Aircraft empennage synchronous telescopic device, synchronous telescopic method and aircraft

Abstract

The invention belongs to the field of aircrafts, and particularly relates to an aircraft empennage synchronous expansion device which comprises a first expansion piece and a second expansion piece which are used for connecting a wing body assembly and an empennage assembly, and the first expansion piece and the second expansion piece each comprise a fixed part and a movable part which are installed in a matched mode; the first expansion piece and the second expansion piece are connected through a transmission mechanism, the transmission mechanism is at least connected with a moving part of the first expansion piece and a moving part of the second expansion piece, and the transmission mechanism is used for synchronously driving the second expansion piece to contract when the first expansion piece is stressed to contract. The invention provides an aircraft empennage synchronous telescopic device which aims at solving the problem that in the prior art, the service life of an aircraft is shortened due to the fact that the single side of the aircraft is grounded in advance and telescopic devices are not synchronously contracted.

Description

Technical Field

[0001] This invention belongs to the field of aircraft, specifically relating to an aircraft tail fin synchronous telescopic device, synchronous telescopic method, and aircraft. Background Technology

[0002] Aircraft refer to all kinds of vehicles that fly within the Earth's atmosphere using their own power or aerodynamics. Their core characteristic is the ability to overcome ground constraints and achieve spatial transfer and operation of personnel, cargo, or mission equipment. The inventor's prior patent application (application number: CN202411822289.5) also proposed a vertical takeoff and landing fixed-wing aircraft. This aircraft can achieve vertical takeoff and landing and, compared to conventional pod-type designs, has a better streamlined shape, significantly reducing energy consumption during flight and increasing the range of small aircraft.

[0003] In a prior patent application (application number: CN202411822289.5), a wing-body assembly, a tail assembly, and a telescopic assembly were disclosed, with the tail assembly connected to the wing-body assembly via the telescopic assembly. The telescopic assembly can remain deployed during flight, thereby increasing the distance between the tail assembly and the wing-body assembly. This reduces the degree of deviation caused by airflow disturbances during flight and improves stability during handling. Simultaneously, the deployment of the telescopic assembly increases the effective lift area of ​​the aircraft due to the gap between the tail assembly and the wing-body assembly, while reducing the contact time between the airflow and the aircraft's surface. This reduces drag caused by friction between the aircraft surface and the air, thus reducing energy consumption and further improving the cruising capability of the small manned aircraft. Furthermore, during landing, the telescopic assembly acts as a buffer, especially during forced landings of small manned aircraft. When using parachutes or quadcopter-assisted landings to change the landing attitude, controlling and increasing the gas pressure within the telescopic assembly can effectively reduce or mitigate the impact damage to the aircraft from the ground, thereby ensuring the safety of the aircraft and personnel.

[0004] However, in practical use, it has been found that during landing, due to local airflow, manual operation during takeoff and landing, or a non-horizontal ground surface, the aforementioned aircraft is prone to premature contact with the ground on one side. When premature contact occurs, the telescopic component's telescopic joint will retract first, while the joint at the rear touchdown will retract later due to the clearance between components and the deformation of the tail fin's elastic component. This asynchronous force distribution on the two telescopic joints, especially under long-term takeoff and landing conditions and the impact of normal landings, will severely shorten the aircraft's lifespan. During a forced landing, the impact is even greater; if the two telescopic joints do not retract synchronously, they will not only fail to provide adequate cushioning and protection but may also cause the aircraft to disintegrate. Summary of the Invention

[0005] This invention provides a synchronous telescopic device, synchronous telescopic method, and aircraft tail fin, aiming to solve the problem of asynchronous retraction of the telescopic device when one side of the aircraft touches down prematurely in the prior art.

[0006] To solve the above-mentioned technical problems, the present invention provides a synchronous telescopic device for the tail fin of an aircraft, including a first telescopic member and a second telescopic member for connecting the wing-body assembly and the tail fin assembly, wherein both the first telescopic member and the second telescopic member include a fixed part and a movable part that are fitted together. The first telescopic joint and the second telescopic joint are connected by a transmission mechanism. The transmission mechanism is at least connected to the moving part of the first telescopic joint and the moving part of the second telescopic joint. The transmission mechanism is used to synchronously drive the second telescopic joint to contract when the first telescopic joint is contracted under force, or to synchronously drive the first telescopic joint to contract when the second telescopic joint is contracted under force.

[0007] Preferably, the transmission mechanism is a connecting component, one end of which is fixedly connected to the moving part of the first telescopic device, and the other end of which is fixedly connected to the moving part of the second telescopic device.

[0008] Preferably, the connecting component is a connecting plate or a connecting rod.

[0009] Multiple connecting components are provided.

[0010] The connecting component is connected to the front end of the moving part of the first telescopic device, and the connecting component is connected to the front end of the moving part of the second telescopic device.

[0011] Preferably, the transmission mechanism includes a first transmission component, a second transmission component, a mounting base, and a transmission shaft. The first transmission component is mounted on the mounting base and is connected to the first expansion joint. The second transmission component is mounted on the mounting base and is connected to the second expansion joint. The drive shaft is connected to the first and second drive components, and the drive shaft drives the first and second telescopic devices to contract synchronously by rotating.

[0012] Preferably, the first transmission assembly includes a first rack and a first gear, which are meshed together; the second transmission assembly includes a second rack and a second gear, which are meshed together. The two ends of the drive shaft are fixedly connected to the first gear and the second gear, and the drive shaft rotates through meshing transmission.

[0013] Preferably, the movable part of the first telescopic device is fixedly connected to the first rack, and the first gear is fixedly and rotatably mounted on the mounting base; The moving part of the second telescopic device is fixedly connected to the second rack, and the second gear is fixedly and rotatably mounted on the mounting base.

[0014] Preferably, the movable part of the first telescopic device is fixedly connected to the first rack, and the first gear is fixedly and rotatably mounted on the mounting base; The moving part of the second telescopic device is fixedly connected to the second rack, and the second gear is fixedly and rotatably mounted on the mounting base.

[0015] Preferably, the first transmission component includes a first toothed belt, a first mating wheel, and a first toothed pulley. The first mating wheel and the first toothed pulley are fixedly and rotatably mounted on the mounting base, and the first toothed belt meshes with the first mating wheel and the first toothed pulley. The first toothed belt is fixedly connected to the moving part of the first telescopic device. The second transmission assembly includes a second toothed belt, a second mating wheel, and a second toothed pulley. The second mating wheel and the second toothed pulley are fixedly and rotatably mounted on the mounting base. The second toothed belt meshes with the second mating wheel and the second toothed pulley. The second toothed belt is fixedly connected to the moving part of the second telescopic device. The drive shaft is fixedly connected to the first toothed pulley and the second toothed pulley, and the drive shaft rotates through belt drive.

