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

Abstract

The utility model relates to an empennage device for self-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 a reset assembly which are 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 utility model relates to the field of aerospace, and in particular to a tail wing device for adaptively adjusting the aerodynamic center of an aircraft and an aircraft. Background Art

[0002] During a rocket's flight, the position of the resultant aerodynamic force acting on it changes dynamically, influenced by a variety of factors, such as attitude, Mach number, and atmospheric conditions. Changes in the aerodynamic center of mass (ACC) can alter the rocket's static and dynamic stability. A mismatch between the ACC and the center of mass can lead to unstable attitude changes during flight. Furthermore, fuel consumption can cause ACC changes, adversely affecting the rocket's stability. To prevent this mismatch between the ACC and the aerodynamic center of mass, the traditional solution is to rationally design the rocket's mass distribution, positioning the ACC as far forward as possible while retaining a certain degree of redundancy. This ensures that the ACC remains behind the ACC at all stages of flight, ensuring stability during flight. However, if the ACC is too far back, the rocket's maneuverability will be adversely affected.

[0003] To address the above-mentioned issues and balance the stability and maneuverability of the rocket, and based on a thorough study of the characteristics of shape memory alloy materials, this patent designs a rocket aerodynamic center adaptive intelligent adjustment device and control method based on thermo-deformable shape memory alloy wire. This device can achieve the overall movement of the rocket's tail and adaptively adjust the position of the aerodynamic center in real time. Furthermore, the structure has the characteristics of a large deformation range, light weight, and simple structure, and has strong practical significance and good application prospects. The device is driven by thermo-deformable shape memory alloy wire, which controls the temperature of the alloy wire through electric current, and is equipped with a displacement feedback device that can control the axial position of the tail in real time as required. At the same time, since the four sets of tail devices are relatively independent, the device can also achieve independent axial displacement control of the rocket tail in four different positions as needed, providing an additional control torque for the aircraft. Utility Model Content

[0004] The purpose of the utility model is to provide a tail wing device for adaptively adjusting the aerodynamic center of an aircraft and an aircraft.

[0005] To achieve the above-mentioned purpose of the utility model, the utility model provides a tail device for adaptively adjusting the aerodynamic center of an aircraft, comprising: a sliding support, tail wings and tail wing drives arranged on both sides of the sliding support, and a support drive and reset assembly connected to the sliding support;

[0006] The tail drive is connected to the tail to adjust the posture of the tail;

[0007] Along the sliding direction of the sliding support, the support driving and reset components are respectively connected to the opposite ends of the sliding support;

[0008] The support drive includes: a driver, a controller electrically connected to the driver;

[0009] The reset assembly includes: a resetter, a tension sensor connected to the resetter;

[0010] The controller is electrically connected to the tension sensor to control the magnitude of the sliding driving force exerted by the driver on the sliding support based on an output signal of the tension sensor.

[0011] According to one aspect of the present invention, the driver is a shape memory alloy wire.

[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;

[0013] The pulley is rotatably connected to the lower end of the pulley support;

[0014] The pulley is an insulating roller;

[0015] 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;

[0016] 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;

[0017] 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;

[0018] The first clamp and the second clamp respectively use insulating members to fix the ends of the driver.

[0019] According to one aspect of the present invention, the resetter includes: a return spring and a spring support;

[0020] 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;

[0021] When the front end of the sliding support is in the initial position, the return spring is in an extended state;

[0022] 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.

[0023] 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.

[0024] According to one aspect of the present invention, an annular limiting groove is provided on the outer side surface of the pulley;

[0025] The driver is located in the annular limiting groove.

[0026] To achieve the above-mentioned purpose of the utility model, the utility model provides an aircraft using the aforementioned tail device, comprising: an aircraft body and a plurality of tail devices arranged on the aircraft body;

[0027] The aircraft body includes: an aircraft shell and a heat insulation structure arranged in the aircraft shell;

[0028] The thermal insulation structure is coaxial with the aircraft shell and spaced apart;

[0029] A plurality of tail fin devices are arranged at equal intervals along the circumference of the aircraft shell, and the tail fin devices are located between the heat insulation structure and the aircraft shell;

[0030] The tail device includes: a sliding support, tail wings and tail wing drives arranged on both sides of the sliding support, and a support drive and reset assembly connected to the sliding support;

[0031] The tail drive is connected to the tail to adjust the posture of the tail;

[0032] Along the sliding direction of the sliding support, the support driving and reset components are respectively connected to the opposite ends of the sliding support;

[0033] The support drive includes: a driver, a controller electrically connected to the driver;

[0034] The reset assembly includes: a resetter, a tension sensor connected to the resetter;

[0035] The controller and the tension sensor are fixedly supported on the inner side of the aircraft shell;

[0036] The controller is electrically connected to the tension sensor to control the sliding driving force of the driver on the sliding support based on the output signal of the tension sensor;

[0037] The aircraft shell is provided with a guide groove for the sliding support to slide.

