 can be accurately limited and the accurate control of the position of the tail wing 12 is ensured.

[0074] Combination Figure 7 and Figure 8 As shown, according to one embodiment of the present invention, the driver 141 is provided with a length controller 141a; wherein the length controller 141a comprises: a mounting seat 141a1, and a telescopic control component 141a2 mounted on the mounting seat 141a1; wherein the telescopic control component 141a2 is slidably connected to the mounting seat 141a1, and the sliding direction of the telescopic control component 141a2 on the mounting seat 141a1 is consistent with the length direction of the driver 141. In this embodiment, the driver 141 is partially wound around the telescopic control component 141a2, so as to control the rapid change of the length of the driver 141 through the telescopic action of the telescopic control component 141a2.

[0075] In this embodiment, the mounting seat 141a1 includes: a top plate 141a11, and side plates 141a12 arranged at opposite ends of the top plate 141a11, wherein the two top plates 141a11 are located on the same side of the top plate 141a11. In this embodiment, a limited sliding groove 141a121 is arranged on the side of the side plate 141a12 away from the top plate 141a11, wherein the limited sliding groove 141a121 is located on the inner side of the side plate 141a12, so that the limited sliding grooves 141a121 on the two side plates 141a12 are opposite to each other, so as to achieve sliding connection with the telescopic control component 141a2. In this embodiment, the limited sliding groove 141a121 can be set as a T-shaped groove, so that the telescopic control component 141a2 can slide along the limited sliding groove 141a121, effectively preventing the telescopic control component 141a2 from coming out in a direction perpendicular to the limited sliding groove 141a121. Through the above arrangement, the actuator 141 can be thermally contracted to synchronously move the telescopic control assembly 141a2, effectively ensuring the reliability and accuracy of the movement of the actuator 141. In addition, the mounting seat 141a1 can also effectively ensure the support of the telescopic control assembly 141a2 on the actuator 141, so as to effectively avoid the influence of the gravity of the actuator 141 on its size. In addition, the shaking of the actuator 141 during the actuation process can also be effectively avoided, which is further beneficial to ensuring the stable operation of the actuator 141.

[0076] In this embodiment, the top plate 141a11 can be installed on the inner side of the aircraft shell a1 by using threaded connectors, wherein along the axial direction of the aircraft shell a1, the length controller 141a can be set to one or more.

[0077] In this embodiment, the telescopic control component 141a2 includes: arc portions 141a21 arranged relatively to each other, a middle connector 141a22 arranged between the two arc portions 141a21, an elastic connector 141a23 and a telescopic limiting member 141a24; wherein, a guide tube 141a211 is arranged on the inner side of the arc portion 141a21, and the guide tube 141a211 has a corresponding opening on the arc portion 141a21, thereby, the elastic connector 141a23 can be installed in the guide tube 141a211, and a threaded member is arranged at the opening position on the arc portion 141a21 to limit the elastic connector 141a23 in the guide tube 141a211. Furthermore, the middle piece connecting piece 141a22 is slidably connected to the guide tube 141a211, and under the pressure of the elastic connecting piece 141a23, the middle piece connecting piece 141a22 is elastically restricted, thereby realizing the telescopic movement of the two relative arc parts 141a21.

[0078] In this embodiment, the arc portion 141a21 can be set to a semicircular arc or a sector-shaped arc with a central angle less than 180°. The quality of the arc portion 141a21 can be controlled by setting the arc portion 141a21 in different states. Of course, in order to further reduce its weight, it can also be made of a material with light density and high strength, such as aluminum alloy material, etc. Of course, the arc portion 141a21 can also be made into a hollow structure by 3D printing to reduce its weight.

[0079] In this embodiment, the guide tube 141a211 is arranged along the radial direction of the arc portion 141a21, and is located in the middle position of the arc portion 141a21 in the circumferential direction of the arc portion 141a21, wherein along the axial direction of the arc portion 141a21, the guide tube 141a211 can be set to one, or can be set to multiple (such as two, three, etc.) at intervals.