[0016] Preferably, the first transmission assembly further includes a first tensioning pulley, which engages with the first toothed belt. The position of the first tensioning pulley is adjustable, thereby tensioning the first toothed belt.

[0017] The second transmission assembly also includes a second tensioning pulley, which engages with the second toothed belt. The position of the second tensioning pulley is adjustable, thereby tensioning the second toothed belt.

[0018] Preferably, it further includes a guide assembly for guiding the moving part, the guide assembly including a guide component and a mating component, the guide component and the mating component being fitted together.

[0019] Preferably, the guiding component is a guide hole, the guiding component is disposed in the moving part, and the mating component is a guide rod, the guide rod being accommodated inside the guide hole; Alternatively; the mating component is a guide rod, the mating component is disposed in the moving part, the guide component is a guide hole, and the guide rod is accommodated inside the guide hole.

[0020] Preferably, a shock-absorbing structure is provided between the fixed part and the movable part.

[0021] Preferably, the first telescopic device is a hydraulic cylinder or a pneumatic cylinder; The second telescopic device is a hydraulic cylinder or a pneumatic cylinder.

[0022] The second aspect of this invention discloses a method for synchronous extension and retraction of an aircraft tail fin, comprising the following steps: A first expansion joint and a second expansion joint are provided to connect with the wing-body assembly and the tail assembly; The first and second expansion joints are connected by a transmission mechanism; When the first telescopic member contracts under force, it drives the second telescopic member to extend and retract synchronously through the transmission mechanism, thereby causing the tail fin assembly to extend and retract synchronously; or, when the second telescopic member contracts under force, it drives the first telescopic member to extend and retract synchronously through the transmission mechanism, thereby causing the tail fin assembly to extend and retract synchronously.

[0023] A third aspect of the present invention discloses an aircraft, including the aforementioned synchronous telescopic device, wing-body assembly, tail assembly, and power assembly, wherein the wing-body assembly and tail assembly are connected via the aircraft tail synchronous telescopic device.

[0024] Preferably, the fixed portion of the first telescoping member and the fixed portion of the second telescoping member are connected to the wing-body assembly, and the movable portion of the first telescoping member and the movable portion of the second telescoping member are connected to the tail wing assembly.

[0025] Preferably, it also includes a power assembly, which comprises 2N+2 power units, where N is a natural number; the power unit includes a support and a vector force unit; one end of the support is fixedly connected to the wing-body assembly, and the other end is equipped with the vector force unit; the installation direction of the power unit is such that the direction of the thrust generated by the vector force unit should be consistent with the heading direction of the fixed-wing cruise flight state of the aircraft.

[0026] Preferably, the power unit is a multi-rotor.

[0027] The beneficial effects of this invention are as follows: This solution incorporates a transmission mechanism between the first and second telescopic joints. During aircraft landing, if the aircraft experiences a single-sided touchdown due to airflow, manual landing operations, or uneven ground, the transmission mechanism enables the first and second telescopic joints to retract synchronously, thereby solving the problem in the prior art where the asynchronous retraction of the first and second telescopic joints damages the aircraft's lifespan. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the synchronous telescopic device in Example 1.

[0029] Figure 2 This is a schematic diagram of the structure of the first expansion joint in Example 1.

[0030] Figure 3 This is a schematic diagram of the installation foundation in Example 1.

[0031] Figure 4 This is a schematic diagram of the synchronous telescopic device in Example 2.

[0032] Figure 5 This is an exploded view of the synchronous telescopic device in Example 2.

[0033] Figure 6 This is a schematic diagram of the synchronous telescopic device in Example 3.

[0034] Figure 7 This is an exploded view of the synchronous telescopic device in Example 3.

[0035] Figure 8 This is a schematic diagram of the synchronous telescopic device in Example 4.

[0036] Figure 9 This is a schematic diagram of the first belt drive assembly and the first belt drive assembly in Embodiment 4.

[0037] Figure 10 This is a schematic diagram of the first toothed belt in Example 4.

[0038] Figure 11 This is a schematic diagram of the installation foundation in Example 4.

[0039] Figure 12 This is a schematic diagram of the aircraft in Example 6.

[0040] The reference numerals in the accompanying drawings include: first telescopic device 1, fixed part 111, front cover 112, moving part 113, rear cover 114, second telescopic device 2, connecting part 3, mounting base 4, mounting plate 41, first meshing transmission assembly 5, first gear 52, first rack 51, first gear seat 53, first fixing ring 54, second meshing transmission assembly 6, second gear 62, second rack 61, second gear seat 63, second fixing ring 64, first belt drive assembly 7, first toothed belt 71, first toothed pulley 72, first mating pulley 73, first tension pulley 74, first mating ring 75, second belt drive assembly 8, second toothed belt 81, second toothed pulley 82, second mating pulley 83, second tension pulley 84, second mating ring 85, drive shaft 9, guide part 10, tail fin assembly 11, wing-body assembly 12, and power assembly 13. Detailed Implementation

[0041] To make the objectives, technical solutions, and advantages of the embodiments clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only for explaining the present invention and are not intended to limit the present invention.

[0042] Example 1 The basics are as follows: Figure 1 As shown, a synchronous telescopic device for the tail fin of an aircraft includes a first telescopic member 1, a second telescopic member 2, and a transmission mechanism.

[0043] In this embodiment, the first expansion joint 1 and the second expansion joint 2 preferably have the same structure and are symmetrically arranged. The following description uses the first expansion joint 1 as an example. Figure 2As shown, the first expansion joint 1 includes a movable part 113 and a fixed part 111, both of which are rod-shaped. A front cover 112 is provided at the front end of the fixed part 111 to close the front end of the fixed part 111. The front cover 112 is also equipped with an air source interface to ensure that gas can enter the interior of the first expansion joint 1 to provide movement power. A fixing seat is also provided at the front end of the fixed part 111 for connection with the mounting base 4. The fixing seat is annularly sleeved on the front end of the fixed part 111, and a stable connection with the mounting base 4 can be achieved by direct welding or by setting fasteners. The tail end of the fixed part 111 is accommodated inside the movable part 113, achieving a sealed and slidable fit between the fixed part 111 and the movable part 113. A buffer structure is also provided between the fixed part 111 and the movable part 113. The buffer structure can be a buffer pad or a conventional buffering method used in the prior art; the buffer structure used in the inventor's prior application can also be used here. The rear end of the movable part 113 is provided with a rear cover 114, which closes the rear end of the movable part 113, thus keeping the interior of the first telescopic member 1 in a closed state. A fixing seat is also provided at the rear end of the movable part 113, which can be connected to the component requiring telescopic movement by direct welding or by using fasteners. During retraction, the movable part 113 and the fixing part 111 move closer together; during extension, they move further apart.