[0038] 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;

[0039] The pulley is rotatably connected to the lower end of the pulley support;

[0040] The pulley is an insulating roller;

[0041] 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;

[0042] 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;

[0043] 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;

[0044] 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;

[0045] The first clamp and the second clamp respectively use insulating members to fix the ends of the driver.

[0046] According to one aspect of the present invention, the resetter includes: a return spring and a spring support;

[0047] 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;

[0048] When the front end of the sliding support is in the initial position, the return spring is in an extended state;

[0049] 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;

[0050] The tension sensor is fixedly connected to the inner side of the aircraft shell.

[0051] According to one aspect of the present invention, sliding guide rails are provided on opposite sides of the guide groove;

[0052] 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;

[0053] The sliding groove is matched with the sliding guide rail in a sliding connection.

[0054] According to one solution of the utility model, the utility model 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, it can offset the changes in the rocket's aerodynamic center caused by fuel consumption, changes in the flight Mach number, sudden changes in atmospheric conditions, etc., so that the rocket has both stability and maneuverability.

[0055] According to one embodiment of the present invention, the actuator is a shape memory alloy wire, which offers advantages such as a simple structure, a high power-to-weight ratio, and a high driving force, significantly improving the reliability and lightweighting of the structure. By increasing the diameter of the shape memory alloy wire, sufficient driving force can be generated, enabling the structure to withstand sufficient loads. Furthermore, the shape memory alloy wire can be replaced at any time, enabling the structure to be reused.

[0056] 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, which 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.

[0057] 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 thereby increasing the adjustable range of the rocket's aerodynamic center.

[0058] According to one solution of the utility model, the structure of the utility model is 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.

[0059] According to one solution of the present invention, the tail wing device designed based on 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.

[0060] According to one solution of the present invention, the present invention is based on a thermally deformable shape memory alloy wire that transforms from a non-twinned martensite phase to an austenite phase after heating, during which time it shrinks by approximately 8%, thereby driving the movement of the rocket's 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 returns to a non-twinned martensite phase under the tension of the return spring, and the shrinkage is restored. The total length of the shape memory alloy wire is relatively large, capable of generating a sufficiently large drive stroke. The thermally driven shape memory alloy wire utilizes electric current heating and natural convection cooling to achieve rapid back-and-forth deformation, providing sufficient drive force and drive stroke, and capable of withstanding a certain load. The device can adjust the position of the tail fin in real time according to external flight conditions and changes in its own internal state parameters, taking into account the rocket's aerodynamic stability and maneuverability. By relaxing the allowable position of the rocket's center of mass distribution, the device can also, to a certain extent, increase the freedom of the rocket's structural design.

[0061] According to one solution of the present invention, the present invention can clamp the shape memory alloy wire through the first clamp and the second clamp provided by screw connection. It is easy to disassemble, and the shape memory alloy wire can be disassembled and replaced at any time, which effectively improves the maintainability of the present invention.

[0062] According to one solution 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 in four different positions, providing an additional control torque to the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0063] Figure 1 is a perspective view of an aircraft schematically showing a tail device according to an embodiment of the present invention;

[0064] Figure 2 is a cross-sectional view of an aircraft schematically showing a tail device according to an embodiment of the present invention;

[0065] Figure 3 is a rear view of an aircraft schematically showing a tail device according to an embodiment of the present invention;

[0066] Figure 4 is a rear perspective view of an aircraft schematically showing a tail device according to an embodiment of the present invention;

[0067] Figure 5 is a perspective view schematically showing a first clamp or a second clamp according to an embodiment of the present invention;

[0068] Figure 6 is a perspective view schematically showing a reset assembly according to an embodiment of the present utility model;

[0069] Figure 7 is a perspective view schematically showing a length controller according to an embodiment of the present invention;

[0070] Figure 8 is a cross-sectional view schematically showing a length controller according to an embodiment of the present invention;

[0071] Figure 9 FIG. 1 is a control flow chart schematically showing a tail wing device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0072] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0073] When describing the embodiments of the present invention, the orientation or positional relationship expressed by the terms "longitudinal", "transverse", "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. 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, be constructed and operate in a specific orientation. Therefore, the above terms cannot be understood as limiting the present invention.

[0074] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. The embodiments cannot be described one by one here, but the embodiments of the present invention are not limited to the following embodiments.

[0075] Combine 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 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.