[0080] In this embodiment, the middle connector 141a22 includes: a central support column 141a221, and guide columns 141a222 arranged on opposite sides of the central support column 141a221; wherein the guide columns 141a222 are arranged one-to-one with the guide tubes 141a211, and the guide columns 141a222 extend into the guide tubes 141a211 and are slidably connected to the guide tubes 141a211, thereby, the ends of the guide columns 141a222 are abutted against the elastic connector 141a23; wherein the elastic connector 141a23 is configured as a compression spring, whereby, in an initial state, the two relative arc portions 141a21 are arranged to be far away from each other, wherein, in order to prevent the guide column 141a222 from escaping from the guide tube 141a211, a radially enlarged protrusion may be configured at the end of the guide column 141a222, whereby a limiting ring abutting against the end of the guide column 141a222 is configured on the inner side of the end of the guide tube 141a211, thereby allowing the end of the guide column 141a222 to reliably slide in the guide tube 141a211.

[0081] In this embodiment, a movable connection structure is provided at opposite ends of the central support column 141a221, wherein the movable connection structure includes: a rotation limiting portion and a sliding connection portion, wherein the rotation limiting portion and the sliding connection portion are sequentially arranged in a direction away from the central support column 141a221, wherein the area of ​​the sliding connection portion is larger than the area of ​​the rotation limiting portion, and the size of the rotation limiting portion matches the small opening portion of the limited sliding groove 141a121, and the sliding connection portion is connected to the large opening portion of the limited sliding groove 141a121; wherein the rotation limiting portion can be set as a rectangular body, and the sliding connection portion can be set as a rectangular column or a cylinder. Of course, in another embodiment, the sliding connection portion can be set to be rotatable so as to reduce friction during movement.

[0082] In this embodiment, an insulating layer (for example, an insulating plastic layer, a ceramic layer, etc.) is provided on the outer arc surface of the circular arc portion 141a21; further, a first mounting groove for mounting the telescopic limiting member 141a24 is provided on the outer arc surface of the circular arc portion 141a21, wherein the telescopic limiting member 141a24 can be made of shape memory alloy wire, for example, thermally deformable shape memory alloy, which is connected to the telescopic controller by a wire. In the present embodiment, the telescopic limiting member 141a24 is wound around two opposite arc portions 141a21, and the telescopic limiting member 141a24 is wound around when the two arc portions 141a21 are in an initial state (a state where the two opposite arc portions 141a21 are away from each other), thereby, when the telescopic limiting member 141a24 is energized and heated, the two arc portions 141a21 are moved toward each other, thereby, the portion of the driver 141 wound around the two arc portions 141a21 is loosened, thereby increasing the effective length of the driver 141, thereby enabling the resetter 151 to quickly reset the sliding support 11, thereby effectively increasing the flexible control over the reset of the sliding support 11.

[0083] In this embodiment, a second mounting groove for winding the driver 141 is provided on the outer arc surface of the arc portion 141a21, wherein the second mounting groove is provided at the middle position of the arc portion 141a21 along the axial direction of the arc portion 141a21, and the first mounting groove can be provided on opposite sides of the second mounting groove, thereby, the telescopic limiting member 141a24 can be respectively installed on both sides of the second mounting groove to achieve a fast response of the telescopic control. In this embodiment, the radial depth of the first mounting groove on the arc portion 141a21 is less than the radial depth of the second mounting groove, thereby, the length of the telescopic limiting member 141a24 can be effectively increased, so as to facilitate the increase of the range of motion between the two arc portions 141a21.

[0084] In this embodiment, in order to prevent the driver 141 from compressing the two arc parts 141a21 in the telescopic control component 141a2 during the thermal contraction process, the insulating layer of the outer arc surface of the arc part 141a21 can be set to a smooth surface to reduce the friction between the driver 141 and the arc part 141a21, and the performance of the elastic connecting member 141a23 is set to offset the compression effect of the driver 141 on the two arc parts 141a21, so as to effectively ensure the accuracy of the driver 141 during the operation process. In addition, in order to ensure the rapid compression of the two arc parts 141a21 by the telescopic limiting member 141a24, the wire diameter and the number of windings of the telescopic limiting member 141a24 can be flexibly arranged to ensure the effectiveness of the operation of the telescopic limiting member 141a24.

[0085] In this embodiment, in order to restore the winding length of the driver 141 on the arc portion 141a21, the telescopic limiting member 141a24 can be powered off, and the two relative arc portions 141a21 can be restored to their initial positions under the action of the elastic connecting member 141a23 to achieve the recovery of the driver 141.

[0086] It should be noted that an insulating member is provided between each turn of the telescopic limiting member 141a24 wound on the arc portion 141a21 and between each turn of the driver 141 to effectively avoid short circuits between each other and ensure the effectiveness of the actuation.