[0044] It is understood that this embodiment provides a structure for a telescopic device, but in some implementations, the first telescopic device 1 and / or the second telescopic device 2 may also directly use cylinders, hydraulic cylinders or other telescopic structures commonly used in the prior art, as long as the telescopic effect can be achieved.

[0045] In this embodiment, the first telescopic joint 1 and the second telescopic joint 2 are arranged in parallel, with their ends respectively used to connect to the tail assembly 11 and the wing-body assembly 12. The first telescopic joint 1 and the second telescopic joint 2 are preferably fixedly connected to the tail assembly 11 and the wing-body assembly 12. However, in some embodiments, the connection between the first telescopic joint 1 and the second telescopic joint 2 and the tail assembly 11 may not be fixed, but other connection methods may be used. When both the first telescopic joint 1 and the second telescopic joint 2 are in the extended state, the distance between the tail assembly 11 and the wing-body assembly 12 increases; when both the first telescopic joint 1 and the second telescopic joint 2 are in the retracted state, the distance between the tail assembly 11 and the wing-body assembly 12 decreases. The extension and retraction of the first telescopic joint 1 and the second telescopic joint 2 adjusts the overall state of the aircraft. Simultaneously, when the aircraft lands, the first telescopic joint 1 and the second telescopic joint 2 retract due to the impact force during landing, thus providing a landing cushioning effect and lowering the height of the wing-body assembly 12, facilitating the loading and unloading of personnel or cargo.

[0046] To address the issue of the inability of the first telescopic member 1 and the second telescopic member 2 to retract synchronously, a transmission mechanism is installed between the first telescopic member 1 and the second telescopic member 2, forming a U-shaped structure between the transmission mechanism and the wing-body assembly 12. When the aircraft touches down prematurely on one side due to airflow, manual landing operation, or uneven ground, the first telescopic member 1 at the touchdown point retracts, and through the transmission mechanism, it drives the second telescopic member 2 to retract synchronously.

[0047] It is understandable that in practice, either the first expansion joint 1 or the second expansion joint 2 may ground first. When the first expansion joint is grounded first, the first expansion joint 1 drives the second expansion joint 2 to retract via the transmission mechanism; when the second expansion joint is grounded first, the second expansion joint 2 drives the first expansion joint 1 to retract via the transmission mechanism. It is not necessary for either the first expansion joint 1 or the second expansion joint 2 to ground first; in practice, either the first expansion joint 1 or the second expansion joint 2 may ground first, and in both states, the transmission mechanism can achieve synchronous retraction of both the first expansion joint 1 and the second expansion joint 2.

[0048] like Figure 3 As shown, the transmission mechanism in this embodiment is specifically a connecting component 3. The connecting component 3 is preferably a connecting plate with a relatively thin thickness to meet the weight reduction requirements of the aircraft. Multiple connecting plates can be provided, but two are preferred. The connection points are linked by connecting rods to improve connection strength. One end of the connecting component 3 is fixedly connected to the front end of the moving part 113 of the first telescopic member 1, and the other end of the connecting component 3 is fixedly connected to the front end of the moving part of the second telescopic member 2. The connection between the connecting component 3 and the moving part 113 can be achieved using existing connection methods such as welding, fastener connection, or bonding.

[0049] It is understood that in this embodiment, the connecting component 3 is preferably set as a connecting plate. However, in some other embodiments, the connecting component 3 can be a connecting rod, a connecting cylinder, or other connecting components 3, as long as the first telescopic member 1 and the second telescopic member 2 are fixedly connected.

[0050] To ensure more stable installation of the first expansion joint 1 and the second expansion joint 2, and to provide a mounting base for the transmission mechanism, this embodiment includes a mounting base 4. The mounting base 4 specifically comprises multiple parallel mounting plates 41, each with a first and a second receiving opening in its center. The first receiving opening accommodates the first expansion joint 1, preventing the mounting base 4 from interfering with its extension and retraction. The second receiving opening accommodates the second expansion joint 2, preventing the mounting base 4 from interfering with its extension and retraction. The mounting plates 41 can be connected to external structures via welding or fasteners to ensure the stability of the first expansion joint 1, the second expansion joint 2, and the transmission mechanism.

[0051] It is understandable that when the synchronous telescopic device in this embodiment is used on an aircraft, the wing body of the aircraft can be used directly as the installation base, without the need to configure a separate installation base 4, thereby reducing the use of parts and achieving weight reduction.

[0052] To guide the extension and retraction of the first telescopic member 1 and the second telescopic member 2, this embodiment provides guide components on both the first telescopic member 1 and the second telescopic member 2, further reducing the impact of structural deformation caused by impact on the contraction of the first telescopic member 1 and the second telescopic member 2. An example is the guide component provided on the first telescopic member 1. A guide member 10 is provided on the mounting base 4. The guide member 10 can be a guide rod and is in a straight line shape. The guide member 10 is arranged along the length direction of the first telescopic member 1. Simultaneously, a mating component, which is a guide hole, is provided on the moving part 113 of the first telescopic member 1, and the guide rod is accommodated within the guide hole. When the moving part 113 extends or retracts, the guide member 10 moves within the guide hole. Through the mating movement of the guide member 10 and the guide hole, the extension and retraction guidance of the moving part 113 and the fixed part 111 is achieved.

[0053] It is understood that in this embodiment, the guide component 10 is disposed on the mounting base 4, and the guide hole is disposed on the moving part. However, in some embodiments, the guide component 10 can be connected to the moving part, and the mating component can be disposed on the mounting base 4. Both methods can achieve telescopic guidance. Furthermore, the mating component is not limited to the guide hole; it can also be other guide structures found in the prior art.

[0054] The following detailed description illustrates the following implementation method: When the aircraft lands, if it touches down on one side due to airflow, manual landing operation, or uneven ground, the first expansion joint 1 (second expansion joint 2) at the touchdown point will contract under the impact force. When the first expansion joint 1 (second expansion joint 2) contracts under the force, the connecting component 3 can drive the second expansion joint 2 (first expansion joint 1) to expand and contract synchronously, ultimately achieving synchronized contraction of the first expansion joint 1 and the second expansion joint 2, thus overcoming the shortcomings of the prior art.

[0055] Example 2 The difference between this embodiment and Embodiment 1 is that, as Figure 4 and Figure 5 As shown, the transmission mechanism structure used in this embodiment is different.