[0076] In this embodiment, the tail drive 13 is connected to the tail 12 to adjust the posture of the tail 12. The tail drive 13 can be configured as a rotary drive, whose shaft passes through the sliding support 11 to achieve connection with the tail 12, and is used to realize the rotation of the tail 12, thereby achieving the adjustment of the posture of the tail 12.

[0077] 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.

[0078] 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.

[0079] Combine 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 starting 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 Lowered to the martensite finish temperature M f When the shape memory alloy wire gradually transforms from the austenite phase to the austenite phase, the controller 142 electrically heats the driver 141 to control the contraction amount of the driver 141. The controller 142 can be an output voltage controller that is directly connected to the driver 141 to control the output voltage and electrically heat the driver 141, thereby maintaining a stable and controllable contraction amount of the driver 141.

[0080] Combine 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, 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 the ceramic roller method, 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.

[0081] In this embodiment, a first clamp 143, a second clamp 144, and a pulley support 145 are sequentially spaced along the direction of movement of the sliding support 11 from its forward initial position to its rearward end position. The second clamp 144 is fixedly supported on the underside of the sliding support 11 and adjacent to the rear end of the sliding support 11. In this embodiment, the driver 141 is bendably supported on a pulley 146, with its ends fixedly connected to the first clamp 143 and the second clamp 144, respectively. Since the driver 141 can be configured as a shape memory alloy wire, the pulley 146 can be used to control the steering of the driver 141, thereby conveniently connecting the two ends of the driver 141 to the first clamp 143 and the second clamp 144 located in front of the pulley support 145. Alligator clips or other connecting structures are used at opposite ends of the driver 141 to establish a point connection with the controller 142, thereby energizing the driver 141 with current from the controller 142.

[0082] like Figure 5 As shown, in this embodiment, the first clamp 143 and the second clamp 144 have the same structure, specifically comprising: a clamp column A and a clamp plate B. Clamp column A is generally a rectangular cylinder, while clamp plate B is generally a rectangular plate. In this embodiment, clamp plate B is connected to clamp column A using a threaded connector to clamp and secure the end of driver 141. To effectively ensure insulation between the first clamp 143 and the second clamp 144 and the driver 141, insulating members may be further provided between the first clamp 143 and the end of driver 141, and between the second clamp 144 and the end of driver 141, respectively. The insulating members may be provided as two opposing insulating sheets, one portion of which is fixedly connected to the end face of clamp column A, and the other portion of which is fixedly connected to the end face of clamp plate B. Thus, the clamp column A and clamp plate B are fixedly connected to each other to secure the end of driver 141, ensuring a reliable connection position and long-term stable operation. In this embodiment, the insulating sheet may be a polytetrafluoroethylene gasket.

[0083] 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.

[0084] 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 reinforcing ribs 1453 for connecting the support connecting plate 1451 and the pulley connecting plates 1452. In this embodiment, the support connecting plate 1451 is a rectangular plate, wherein the two pulley connecting plates 1452 are spaced apart and arranged relative to each other along the length of the support connecting plate 1451. In this embodiment, the reinforcing ribs 1453 are right-angled triangular plates, which are fixedly connected to the support connecting plate 1451 and the pulley connecting plate 1452 to ensure the stability and reliability of the entire pulley support 145 structure.

[0085] In this embodiment, the pulley 146 is disposed between the two pulley connecting plates 1452 and is rotatably connected to the ends of the pulley connecting plates 1452 via a rotating shaft.

[0086] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 and Figure 6 As shown, according to one embodiment of the present invention, the returner 151 includes a return spring 151a and a spring support 151b. In this embodiment, the spring support 151b is fixedly supported on the underside of the sliding support 11 and 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 extended state. Thus, the pretension provided by the return spring 151a enables the tail wing 12 to withstand a certain axial aerodynamic load during flight, thereby ensuring stable flight control.

[0087] Furthermore, 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 configured as a regularly shaped column, which can be configured as a circular cylinder or a rectangular column. A through hole can be provided on the spring support 151b to connect with the return spring 151a, thereby ensuring a stable and reliable connection.

[0088] Combine Figure 1 、 Figure 2 、 Figure 3 and Figure 4As shown, according to one embodiment of the present invention, the sliding support 11 is generally in the shape of a long strip, and sliding grooves 11a are respectively provided at both ends of the width direction of the sliding support 11. In this embodiment, the sliding grooves 11a are configured as rectangular grooves with a rectangular cross-section, which extend through both ends of the sliding support 11 along the length direction of the sliding support 11 to facilitate stable sliding of the sliding support 11.

[0089] Combine 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 surface of the pulley 146; in this embodiment, the driver 141 is in the annular limiting groove to achieve stable limitation of 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 guaranteed.

