A detachable tail structure for an eVTOL aircraft

Abstract

The utility model discloses a detachable tail wing structure of eVTOL aircraft, more particularly to related technical field of structure design, including flight stabilizing device, flight stabilizing device includes tail wing, tail wing one end symmetry is equipped with horizontal stabilizer plate, and the circumferential surface on the other end is fixedly connected with vertical stabilizer plate, still include clamping device for installing and disassembling to horizontal tail wing, sealing device for the junction of tail wing and horizontal tail wing is sealed. When needing to install horizontal stabilizer plate, the operator will push the clamping plate fixed to the end along the tail wing circumferential direction, then, the clamping plate first contacts and pushes the sliding block, thereby solve the tail wing in the installation and disassembly process can become complicated time -consuming, need the help of professional tool and personnel and carry out the tedious fastening and calibration, seriously reduce maintenance efficiency and attendance rate, finally may damage the aerodynamic integrity and reliability of connection structure, increase the problem of security hidden danger and operating cost.

Description

Technical Field

[0001] This utility model relates to the technical field of structural design, and more specifically, to a detachable tail structure for an eVTOL aircraft. Background Technology

[0002] A detachable tail structure for an eVTOL (electric vertical takeoff and landing) aircraft is a modular design, typically made of lightweight composite materials such as carbon fiber, and connected to the main fuselage via quick-connect components (such as pins, latches, or electronic interfaces). The primary function of this structure is to provide necessary pitch and yaw stability during flight, enhancing aerodynamic efficiency, especially improving lift-to-drag ratio and maneuverability during the cruise phase of a fixed-wing aircraft. Simultaneously, its detachable design facilitates ground storage, transportation, and maintenance, saving space and reducing operating costs, adapting to the high-density deployment requirements of urban air mobility (UAM). Furthermore, this structure allows for rapid replacement or upgrading of tail modules for different missions (such as cargo and passenger transport), enhancing the aircraft's versatility and adaptability.

[0003] Currently, the detachable tail fin of an existing eVTOL aircraft is complex and time-consuming to install and remove, requiring specialized tools and personnel for tedious tightening and calibration, which seriously reduces maintenance efficiency and uptime. Ultimately, it may damage the aerodynamic integrity and reliability of the connection structure, increasing safety hazards and operating costs.

[0004] Therefore, a detachable tail structure for an eVTOL aircraft is proposed to address the above problems. Utility Model Content

[0005] In order to overcome the above-mentioned defects of the prior art, the present invention provides a detachable tail structure for an eVTOL aircraft to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a detachable tail structure for an eVTOL aircraft, including a flight stabilization device, the flight stabilization device including a tail fin, one end of which is symmetrically provided with a horizontal stabilizing plate, and the other end of which is fixedly connected to a vertical stabilizing plate on its circumferential surface; it also includes a snap-fit ​​device for installing and removing the horizontal tail fin; a sealing device for sealing the connection between the tail fin and the horizontal tail fin; the snap-fit ​​device includes a snap-fit ​​plate, a sliding plate is provided below the snap-fit ​​plate, the snap-fit ​​device also includes a protective plate, a slider is provided inside the protective plate, one end of the slider is fixedly connected to a spring telescopic rod, the bottom of the slider is fixedly connected to a connecting rod, and the end of the connecting rod away from the slider is fixedly connected to a wedge.

[0007] Preferably, a locking block is provided on the side of the wedge away from the slider, a long rod is fixedly connected to the side of the locking block away from the wedge, a button plate is fixedly connected to the end of the long rod away from the locking block, and a protective shell is provided on the outside of the button plate.

[0008] Preferably, the protective plate has multiple grooves inside, the end of the spring telescopic rod away from the slider is fixedly connected to the inner wall surface of the groove inside the protective plate, the two ends of the connecting rod are respectively fixedly connected to the slider and the wedge, the protective shell has a cavity inside and is fixedly connected to the circumferential surface of the tail fin, and the end of the clamping plate away from the protective plate is fixedly connected to one end of the horizontal stabilizing plate.