[0056] In Embodiment 1, since the transmission mechanism is the connecting component 3, the connecting component 3 moves along with the moving part 113 of the telescopic device. Therefore, to avoid collisions, a movement opening (e.g., ...) needs to be provided on the mounting base 4 corresponding to the movement path of the connecting component 3. Figure 3(As shown). Obviously, the addition of the movement port resulted in a decrease in the connection strength of the mounting base 4.

[0057] To address the aforementioned problems, this embodiment preferably includes a first transmission assembly, a second transmission assembly, and a transmission shaft 9. The first transmission assembly is installed with the first expansion joint 1 via a mounting base 4, and the second transmission assembly is installed with the second expansion joint 2 via a mounting base 4. The mounting base 4 serves as the mounting foundation to ensure the stability of the first and second transmission assemblies. Simultaneously, both ends of the transmission shaft 9 are connected to the first and second transmission assemblies for transmission. When the first expansion joint 1 (second expansion joint 2) retracts, the first transmission assembly (second transmission assembly) drives the transmission shaft 9 to rotate. The rotating transmission shaft 9 then drives the second expansion joint 2 (first expansion joint 1) to retract via the second transmission assembly (first transmission assembly).

[0058] like Figure 4 and Figure 5 As shown. In this embodiment, the first transmission component is a first meshing transmission component 5, which includes a first rack 51 and a first gear 52. The first rack 51 is in the shape of a straight line and is arranged along the length direction of the first telescopic member 1. The first rack 51 is fixedly connected to the moving part 113 of the first telescopic member 1. Specifically, during installation, the first rack 51 can be installed by welding or by setting fasteners. In this embodiment, when the moving part 113 of the first telescopic member 1 extends or retracts, the first rack 51 will also move linearly accordingly; when the first rack 51 is driven by an external force to move linearly, the moving part 113 of the first telescopic member 1 will also extend or retract accordingly. The first gear 52 is in a meshing state with the first rack 51 and is fixedly connected to the first end of the transmission shaft 9. Specifically, during installation, the first gear 52 can be sleeved and installed on the first end of the transmission shaft 9. To ensure that the first gear 52 and the drive shaft 9 can stably adapt to the moving first rack 51, the first gear 52 is rotatably mounted on the first gear seat 53, which is fixedly connected to the mounting plate 41. By fixing the positions of the first gear 52 and the drive shaft 9, the first gear 52 and the drive shaft 9 are prevented from moving with the first rack 51.

[0059] To guide the moving part 113 of the first expansion joint 1, a guide member 10, which is a guide rod, is provided on the mounting base 4 in this embodiment. The moving part 113 of the first expansion joint 1 is connected to a mating member, which is a guide hole. When the moving part 113 extends or retracts, the guide rod moves inside the guide hole. Through the mating movement of the guide rod and the guide hole, the extension and retraction guidance of the moving part 113 and the fixed part 111 is achieved.

[0060] like Figure 4 and Figure 5As shown. The second transmission component in this embodiment is a second meshing transmission component 6, which specifically includes a second rack 61 and a second gear 62. The second rack 61 is in the shape of a straight line and is arranged along the length direction of the second telescopic member 2. The second rack 61 is fixedly connected to the moving part of the second telescopic member 2. Specifically, during installation, the second rack 61 can be installed by welding or by setting fasteners. When the moving part of the second telescopic member 2 extends or retracts, the second rack 61 will also move linearly accordingly; when the second rack 61 moves linearly, the moving part of the second telescopic member 2 will also extend or retract accordingly. The second gear 62 is in a meshing state with the second rack 61, and the second gear 62 is fixedly connected to the second end of the transmission shaft 9. Specifically, during installation, the second gear 62 can be sleeved and installed on the second end of the transmission shaft 9. In order to ensure that the second gear 62 and the transmission shaft 9 can stably adapt to the moving second rack 61, the second gear 62 is rotatably mounted on the second gear seat 63, and the second gear seat 63 is fixedly connected to the mounting plate 41. By fixing the positions of the second gear 62 and the drive shaft 9, the second gear 62 and the drive shaft 9 are prevented from moving with the second rack 61.

[0061] To guide the moving part of the second expansion joint 2, a guide component 10, which is a guide rod, is provided on the mounting base 4 in this embodiment. The moving part of the second expansion joint 1 is connected to a mating component, which is a guide hole. When the moving part extends or retracts, the guide rod moves inside the guide hole. Through the coordinated movement of the guide rod and the guide hole, the extension and retraction guidance of the moving part and the fixed part is achieved.

[0062] The specific transmission process is described below: When the aircraft lands, due to airflow, manual landing operation, or uneven ground, if the aircraft touches down on one side, the first telescopic device 1 (second telescopic device 2) at the touchdown point will retract due to the impact force. When the first telescopic device 1 (second telescopic device 2) retracts, the first rack 51 (second rack 61) moves linearly in tandem with the retraction of the first telescopic device (second telescopic device 2). Since the first rack 51 (second rack 61) is meshed with the first gear 52 (second gear 62), the linear movement of the first rack 51 (second rack 61) synchronously drives the first gear 52 (second gear 62) to rotate. Furthermore, since the first gear 52 (second gear 62) is fixedly connected to the drive shaft 9, when the first gear 52 (second gear 62) rotates, the drive shaft 9 also rotates. The rotating drive shaft 9 drives the second gear 62 (first gear 52) to rotate synchronously. Furthermore, since the second gear 62 (first gear 52) and the second rack 61 (first rack 51) are in a meshing transmission state, and the second rack 61 (first rack 51) is fixedly connected to the second telescopic device 2 (first telescopic device 1), the second gear 62 (first rack 51) can drive the second telescopic device (first telescopic device 1) to retract synchronously. Through the above transmission process, the second telescopic device (first telescopic device 1) retracts synchronously when the first telescopic device (second telescopic device 2) retracts.

[0063] Example 3 The difference between this embodiment and Embodiment 2 is that, as Figure 6 and Figure 7 As shown, the transmission mechanism in this embodiment is different.

[0064] In Embodiment 2, since the first rack 51 is installed at the retracted end of the first telescoping device 1 and the second rack 61 is installed close to the retracted end of the second telescoping device 2, due to the structural layout, the first rack 51 and the second rack 61 may not be fully embedded. The first rack 51 and the second rack 61 are in a state of being exposed at the tail of the wing-body assembly, which is not aesthetically pleasing and will also disrupt aerodynamics.