[0090] Combine 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. The length controller 141a comprises a mounting base 141a1 and a telescopic control assembly 141a2 mounted on the mounting base 141a1. The telescopic control assembly 141a2 is slidably connected to the mounting base 141a1, and the sliding direction of the telescopic control assembly 141a2 on the mounting base 141a1 is aligned with the length direction of the driver 141. In this embodiment, the driver 141 is partially wrapped around the telescopic control assembly 141a2, so that the telescopic movement of the telescopic control assembly 141a2 controls the rapid change in the length of the driver 141.

[0091] In this embodiment, the mounting base 141a1 includes a top plate 141a11 and side plates 141a12 disposed at opposite ends of the top plate 141a11. The two top plates 141a11 are located on the same side of the top plate 141a11. In this embodiment, a limiting sliding groove 141a121 is disposed on the side of the side plates 141a12 away from the top plate 141a11. The limiting sliding groove 141a121 is located on the inner side of the side plates 141a12, so that the limiting sliding grooves 141a121 on the two side plates 141a12 face each other, thereby achieving a sliding connection with the telescopic control assembly 141a2. In this embodiment, the limiting sliding groove 141a121 can be configured as a T-slot, so that the telescopic control assembly 141a2 can slide along the limiting sliding groove 141a121, effectively preventing the telescopic control assembly 141a2 from dislodging in a direction perpendicular to the limiting sliding groove 141a121. Through this arrangement, actuator 141 can synchronize its movement with the expansion and contraction control assembly 141a2 during thermal contraction, effectively ensuring the reliability and accuracy of actuator 141's movement. Furthermore, the mounting base 141a1 effectively supports the expansion and contraction control assembly 141a2 on actuator 141, effectively preventing the weight of actuator 141 from affecting its dimensions. Furthermore, this effectively prevents shaking of actuator 141 during actuation, further contributing to the stable operation of actuator 141.

[0092] In this embodiment, the telescopic control assembly 141a2 includes: arc portions 141a21 arranged opposite 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 provided 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 provided at the opening position on the arc portion 141a21 to limit the elastic connector 141a23 in the guide tube 141a211. Furthermore, the middle connector 141a22 is slidably connected to the guide tube 141a211, and under the pressure of the elastic connector 141a23, the middle connector 141a22 is elastically restricted, thereby realizing the telescopic movement of the two relative arc portions 141a21.

[0093] In this embodiment, the arc portion 141a21 can be set to a semicircular arc or a fan-shaped arc with a central angle less than 180°. By setting the arc portion 141a21 in different states, its quality can be controlled. 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.

[0094] 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. Among them, along the axial direction of the arc portion 141a21, the guide tube 141a21 can be set to one or multiple (such as two, three, etc.) at intervals.

[0095] In this embodiment, the middle connector 141a22 includes: a central support column 141a221, and guide columns 141a222 provided on opposite sides of the central support column 141a221; wherein the guide columns 141a222 are provided in a one-to-one correspondence 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 enabling the ends of the guide columns 141a222 to abut against the elastic connector 141a23; wherein the elastic connector 141a23 is configured as a compression spring, whereby, in the initial state, the two opposite arc portions 141a21 are arranged away from each other, wherein, in order to prevent the guide column 141a222 from falling out of 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 provided on the inner side of the end of the guide tube 141a211, thereby enabling the end of the guide column 141a222 to slide reliably in the guide tube 141a211.

[0096] In this embodiment, a movable connection structure is provided at opposite ends of the central support column 141a221. The movable connection structure includes a rotation-limiting portion and a sliding connection portion. The rotation-limiting portion and the sliding connection portion are sequentially arranged in a direction away from the central support column 141a221. The sliding connection portion has an area larger than that of the rotation-limiting portion, and the size of the rotation-limiting portion matches the small opening of the sliding groove 141a121. The sliding connection portion is connected to the large opening of the sliding groove 141a121. The rotation-limiting portion can be configured as a rectangular body, and the sliding connection portion can be configured as a rectangular column or a cylinder. Of course, in another embodiment, the sliding connection portion can be configured to be rotatable to reduce friction during movement.