[0087] Through the above arrangement, based on the arranged length controller 141a, by controlling the power-on timing and time of the telescopic limiting member 141a24 thereon, combined control with the driver 141 can also be achieved to flexibly adjust the movement flexibility of the sliding support 11.

[0088] To further illustrate this solution, the execution flow of its control is further described.

[0089] S1. Complete the program design, equipment installation, debugging and inspection of the tail device during the flight of the aircraft during the ground preparation stage; S2. After the aircraft (such as a missile / rocket) takes off, the tail 12 in the tail device needs to move axially during the flight. When the aircraft enters supersonic flight from subsonic speed, the aerodynamic center of the missile / rocket will change dramatically, and the performance and response characteristics of the aircraft's flight control system may be affected. In order to eliminate this effect, the axial position of the tail 12 can be adjusted. The specific implementation method is: combined with Fig. 9As shown, the controller 142 can calculate the required axial displacement of the tail 12 according to the information transmitted by the flight control computer of the aircraft and the external sensor, obtain the corresponding control signal, and give a voltage output to the driver 141. When the stiffness coefficient, original length and other parameters of the resetter 151 are given, the controller 142 can calculate the actual position of the axial sliding support 11 or the tail 12 according to the feedback signal of the tension sensor 152, and control the voltage output. When the electric heating power and the heat dissipation power of the driver 141 reach a balance, the temperature remains stable and the deformation remains stable. For another example, during the flight of the aircraft, as the fuel is consumed, the position of the center of mass of the aircraft will move backward. If the aerodynamic center position does not match the center of mass position, it may cause the rocket to have unstable attitude changes during the flight. To prevent this from happening, the position of the tail 12 needs to be moved backward, and the specific method is the same as above. It should be noted that in order to ensure that the tail 12 can move forward and backward in the axial direction after the aircraft takes off, before takeoff, the driver 141 should be given an initial temperature so that it is in a mixed state of austenite and martensite phases. In this embodiment, during the flight, the length controller 141 a can be flexibly controlled based on the control requirements of the sliding support 11 to achieve rapid movement of the sliding support 11 under preset conditions.

[0090] S3. After the flight of the aircraft, equipment maintenance is carried out. If the aircraft is required to be recovered and reused, the integrity of the entire device is evaluated after the flight mission is completed to determine whether some vulnerable structures and electronic components need to be repaired or replaced.

[0091] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail therein, it should be understood that they can be implemented by adopting general devices and general methods available in the art.

[0092] The above is only one solution of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A tail device for adaptively adjusting the aerodynamic center of an aircraft, characterized in that: include: A sliding support (11), tail wings (12) and a tail wing drive (13) arranged on both sides of the sliding support (11), a support drive (14) and a reset assembly (15) connected to the sliding support (11); The tail wing drive (13) is connected to the tail wing (12) to adjust the posture of the tail wing (12); Along the sliding direction of the sliding support (11), the support drive (14) and the reset assembly (15) are respectively connected to opposite ends of the sliding support (11); The support drive (14) comprises: a driver (141), and a controller (142) electrically connected to the driver (141); The reset component (15) comprises: a reset device (151), and a tension sensor (152) connected to the reset device (151); The controller (142) is electrically connected to the tension sensor (152) so as to control the magnitude of the sliding driving force exerted by the driver (141) on the sliding support (11) based on an output signal of the tension sensor (152).

2. The tail device according to claim 1, characterized in that: The driver (141) is a shape memory alloy wire.

3. The tail device according to claim 2, characterized in that: The support drive (14) further comprises: a first clamp (143), a second clamp (144), a pulley support (145) and a pulley (146); The pulley (146) is rotatably connected to the lower end of the pulley support (145); The pulley (146) is an insulating roller; Along the sliding direction of the sliding support (11) from the front initial position to the rear end position, the first clamp (143), the second clamp (144) and the pulley support (145) are arranged in sequence and spaced apart; The second clamp (144) is fixedly supported on the lower side of the sliding support (11), and the second clamp (144) is adjacent to the rear end of the sliding support (11); The driver (141) is bendably supported on the pulley (146), and two ends of the driver (141) are respectively fixedly connected to the first clamp (143) and the second clamp (144); The first clamp (143) and the second clamp (144) respectively use insulating members to fix the ends of the driver (141).