[0065] To address the aforementioned issues, the transmission mechanism in this embodiment is also configured to include a first transmission assembly, a second transmission assembly, and a transmission shaft 9. The first transmission assembly is installed in conjunction with the first telescopic member 1 via a mounting base 4, and the second transmission assembly is also installed in conjunction with the first telescopic member 1 via a mounting base 4. The mounting base 4 ensures the stable installation of both the first and second transmission assemblies. Simultaneously, both ends of the transmission shaft 9 are connected to the first and second transmission assemblies, respectively. In this embodiment, when the first telescopic member 1 (second telescopic member 2) retracts, the first transmission assembly (second transmission assembly) drives the transmission shaft 9 to rotate. Then, the rotating transmission shaft 9, in turn, drives the second telescopic member 2 (first telescopic member 1) to retract via the second transmission assembly (first transmission assembly).

[0066] like Figure 6 and Figure 7 As shown, the first transmission component in this embodiment is a first meshing transmission component 5, specifically including a first rack 51 and a first gear 52. The first rack 51 is fixedly connected to the mounting base 4. The first rack 51 is in the shape of a straight line, distributed along the length direction of the first telescopic member 1, and is parallel to the first telescopic member 1. During installation, the first rack 51 can be fixedly installed to the mounting base 4 by welding or by setting fasteners. A first fixing ring 54 is provided at the front end of the moving part 113 of the first telescopic member 1, and the first fixing ring 54 is sleeved on the front end of the moving part 113. The first gear 52 is rotatably mounted on the first fixing ring 54. Specifically, during installation, a rotating shaft can be set on the first fixing ring 54, and then the first gear 52 can be sleeved on the rotating shaft to achieve a rotatable connection of the first gear 52. The first gear 52 is fixedly connected to the transmission shaft 9, specifically, the first gear 52 can be sleeved on the first end of the transmission shaft 9. When the first gear 52 rotates, the transmission shaft 9 rotates accordingly. The first gear 52 and the first rack 51 are in a meshing state. When the first telescopic member 1 retracts, the moving part 113 of the first telescopic member 1 drives the first gear 52 to rotate and move along the setting direction of the first rack 51. When the first gear 52 is driven to rotate due to the rotation of the transmission shaft 9, the first gear 52 can also drive the first telescopic member 1 to retract.

[0067] It is understandable that, since the first gear 52 and the drive shaft 9 need to move along the first rack 51, a notch is provided on the mounting plate 41 corresponding to the movement path of the first gear 52 and the drive shaft 9, so as to avoid the mounting plate 41 interfering with the movement of the first gear 52 and the drive shaft 9.

[0068] To guide the moving part 113 of the first expansion joint 1, a guide member 10, which is a guide rod, is provided on the mounting base 4 in this embodiment. The moving part 113 of the first expansion joint 1 is connected to a mating member, which is a guide hole. When the moving part 113 extends or retracts, the guide rod moves inside the guide hole. Through the mating movement of the guide rod and the guide hole, the extension and retraction guidance of the moving part 113 and the fixed part 111 is achieved.

[0069] like Figure 6 and Figure 7 As shown, the second transmission component in this embodiment is a second meshing transmission component 6, which specifically includes a second rack 61 and a second gear 62. The second rack 61 is fixedly connected to the mounting base 4. The second rack 61 is in the shape of a straight line, distributed along the length direction of the second telescopic member 2, and is arranged parallel to the second telescopic member 2. During installation, the second rack 61 can be fixedly installed to the mounting base 4 by welding or by setting fasteners. A second fixing ring 64 is provided at the front end of the moving part of the second telescopic member 2, and the second fixing ring 64 is sleeved and installed at the front end of the moving part. The second gear 62 is rotatably installed on the second fixing ring 64. Specifically, during installation, a rotating shaft can be set on the second fixing ring 64, and then the second gear 62 can be sleeved and installed on the rotating shaft to achieve the rotatable connection of the second gear 62. The second gear 62 is fixedly connected to the transmission shaft 9, specifically, the second gear 62 can be sleeved and installed at the second end of the transmission shaft 9. When the second gear 62 rotates, the transmission shaft 9 rotates accordingly. The second gear 62 is also in a meshing state with the second rack 61. When the second telescopic member 2 retracts, the moving part of the second telescopic member 2 drives the second gear 62 to rotate and move along the direction set by the second rack 61. When the second gear 62 is driven to rotate due to the rotation of the transmission shaft 9, the second gear 62 can also drive the second telescopic member 2 to retract.

[0070] It is understandable that, since the second gear 62 and the drive shaft 9 need to move along the second rack 61, a notch is provided on the mounting plate 41 corresponding to the movement path of the second gear 62 and the drive shaft 9, so as to avoid the mounting plate 41 interfering with the movement of the second gear 62 and the drive shaft 9.

[0071] To guide the moving part of the second expansion joint 2, a guide component 10, which is a guide rod, is provided on the mounting base 4 in this embodiment. The moving part of the second expansion joint 1 is connected to a mating component, which is a guide hole. When the moving part extends or retracts, the guide rod moves inside the guide hole. Through the coordinated movement of the guide rod and the guide hole, the extension and retraction guidance of the moving part and the fixed part is achieved.

[0072] The specific transmission process is described below: When the aircraft lands, due to airflow, manual landing operation, or uneven ground, if the aircraft touches down on one side, the first telescopic device 1 (second telescopic device 2) at the touchdown point will retract due to the impact force. As the first telescopic device 1 (second telescopic device 2) retracts, the first gear 52 (second gear 62) follows the retraction of the first telescopic device (second telescopic device 2) and rotates linearly along the first rack 51 (second rack 61). Since the first gear 52 (second gear 62) is fixedly connected to the drive shaft 9, the drive shaft 9 also rotates when the first gear 52 (second gear 62) rotates. The rotating drive shaft 9 drives the second gear 62 (first gear 52) to rotate synchronously along the second rack 61 (first rack 51). Furthermore, since the second gear 62 (first gear 52) is fixedly connected to the second telescopic device 2 (first telescopic device 1), the second telescopic device 2 (first telescopic device 1) is driven to retract by the second gear 62 (first gear 52).

[0073] Example 4 The difference between this embodiment and embodiment 2 or embodiment 3 is that, as Figure 8 As shown, the structure of the transmission mechanism in this embodiment differs.

[0074] In Embodiment 2, since the first rack 51 is installed on the moving part 113 of the first telescopic member 1, and the second rack 61 is installed on the moving part of the second telescopic member 2, the first rack 51 and the second rack 61 cannot be embedded. They are exposed, which is aesthetically unappealing and also disrupts aerodynamics. In Embodiment 3, to allow space for the drive shaft 9, the first gear 52, and the second gear 62 to move, openings need to be provided at corresponding positions on the mounting base 4. These openings, however, reduce the strength of the mounting plate 41 (e.g., ...). Figure 7 (As shown).