[0097] In this embodiment, an insulating layer (e.g., an insulating plastic layer, a ceramic layer, etc.) is provided on the outer curved surface of the circular arc portion 141a21. Furthermore, a first mounting groove for mounting the telescopic limiting member 141a24 is provided on the outer curved surface of the circular arc portion 141a21. The telescopic limiting member 141a24 can be made of a shape memory alloy wire, e.g., a thermally deformable shape memory alloy, which is connected to the telescopic controller using a wire. In this embodiment, the telescopic limiting member 141a24 is wrapped around two opposite arc portions 141a21, and the telescopic limiting member 141a24 is wrapped when the two arc portions 141a21 are in an initial state (a state in which the two opposite arc portions 141a21 are away from each other). Thus, when the telescopic limiting member 141a24 is energized and heated, the two arc portions 141a21 move toward each other, thereby loosening the portion of the driver 141 wrapped around the two arc portions 141a21, thereby increasing the effective length of the driver 141, and enabling the resetter 151 to quickly reset the sliding support 11, thereby effectively increasing the flexible control of the reset of the sliding support 11.

[0098] In this embodiment, a second mounting groove for the driver 141 to be wound around is provided on the outer curved surface of the arc portion 141a21. The second mounting groove is located axially in the middle of the arc portion 141a21, while the first mounting groove can be provided on opposite sides of the second mounting groove. This allows for mounting telescopic limiting members 141a24 on either side of the second mounting groove to achieve rapid telescopic control response. In this embodiment, the radial depth of the first mounting groove on the arc portion 141a21 is less than that of the second mounting groove. This effectively increases the length of the telescopic limiting member 141a24, thereby increasing the range of motion between the two arc portions 141a21.

[0099] In this embodiment, to prevent the actuator 141 from compressing the two arcuate portions 141a21 of the telescopic control assembly 141a2 during thermal contraction, the insulating layer on the outer arcuate surface of the arcuate portion 141a21 is smooth to reduce friction between the actuator 141 and the arcuate portion 141a21. Furthermore, the elastic connector 141a23 is configured to offset the compression of the two arcuate portions 141a21 by the actuator 141, thereby effectively ensuring the precision of the actuator 141 during operation. Furthermore, to ensure rapid compression of the two arcuate portions 141a21 by the telescopic limiting member 141a24, the wire diameter and number of windings of the telescopic limiting member 141a24 can be flexibly configured to ensure effective operation of the telescopic limiting member 141a24.

[0100] 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.

[0101] 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.

[0102] 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.

[0103] Combine Figure 1 、 Figure 2 、 Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, an aircraft employing the aforementioned tail device is provided, comprising: an aircraft body a and a plurality of tail devices b disposed on the aircraft body a. In this embodiment, the aircraft body a comprises: an aircraft shell a1 and a heat-insulating structure a2 disposed within the aircraft shell a1. The heat-insulating structure a2 is coaxial with and spaced from the aircraft shell a1. The aircraft shell a1 can be cylindrical, and the corresponding heat-insulating structure a2 can also be cylindrical. The coaxial arrangement creates an annular space between the heat-insulating structure a2 and the aircraft shell a1 for mounting the tail devices b, thereby facilitating the installation of the tail devices b. Furthermore, the heat-insulating structure a2 allows for the installation of aircraft engines, nozzles, combustion chambers, and other structures within the heat-insulating structure a2, thereby separating them from the tail devices b. This prevents heat generated by the aircraft engines, nozzles, combustion chambers, and other structures from affecting the tail devices b, thereby ensuring reliable and stable operation of the tail devices b.

[0104] In this embodiment, multiple tail wing devices b are arranged at equal intervals along the circumference of the aircraft shell a1, and the tail wing devices b are located between the thermal insulation structure a2 and the aircraft shell a1. For example, if four tail wing devices b are provided, the four tail wing devices b can be arranged in a cross-shaped pattern along the circumference of the aircraft shell a1. In this embodiment, the tail wing device b includes: 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 connected to the sliding support 11, and a reset assembly 15. In this embodiment, the sliding support 11 serves as the main support for the tail wings 12 and tail wing drive 13. The sliding support 11 enables the overall movement of the tail wings 12 and tail wing drive 13, thereby flexibly adjusting the positions of the tail wings 12 and tail wing drive 13 along the sliding direction.

[0105] In this embodiment, the tail drive 13 is connected to the tail 12 to adjust the posture of the tail 12. The tail drive 13 can be configured as a rotary drive, whose shaft passes through the sliding support 11 to achieve connection with the tail 12, and is used to realize the rotation of the tail 12, thereby achieving the adjustment of the posture of the tail 12.

[0106] 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.

[0107] In this embodiment, the support drive 14 includes: a driver 141, a controller 142 electrically connected to the driver 141; and a reset assembly 15 includes: a resetter 151, and a tension sensor 152 connected to the resetter 151. 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 to control the magnitude of the sliding driving force exerted by 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. The guide groove a11 is provided to achieve directional and stable sliding of the sliding support 11, and the extension direction of the guide groove a11 is arranged to be consistent with the axial direction of the aircraft shell a1.

[0108] 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 using a wire.