4. The tail wing device according to claim 3, characterized in that: The resetter (151) comprises: a return spring (151a) and a spring support (151b); The spring support (151b) is fixedly supported on the lower side of the sliding support (11), and the spring support (151b) is adjacent to the front end of the sliding support (11); When the front end of the sliding support (11) is in an initial position, the return spring (151a) is in an extended state; The tension sensor (152) is located in front of the spring support (151b), and the return spring (151a) is respectively connected to the spring support (151b) and the tension sensor (152).

5. The tail wing device according to claim 4, characterized in that: The sliding support (11) is in the shape of a long strip as a whole, and sliding grooves (11a) are respectively provided at both ends of the sliding support (11) in the width direction.

6. The tail wing device according to claim 5, characterized in that: An annular limiting groove is provided on the outer side surface of the pulley (146); The driver (141) is located in the annular limiting groove.

7. An aircraft using the tail device according to any one of claims 1 to 6, characterized in that: include: An aircraft body (a) and a plurality of tail wing devices (b) arranged on the aircraft body (a); The aircraft body (a) comprises: an aircraft shell (a1) and a heat insulation structure (a2) arranged in the aircraft shell (a1); The heat insulation structure (a2) is coaxial with the aircraft shell (a1) and is spaced apart; Along the circumference of the aircraft shell (a1), a plurality of the tail wing devices (b) are arranged at equal intervals, and the tail wing devices (b) are located between the heat insulation structure (a2) and the aircraft shell (a1); The tail device (b) comprises: a sliding support (11), tail wings (12) and a tail wing drive (13) arranged on both sides of the sliding support (11), a support drive (14) and a reset assembly (15) connected to the sliding support (11); The tail wing drive (13) is connected to the tail wing (12) to adjust the posture of the tail wing (12); Along the sliding direction of the sliding support (11), the support drive (14) and the reset assembly (15) are respectively connected to opposite ends of the sliding support (11); The support drive (14) comprises: a driver (141), and a controller (142) electrically connected to the driver (141); The reset component (15) comprises: a reset device (151), and a tension sensor (152) connected to the reset device (151); The controller (142) and the tension sensor (152) are fixedly supported on the inner side of the aircraft shell (a1); The controller (142) is electrically connected to the tension sensor (152) so as to control the magnitude of the sliding driving force of the driver (141) on the sliding support (11) based on an output signal of the tension sensor (152); The aircraft shell (a1) is provided with a guide groove (a11) for the sliding support (11) to slide.

8. The aircraft according to claim 7, characterized in that The support drive (14) further comprises: a first clamp (143), a second clamp (144), a pulley support (145) and a pulley (146); The pulley (146) is rotatably connected to the lower end of the pulley support (145); The pulley (146) is an insulating roller; Along the sliding direction of the sliding support (11) from the front initial position to the rear end position, the first clamp (143), the second clamp (144) and the pulley support (145) are arranged in sequence and spaced apart; The first clamp (143) and the pulley support (145) are fixedly supported on the inner side of the aircraft shell (a1), and the pulley support (145) is adjacent to the tail end of the aircraft shell (a1); The second clamp (144) is fixedly supported on the lower side of the sliding support (11), and the second clamp (144) is adjacent to the rear end of the sliding support (11); The driver (141) is bendably supported on the pulley (146), and two ends of the driver (141) are respectively fixedly connected to the first clamp (143) and the second clamp (144); The first clamp (143) and the second clamp (144) respectively use insulating members to fix the ends of the driver (141).

9. The aircraft according to claim 8, characterized in that The resetter (151) comprises: a return spring (151a) and a spring support (151b); The spring support (151b) is fixedly supported on the lower side of the pulley support (145), and the spring support (151b) is adjacent to the front end of the pulley support (145); When the front end of the sliding support (11) is in an initial position, the return spring (151a) is in an extended state; The tension sensor (152) is located in front of the spring support (151b), and the return spring (151a) is connected to the spring support (151b) and the tension sensor (152) respectively; The tension sensor (152) is fixedly connected to the inner side of the aircraft shell (a1).

10. The aircraft according to claim 9, characterized in that Sliding guide rails (a111) are respectively arranged on opposite sides of the guide groove (a11); The sliding support (11) is in the shape of a long strip as a whole, and sliding grooves (11a) are respectively provided at both ends of the sliding support (11) in the width direction; The sliding groove (11a) is slidably connected to match the sliding guide rail (a111).

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