[0075] To address the two problems mentioned above, this embodiment proposes a new transmission mechanism. For example... Figure 8 As shown, the transmission mechanism includes a first transmission assembly, a second transmission assembly, and a transmission shaft 9. The first transmission assembly is installed in conjunction with the first telescopic member 1 via a mounting base 4, and the second transmission assembly is also installed in conjunction with the first telescopic member 1 via a mounting base 4. The mounting base 4 ensures the stable installation of the first and second transmission assemblies. Simultaneously, both ends of the transmission shaft 9 are connected to the first and second transmission assemblies respectively. In this embodiment, when the first telescopic member 1 (second telescopic member 2) retracts, the first transmission assembly (second transmission assembly) drives the transmission shaft 9 to rotate. Then, the rotating transmission shaft 9, in turn, drives the second telescopic member 2 (first telescopic member 1) to retract via the second transmission assembly (first transmission assembly).

[0076] like Figure 9 and Figure 10 As shown, the first transmission component in this embodiment is a first belt transmission component 7, which includes a first toothed belt 71, a first mating pulley 73, and a first toothed pulley 72. Both the first mating pulley 73 and the first toothed pulley 72 are rotatably mounted on the mounting base 4. In implementation, support seats can be provided on the mounting base 4 at positions corresponding to the first toothed pulley 72 and the first mating pulley 73, respectively, with the first toothed pulley 72 and the first mating pulley 73 rotatably connected to their respective support seats. The first toothed belt 71 is sleeved on the first mating pulley 73 and the first toothed pulley 72, and the first mating pulley 73 and the first toothed pulley 72 tension the first toothed belt 71. The first toothed belt 71 can rotate between the first mating pulley 73 and the first toothed pulley 72. Simultaneously, both the first mating pulley 73 and the first toothed pulley 72 are provided with mating teeth that mesh with the first toothed belt 71 for transmission. The two ends of the first toothed belt 71 are fixedly connected to the moving part 113 of the first telescopic device 1, making the first toothed belt 71 annular in shape. To fix the first toothed belt 71 to the first telescopic device 1, a first mating ring 75 can be provided at the front end of the moving part 113 of the first telescopic device 1 during installation. The first mating ring 75 is sleeved and installed on the front end of the moving part 113 of the first telescopic device 1. The first mating ring 75 can be connected to the moving part 113 of the first telescopic device 1 by welding or fasteners. The first mating ring 75 can have mating holes. Fasteners are passed through the two ends of the first toothed belt 71 and connected to the first mating holes, thus achieving a fixed connection between the first toothed belt 71 and the moving part 113 of the first telescopic device 1. The first toothed pulley 72 is fixedly connected to the rotating shaft. When the first toothed pulley 72 rotates, the drive shaft 9 rotates accordingly. When the first telescopic device 1 retracts, it drives the first toothed belt 71 to rotate, and the first toothed pulley 72, the first mating pulley 73, and the drive shaft 9 all rotate synchronously. When the drive shaft 9 and the first toothed pulley 72 rotate, they can also drive the first toothed belt 71 to rotate, and the first toothed belt 71 drives the first telescopic device 1 to retract.

[0077] It is understandable that: Figure 10 As shown, in this embodiment, the first toothed belt 71 is not a one-piece ring, but a straight line, and the first toothed belt 71 has an end. Therefore, when maintenance is required, it is only necessary to disassemble the connection between the end of the first toothed belt 71 and the first telescopic device 1, and then the first toothed belt 71 can be removed.

[0078] To ensure the first toothed belt 71 is under tension, enabling stable transmission between the first mating pulley 73 and the first toothed belt pulley 72, this embodiment also includes a first tensioning pulley 74 mounted on the mounting base 4. The first tensioning pulley 74 is engaged with the first toothed belt 71. The position of the first tensioning pulley 74 is adjustable, thereby adjusting the tension of the first toothed belt 71.

[0079] like Figure 11 As shown, in order to guide the moving part 113 of the first telescopic device 1, a guide component 10, which is a guide rod, is provided on the mounting base 4 in this embodiment. The moving part 113 of the first telescopic device 1 is connected to a mating component. The mating component is a guide hole. When the moving part 113 moves in extension or retraction, the guide rod moves inside the guide hole. Through the mating movement of the guide rod and the guide hole, the extension and retraction guidance of the moving part 113 and the fixed part 111 is realized.

[0080] like Figure 9 As shown, the second transmission component in this embodiment is a second belt drive mechanism, which includes a second toothed belt 81, a second mating pulley 83, and a second toothed pulley 82. Both the second mating pulley 83 and the second toothed pulley 82 are rotatably mounted on the mounting base 4. In implementation, support seats can be provided on the mounting base 4 at positions corresponding to the second toothed pulley 82 and the second mating pulley 83, respectively, with the second toothed pulley 82 and the second mating pulley 83 rotatably connected to their respective support seats. The second toothed belt 81 is sleeved on the second mating pulley 83 and the second toothed pulley 82, and the second mating pulley 83 and the second toothed pulley 82 tension the second toothed belt 81. The second toothed belt 81 is supported by the second mating pulley 83 and the second toothed pulley 82, allowing the second toothed belt 81 to rotate. Simultaneously, both the second mating pulley 83 and the second toothed pulley 82 are provided with mating teeth that mesh with the second toothed belt 81 for transmission. The two ends of the second toothed belt 81 are fixedly connected to the moving part of the second expansion joint 2, making the second toothed belt 81 annular in shape. To fix the second toothed belt 81 to the second expansion joint, a second mating ring 85 can be installed at the front end of the moving part of the second expansion joint 2. The second mating ring 85 is sleeved and installed on the front end of the moving part of the second expansion joint 2. The second mating ring 85 can be connected to the moving part of the second expansion joint 2 by welding or fasteners. Mating holes can be provided on the second mating ring 85. Fasteners are passed through both ends of the second toothed belt 81 and then connected to the mating holes, thereby achieving a fixed connection between the second toothed belt 81 and the moving part of the second expansion joint 2. The second toothed pulley 82 is fixedly connected to the rotating shaft. When the second toothed pulley 82 rotates, the transmission shaft 9 rotates accordingly. When the second telescopic device 2 retracts, it drives the second toothed belt 81 to rotate, and the second toothed pulley 82, the second mating pulley 83, and the drive shaft 9 all rotate synchronously. When the drive shaft 9 and the second toothed pulley 82 rotate, they can also drive the second toothed belt 81 to rotate, and the second toothed belt 81 drives the second telescopic device 2 to retract.