[0109] Combine 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, 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 the ceramic roller method, 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.

[0110] In this embodiment, along the direction in which the sliding support 11 slides 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; 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 tail end of the aircraft shell a1; in this 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. In addition, the pulley support 145 provided can also realize the closure of the tail end of the guide groove a11 to prevent the sliding support 11 from falling out, thereby ensuring the stable and reliable installation of the sliding support 11.

[0111] 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. The first clamp 143, the second clamp 144, and the pulley support 145 are in the same straight line. The driver 141 can be bent and supported on the pulley 146, and the two ends of the driver 141 are respectively fixedly connected to the first clamp 143 and the second clamp 144. Since the driver 141 can be configured as a shape memory alloy wire, the pulley 146 can be used to control the steering of the driver 141, thereby conveniently connecting the two ends of the driver 141 to the first clamp 143 and the second clamp 144 located in front of the pulley support 145.

[0112] In this embodiment, the first clamp 143 and the second clamp 144 have identical structures, specifically comprising a clamp column A and a clamp plate B. Clamp column A is generally a rectangular cylinder, while clamp plate B is generally a rectangular plate. In this embodiment, clamp plate B is connected to clamp column A using a threaded connector to secure the end of driver 141. To effectively insulate the first and second clamps 143, 144 from the driver 141, insulating members may be provided between the first clamp 143 and the end of driver 141, and between the second clamp 144 and the end of driver 141. The insulating members may be provided as two opposing insulating sheets, one portion of which is fixedly connected to the end surface of clamp column A, while the other portion is fixedly connected to the end surface of clamp plate B. This securement of clamp column A and clamp plate B effectively insulates the end of driver 141, ensuring a secure connection and long-term stable operation. In this embodiment, the insulating sheets may be polytetrafluoroethylene gaskets.

[0113] 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.

[0114] 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 reinforcing ribs 1453 for connecting the support connecting plate 1451 and the pulley connecting plates 1452. In this embodiment, the support connecting plate 1451 is a rectangular plate, wherein the two pulley connecting plates 1452 are spaced apart and arranged relative to each other along the length of the support connecting plate 1451. In this embodiment, the reinforcing ribs 1453 are right-angled triangular plates, which are fixedly connected to the support connecting plate 1451 and the pulley connecting plate 1452 to ensure the stability and reliability of the entire pulley support 145 structure.

[0115] In this embodiment, the pulley 146 is disposed between the two pulley connecting plates 1452 and is rotatably connected to the ends of the pulley connecting plates 1452 via a rotating shaft.

[0116] Combine Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 and Figure 6As shown, according to one 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 is adjacent to the front end of the sliding support 11. In this embodiment, the return spring 151a, spring support 151b, tension sensor 152, first clamp 143, second clamp 144, and pulley support 145 are all located in the same linear direction. Consequently, the reset assembly 15 and the support drive 14 pull the sliding support 11 in the same direction, making the position of the sliding support 11 more accurate and flexible.

[0117] 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, thereby ensuring stable control of the flight.

[0118] 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. The tension sensor 152 is fixedly connected to the inside of the aircraft housing a1, thereby ensuring stable installation of the return spring 151a and conveniently enabling accurate measurement of the tension of the return spring 151a through the tension sensor 152. In this embodiment, the spring support 151b can be configured as a regularly shaped column, such as a circular cylinder or a rectangular column. A through-hole can be provided through the spring support 151b to connect to the return spring 151a, ensuring a stable and reliable connection.

[0119] Combine Figure 1 、 Figure 2 、 Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, sliding guide rails a111 are provided on opposite sides of the guide groove a11. In this embodiment, the sliding support 11 is generally in the shape of an elongated plate, and sliding grooves 11a are provided at both ends of the width direction of the sliding support 11. The sliding grooves 11a are slidably connected to the sliding guide rails a111. In this embodiment, the sliding guide rails a111 are made of an elongated plate, and their cross-sectional shape matches the cross-sectional shape of the sliding grooves 11a, thereby achieving stable and reliable installation of the sliding support 11.

[0120] Combine 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 surface of the pulley 146; in this embodiment, the driver 141 is in the annular limiting groove to achieve stable limitation of 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 guaranteed.

[0121] Combine 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. The length controller 141a comprises a mounting base 141a1 and a telescopic control assembly 141a2 mounted on the mounting base 141a1. The telescopic control assembly 141a2 is slidably connected to the mounting base 141a1, and the sliding direction of the telescopic control assembly 141a2 on the mounting base 141a1 is aligned with the length direction of the driver 141. In this embodiment, the driver 141 is partially wrapped around the telescopic control assembly 141a2, so that the telescopic movement of the telescopic control assembly 141a2 controls the rapid change in the length of the driver 141.

[0122] In this embodiment, the mounting base 141a1 includes a top plate 141a11 and side plates 141a12 disposed at opposite ends of the top plate 141a11. The two top plates 141a11 are located on the same side of the top plate 141a11. In this embodiment, a limiting sliding groove 141a121 is disposed on the side of the side plates 141a12 away from the top plate 141a11. The limiting sliding groove 141a121 is located on the inner side of the side plates 141a12, so that the limiting sliding grooves 141a121 on the two side plates 141a12 face each other, thereby achieving a sliding connection with the telescopic control assembly 141a2. In this embodiment, the limiting sliding groove 141a121 can be configured as a T-slot, so that the telescopic control assembly 141a2 can slide along the limiting sliding groove 141a121, effectively preventing the telescopic control assembly 141a2 from dislodging in a direction perpendicular to the limiting sliding groove 141a121. Through this arrangement, actuator 141 can synchronize its movement with the expansion and contraction control assembly 141a2 during thermal contraction, effectively ensuring the reliability and accuracy of actuator 141's movement. Furthermore, the mounting base 141a1 effectively supports the expansion and contraction control assembly 141a2 on actuator 141, effectively preventing the weight of actuator 141 from affecting its dimensions. Furthermore, this effectively prevents shaking of actuator 141 during actuation, further contributing to the stable operation of actuator 141.

[0123] In this embodiment, the top plate 141a11 can be installed on the inner side of the aircraft shell a1 using threaded connectors, wherein along the axial direction of the aircraft shell a1, the length controller 141a can be set to one or more.

[0124] In this embodiment, the telescopic control assembly 141a2 includes: arc portions 141a21 arranged opposite 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 provided 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 provided at the opening position on the arc portion 141a21 to limit the elastic connector 141a23 in the guide tube 141a211. Furthermore, the middle connector 141a22 is slidably connected to the guide tube 141a211, and under the pressure of the elastic connector 141a23, the middle connector 141a22 is elastically restricted, thereby realizing the telescopic movement of the two relative arc portions 141a21.

[0125] In this embodiment, the arc portion 141a21 can be set to a semicircular arc or a fan-shaped arc with a central angle less than 180°. By setting the arc portion 141a21 in different states, its quality can be controlled. 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.

[0126] 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. Among them, along the axial direction of the arc portion 141a21, the guide tube 141a21 can be set to one or multiple (such as two, three, etc.) at intervals.

[0127] In this embodiment, the middle connector 141a22 includes: a central support column 141a221, and guide columns 141a222 provided on opposite sides of the central support column 141a221; wherein the guide columns 141a222 are provided in a one-to-one correspondence 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 enabling the ends of the guide columns 141a222 to abut against the elastic connector 141a23; wherein the elastic connector 141a23 is configured as a compression spring, whereby, in the initial state, the two opposite arc portions 141a21 are arranged away from each other, wherein, in order to prevent the guide column 141a222 from falling out of 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 provided on the inner side of the end of the guide tube 141a211, thereby enabling the end of the guide column 141a222 to slide reliably in the guide tube 141a211.

[0128] In this embodiment, a movable connection structure is provided at opposite ends of the central support column 141a221. The movable connection structure includes a rotation-limiting portion and a sliding connection portion. The rotation-limiting portion and the sliding connection portion are sequentially arranged in a direction away from the central support column 141a221. The sliding connection portion has an area larger than that of the rotation-limiting portion, and the size of the rotation-limiting portion matches the small opening of the sliding groove 141a121. The sliding connection portion is connected to the large opening of the sliding groove 141a121. The rotation-limiting portion can be configured as a rectangular body, and the sliding connection portion can be configured as a rectangular column or a cylinder. Of course, in another embodiment, the sliding connection portion can be configured to be rotatable to reduce friction during movement.

[0129] In this embodiment, an insulating layer (e.g., an insulating plastic layer, a ceramic layer, etc.) is provided on the outer curved surface of the circular arc portion 141a21. Furthermore, a first mounting groove for mounting the telescopic limiting member 141a24 is provided on the outer curved surface of the circular arc portion 141a21. The telescopic limiting member 141a24 can be made of a shape memory alloy wire, e.g., a thermally deformable shape memory alloy, which is connected to the telescopic controller using a wire. In this embodiment, the telescopic limiting member 141a24 is wrapped around two opposite arc portions 141a21, and the telescopic limiting member 141a24 is wrapped when the two arc portions 141a21 are in an initial state (a state in which the two opposite arc portions 141a21 are away from each other). Thus, when the telescopic limiting member 141a24 is energized and heated, the two arc portions 141a21 move toward each other, thereby loosening the portion of the driver 141 wrapped around the two arc portions 141a21, thereby increasing the effective length of the driver 141, and enabling the resetter 151 to quickly reset the sliding support 11, thereby effectively increasing the flexible control of the reset of the sliding support 11.