[0081] It is understood that the second toothed belt 81 in this embodiment is not a one-piece ring, but rather a straight line, with an end portion. Therefore, when maintenance is required, it is only necessary to disassemble the connection between the end portion of the second toothed belt 81 and the second telescopic device 2, thereby removing the second toothed belt 81.

[0082] To ensure the second toothed belt 81 is under tension, enabling stable transmission between the second mating pulley 83 and the second toothed pulley 82, this embodiment also includes a second tensioning pulley 84 mounted on the mounting base 4. The second tensioning pulley 84 is engaged with the second toothed belt 81. The position of the second tensioning pulley 84 is adjustable, thereby adjusting the tension of the second toothed belt 81.

[0083] like Figure 11 As shown, in order to guide the moving part of the second expansion joint 2, a guide component 10, which is a guide rod, is provided on the mounting base 4 in this embodiment. The moving part of the second expansion joint 1 is connected to the mating component. The mating component is a guide hole. When the moving part extends or retracts, the guide rod moves inside the guide hole. Through the mating movement of the guide rod and the guide hole, the extension and retraction guidance of the moving part and the fixed part is achieved.

[0084] The specific transmission process is described below: When the aircraft lands, due to airflow, manual landing operation, or uneven ground, if the aircraft touches down on one side, the first expansion joint 1 (second expansion joint 2) at the touchdown point will contract due to the impact force. When the first expansion joint 1 (second expansion joint 2) contracts, it drives the first toothed belt 71 (second toothed belt 81) to rotate. Since the first toothed belt 71 (second toothed belt 81) and the first toothed pulley 72 (second toothed pulley 82) are in a meshing transmission state, and the first toothed pulley 72 (second toothed pulley 82) and the drive shaft 9 are in a fixed connection state, when the first toothed belt 71 (second toothed belt 81) rotates, the first toothed pulley 72 (second toothed pulley 82) and the drive shaft 9 rotate synchronously. The rotating drive shaft 9 drives the second toothed pulley 82 (first toothed pulley 72) to rotate, and the rotation of the second toothed pulley 82 (first toothed pulley 72) in turn drives the second toothed belt 81 (first toothed belt 71) to rotate. Since the second toothed belt 81 (first toothed belt 71) is connected to the moving part 113 of the second telescopic device 2 (first telescopic device 1), the second telescopic device 2 (first telescopic device 1) is also driven to retract.

[0085] Example 5 This embodiment provides a method for synchronous extension and retraction of the tail fin of an aircraft, which specifically includes the following steps.

[0086] A first telescoping member and a second telescoping member are provided to connect to the wing-body assembly and the tail assembly. Specifically, preferably, the fixed part of the first telescoping member and the fixed part of the second telescoping member are connected to the wing-body assembly, and the movable part of the first telescoping member and the movable part of the second telescoping member are connected to the tail assembly. The first telescoping member and the second telescoping member are fixedly connected to the wing-body assembly and the tail assembly.

[0087] A transmission mechanism is provided between the first and second expansion joints for transmission connection.

[0088] When the first telescopic member contracts under force, the second telescopic member contracts synchronously through the transmission mechanism, thereby enabling the tail fin assembly to contract synchronously; or, when the second telescopic member contracts under force, the first telescopic member contracts synchronously through the transmission mechanism, thereby enabling the tail fin assembly to contract synchronously.

[0089] Example 6 This embodiment discloses an aircraft, such as Figure 12 As shown, the aircraft includes a tail fin synchronous telescopic device according to Embodiment 1, Embodiment 2, Embodiment 3 or Embodiment 4, as well as a wing-body assembly 12, a tail fin assembly 11 and a power assembly.

[0090] In this embodiment, the first telescopic joint 1 and the second telescopic joint 2 of the aircraft tail fin synchronous telescopic device are connected to the wing-body assembly 12 and the tail fin assembly 11, respectively. The mounting base 4 in the aircraft tail fin synchronous telescopic device can be directly the inner frame of the wing-body assembly 12. When the first telescopic joint 1 and the second telescopic joint 2 are in the retracted state, the distance between the wing-body assembly 12 and the tail fin assembly 11 is shortened; when the first telescopic joint 1 and the second telescopic joint 2 are in the extended state, the distance between the wing-body assembly 12 and the tail fin assembly 11 is increased. Simultaneously, during aircraft landing, the first telescopic joint 1 and the second telescopic joint 2 are compressed under force, thereby providing a landing cushioning effect.

[0091] In this embodiment, the fixed part 111 of the first telescoping member 1 is preferably connected to the wing-body assembly 12, and the movable part 113 of the first telescoping member 1 is connected to the tail wing assembly 11. The fixed part 111 of the second telescoping member 2 is connected to the wing-body assembly 12, and the movable part of the second telescoping member 2 is connected to the tail wing assembly 11.

[0092] In this embodiment, the power assembly 13 includes 2N+2 power units, where N is a natural number. Each power unit includes a support frame and a vector force unit. One end of the support frame is connected to the wing-body assembly, and the other end is equipped with the vector force unit. The installation direction of the power units is such that the direction of the thrust generated by the vector force unit is consistent with the heading direction of the fixed-wing cruise flight state of the aircraft 1. The vector force unit is specifically either a propeller power unit or a jet power unit.

[0093] In this embodiment, the power assembly 13 includes four or six power units. For high safety requirements, six power units can be provided; for simpler structures, four power units can be provided. The power units in the power assembly 13 are arranged in a circumferential, equiangular array on the wing-body assembly 12.

[0094] The above descriptions are merely embodiments of the present invention, and common knowledge regarding specific structures and characteristics is not elaborated upon here. It should be noted that those skilled in the art can make various modifications and improvements without departing from the structure of the present invention, and these should also be considered within the scope of protection of the present invention. These modifications and improvements will not affect the effectiveness of the present invention or the practicality of the patent. The scope of protection claimed in this application should be determined by the content of its claims, and the specific embodiments described in the specification can be used to interpret the content of the claims.

Claims

1. A synchronous telescopic device for the tail fin of an aircraft, characterized in that: It includes a first telescoping member (1) and a second telescoping member (2) for connecting the wing-body assembly (12) and the tail assembly (11), and both the first telescoping member (1) and the second telescoping member (2) include a fixed part (111) and a movable part (113) that are fitted together. The first telescopic device (1) and the second telescopic device (2) are connected by a transmission mechanism. The transmission mechanism is at least connected to the moving part (113) of the first telescopic device (1) and the moving part of the second telescopic device (2). The transmission mechanism is used to synchronously drive the second telescopic device (2) to contract when the first telescopic device (1) is contracted by force, or to synchronously drive the first telescopic device (1) to contract when the second telescopic device (2) is contracted by force.