[0130] In this embodiment, a second mounting groove for the driver 141 to be wound around is provided on the outer curved surface of the arc portion 141a21. The second mounting groove is located axially in the middle of the arc portion 141a21, while the first mounting groove can be provided on opposite sides of the second mounting groove. This allows for mounting telescopic limiting members 141a24 on either side of the second mounting groove to achieve rapid telescopic control response. In this embodiment, the radial depth of the first mounting groove on the arc portion 141a21 is less than that of the second mounting groove. This effectively increases the length of the telescopic limiting member 141a24, thereby increasing the range of motion between the two arc portions 141a21.

[0131] In this embodiment, to prevent the actuator 141 from compressing the two arcuate portions 141a21 of the telescopic control assembly 141a2 during thermal contraction, the insulating layer on the outer arcuate surface of the arcuate portion 141a21 is smooth to reduce friction between the actuator 141 and the arcuate portion 141a21. Furthermore, the elastic connector 141a23 is configured to offset the compression of the two arcuate portions 141a21 by the actuator 141, thereby effectively ensuring the precision of the actuator 141 during operation. Furthermore, to ensure rapid compression of the two arcuate portions 141a21 by the telescopic limiting member 141a24, the wire diameter and number of windings of the telescopic limiting member 141a24 can be flexibly configured to ensure effective operation of the telescopic limiting member 141a24.

[0132] 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.

[0133] 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.

[0134] 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.

[0135] To further illustrate this solution, the execution process of its control is further explained.

[0136] S1. Complete the tail device flight program design, equipment installation, commissioning and inspection during the ground preparation phase;

[0137] S2. After an aircraft (such as a missile / rocket) takes off, the tail fin 12 in the tail fin assembly needs to move axially during 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. To eliminate this effect, the axial position of the tail fin 12 can be adjusted. The specific implementation method is as follows: Figure 9As shown, controller 142 can calculate the required axial displacement of empennage 12 based on information transmitted by the aircraft's flight control computer and external sensors, generate a corresponding control signal, and then provide a voltage output to driver 141. Given parameters such as the stiffness coefficient and original length of resetter 151, controller 142 can calculate the actual position of axial sliding support 11 or empennage 12 based on the feedback signal from tension sensor 152 and control the voltage output. When the electrical heating power and heat dissipation power of driver 141 reach a balance, the temperature and deformation remain stable. For example, during flight, as the aircraft consumes fuel, the position of the aircraft's center of mass moves backward. If the aerodynamic center position does not match the center of mass position, this can cause the rocket to experience unstable attitude changes during flight. To prevent this, the position of empennage 12 needs to be moved backward, using the same method as described above. It should be noted that to ensure that empennage 12 can move axially forward and backward in both directions after takeoff, driver 141 should be initially heated to a mixed state of austenite and martensite before takeoff. In this embodiment, during 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.

[0138] S3. After the flight, perform equipment maintenance. If the aircraft is required to be recovered and reused, the integrity of the entire device will be assessed after the flight mission to determine whether some vulnerable structures and electronic components need to be repaired or replaced.

[0139] The above contents are merely examples of specific solutions of the present invention. For devices and structures not described in detail, it should be understood that they can be implemented by adopting common devices and methods available in the art.

[0140] The above description is only one embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection 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 drive (13) is connected to the tail (12) to adjust the posture of the tail (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) includes: a driver (141), a controller (142) electrically connected to the driver (141); The reset assembly (15) comprises: a resetter (151), a tension sensor (152) connected to the resetter (151); 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).

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

3. The tail wing device according to claim 2, characterized in that: The support drive (14) further includes: 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 tail end of the sliding support (11); The driver (141) is bendably supported on the pulley (146), and two ends of the driver (141) are fixedly connected to the first clamp (143) and the second clamp (144), respectively; 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 the 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.

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 fin 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 insulating structure (a2) is coaxial with the aircraft shell (a1) and 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 drive (13) is connected to the tail (12) to adjust the posture of the tail (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) includes: a driver (141), a controller (142) electrically connected to the driver (141); The reset assembly (15) comprises: a resetter (151), a tension sensor (152) connected to the resetter (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) 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 includes: 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 tail end of the sliding support (11); The driver (141) is bendably supported on the pulley (146), and two ends of the driver (141) are fixedly connected to the first clamp (143) and the second clamp (144), respectively; 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 the 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 provided 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 the sliding guide rail (a111) in a matching manner.

Images