2. The aircraft tail fin synchronous telescopic device according to claim 1, characterized in that: The transmission mechanism is a connecting component (3), one end of which is fixedly connected to the moving part (113) of the first telescopic device (1), and the other end of which is fixedly connected to the moving part of the second telescopic device (2).

3. The aircraft tail fin synchronous telescopic device according to claim 2, characterized in that: The connecting component (3) is a connecting plate or a connecting rod; And / or; multiple connecting components (3) are provided; And / or; the connecting component is connected to the front end of the moving part of the first telescopic member (1), and the connecting component is connected to the front end of the moving part of the second telescopic member (2).

4. The aircraft tail fin synchronous telescopic device according to claim 1, characterized in that: The transmission mechanism includes a first transmission component, a second transmission component, a mounting base (4), and a transmission shaft (9). The first transmission component is mounted on the mounting base (4) and is connected to the first telescopic device (1). The second transmission component is mounted on the mounting base (4) and is connected to the second telescopic device (2). The drive shaft (9) is connected to the first transmission component and the second transmission component. The drive shaft (9) drives the first telescopic device (1) and the second telescopic device (2) to contract synchronously by rotating.

5. The aircraft tail fin synchronous telescopic device according to claim 4, characterized in that: The first transmission assembly includes a first rack (51) and a first gear (52), which are meshed together. The second transmission assembly includes a second rack (61) and a second gear (62), which are meshed together. The two ends of the drive shaft (9) are fixedly connected to the first gear (52) and the second gear (62), and the drive shaft (9) rotates through meshing transmission.

6. The aircraft tail fin synchronous telescopic device according to claim 5, characterized in that: The moving part (113) of the first telescopic device (1) is fixedly connected to the first rack (51), and the first gear (52) is fixedly and rotatably mounted on the mounting base (4); The moving part of the second telescopic device (2) is fixedly connected to the second rack (61), and the second gear (62) is fixedly and rotatably mounted on the mounting base (4).

7. The aircraft tail fin synchronous telescopic device according to claim 5, characterized in that: The moving part (113) of the first telescopic device (1) is fixedly and rotatably connected to the first gear (52), and the first rack (51) is fixedly installed on the mounting base (4); The moving part of the second telescopic device (2) is fixed and rotatably connected to the second gear (62), and the second rack (61) is fixedly installed on the mounting base (4).

8. The aircraft tail fin synchronous telescopic device according to claim 4, characterized in that: The first transmission assembly includes a first toothed belt (71), a first mating wheel (73), and a first toothed pulley (72). The first mating wheel (73) and the first toothed pulley (72) are fixedly and rotatably mounted on the mounting base (4). The first toothed belt (71) meshes with the first mating wheel (73) and the first toothed pulley (72). The first toothed belt (71) is fixedly connected to the moving part (113) of the first telescopic device (1). The second transmission assembly includes a second toothed belt (81), a second mating wheel (83), and a second toothed pulley (82). The second mating wheel (83) and the second toothed pulley (82) are fixedly and rotatably mounted on the mounting base (4). The second toothed belt (81) meshes with the second mating wheel (83) and the second toothed pulley (82). The second toothed belt (81) is fixedly connected to the moving part of the second telescopic device (2). The drive shaft (9) is fixedly connected to the first toothed pulley (72) and the second toothed pulley (82), and the drive shaft (9) rotates through belt drive.

9. The aircraft tail fin synchronous telescopic device according to claim 8, characterized in that: The first transmission assembly further includes a first tensioning pulley (74), which engages with the first toothed belt (71). The position of the first tensioning pulley (74) is adjustable so that the first toothed belt (71) is tensioned. And / or; the second transmission assembly further includes a second tensioning pulley (84), which engages with the second toothed belt (81), and the position of the second tensioning pulley (84) is adjustable so that the second toothed belt (81) is tensioned.

10. The aircraft tail fin synchronous telescopic device according to any one of claims 1 to 9, characterized in that: It also includes a guide assembly for guiding the moving part (113), the guide assembly including a guide member (10) and a mating member, the guide member (10) and the mating member being fitted together.

11. The aircraft tail fin synchronous telescopic device according to claim 10, characterized in that: The guide component (10) is a guide hole, the guide component (10) is disposed on the moving part (113), the mating component is a guide rod, and the guide rod is accommodated inside the guide hole; Alternatively; the mating component is a guide rod, the mating component is disposed on the moving part (113), the guide component (10) is a guide hole, and the guide rod is accommodated inside the guide hole.

12. The aircraft tail fin synchronous telescopic device according to any one of claims 1 to 9, characterized in that: A shock-absorbing structure is provided between the fixed part (111) and the moving part (113).

13. The aircraft tail fin synchronous telescopic device according to any one of claims 1 to 9, characterized in that: The first telescopic device (1) is a hydraulic cylinder or a pneumatic cylinder; And / or; the second telescopic device (2) is a hydraulic cylinder or a pneumatic cylinder.

14. A method for synchronous extension and retraction of an aircraft tail fin, characterized in that: Includes the following steps, A first expansion joint and a second expansion joint are provided to connect with the wing-body assembly and the tail assembly; The first and second expansion joints are connected by a transmission mechanism; When the first telescopic member contracts under force, it drives the second telescopic member to extend and retract synchronously through the transmission mechanism, thereby causing the tail fin assembly to extend and retract synchronously; or, when the second telescopic member contracts under force, it drives the first telescopic member to extend and retract synchronously through the transmission mechanism, thereby causing the tail fin assembly to extend and retract synchronously.

15. An aircraft, characterized in that: Includes the synchronous telescopic device, wing-body assembly (12), and tail assembly (11) as described in any one of claims 1 to 13, wherein the wing-body assembly (12) and tail assembly (11) are connected by the aircraft tail synchronous telescopic device.

16. The aircraft according to claim 15, characterized in that: The fixed part (111) of the first telescopic member (1) and the fixed part of the second telescopic member (2) are connected to the wing-body assembly (12), and the moving part (113) of the first telescopic member (1) and the moving part of the second telescopic member (2) are connected to the tail wing assembly (11).

17. The aircraft according to claim 15, characterized in that: It also includes a power assembly (13), which comprises 2N+2 power groups, where N is a natural number; The power unit includes a support frame and a vector force assembly; one end of the support frame is fixedly connected to the wing-body assembly (12), and the other end is equipped with the vector force assembly; the installation direction of the power unit is such that the direction of the thrust generated by the vector force assembly should be consistent with the heading direction of the fixed-wing cruise flight state of the aircraft.

18. The aircraft according to claim 17, characterized in that: The power unit (13) is a multi-rotor.

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