[0009] Preferably, the sealing device further includes a support plate, a cylindrical plate passing through the interior of the support plate and rotatably connected to the support plate, both ends of the cylindrical plate being fixedly connected to a fixed plate, a spring being fixedly connected to the bottom of the support plate, an airbag being fixedly connected to the side of the support plate away from the spring, and a protective cover being fixedly connected to the circumferential surface of the airbag away from the support plate.

[0010] Preferably, a support plate is fixedly connected to the bottom end of the slide plate, and fixing plates are fixedly connected to both ends of the cylindrical plate.

[0011] Preferably, the protective cover is made of carbon fiber composite material, and the airbag is made of silicone rubber.

[0012] Preferably, a groove is formed on the circumferential surface of the tail fin, and an airbag is provided inside the groove. A rotator is provided at the end of the horizontal stabilizing plate away from the tail fin. A recess is formed on the side of the tail fin near the button panel. A rudder is fixedly connected to the side away from the tail fin. An elevator is fixedly connected to the side of the horizontal stabilizing plate near the vertical stabilizing plate.

[0013] The technical effects and advantages of this utility model are as follows:

[0014] 1. Compared with existing technologies, this detachable tail structure for an eVTOL aircraft solves the problem that when a horizontal stabilizing plate needs to be installed, the operator pushes a clamp fixed to its end along the circumference of the tail fin. Subsequently, the clamp first contacts and pushes the slider. This solves the problem that the installation and removal of the tail fin is complicated and time-consuming, requiring professional tools and personnel for tedious fastening and calibration, which seriously reduces maintenance efficiency and uptime, and may ultimately damage the aerodynamic integrity and reliability of the connection structure, increasing safety hazards and operating costs.

[0015] 2. Compared with the prior art, the detachable tail structure of this eVTOL aircraft, after the locking device completes the docking and locking, the sliding plate on the groove surface of the tail fin is squeezed by the locking plate, so that the sealing device can adapt to the angle deviation within a certain range during the docking process. This effectively prevents environmental media such as high-speed airflow, rainwater, and dust from entering the connection mechanism, avoids corrosion of key components and signal interference, and significantly improves the operational reliability of eVTOL under different weather conditions. Attached Figure Description

[0016] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0017] Figure 2 This is a three-dimensional structural diagram of the tail fin half-section of this utility model.

[0018] Figure 3 This is a three-dimensional structural diagram of the connecting rod and wedge block of this utility model.

[0019] Figure 4 This is a three-dimensional structural diagram of the airbag and protective cover of this utility model.

[0020] Figure 5 This is a three-dimensional structural diagram of the skateboard and support plate of this utility model.

[0021] Figure 6 This is a three-dimensional structural diagram of the cross-section of the protective plate of this utility model.

[0022] The attached figures are labeled as follows: 1. Flight stabilization device; 101. Tail fin; 102. Horizontal stabilizer plate; 103. Vertical stabilizer plate; 104. Rudder; 105. Elevator; 2. Snap-fit ​​device; 201. Snap-fit ​​plate; 202. Protective plate; 203. Slider; 204. Spring telescopic rod; 205. Connecting rod; 206. Wedge; 207. Snap-fit ​​block; 208. Long rod; 209. Button plate; 210. Protective shell; 3. Sealing device; 301. Slide plate; 302. Support plate; 303. Cylindrical plate; 304. Fixing plate; 305. Spring; 306. Airbag; 307. Protective cover. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Example 1

[0025] As attached Figures 1 to 6 The detachable tail structure of an eVTOL aircraft shown includes a flight stabilization device 1, which includes a tail 101. A horizontal stabilizing plate 102 is symmetrically provided at one end of the tail 101, and a vertical stabilizing plate 103 is fixedly connected to the circumferential surface of the other end. It also includes a snap-fit ​​device 2 for installing and removing the horizontal tail 101; and a sealing device 3 for sealing the connection between the tail 101 and the horizontal tail 101. The snap-fit ​​device 2 includes a snap-fit ​​plate 201, the bottom end of which is slidably connected to a groove surface on the circumferential surface of the tail 101. The snap-fit ​​device 2 also includes a protective plate 202, inside which is a slider 203. A spring telescopic rod 204 is fixedly connected to one end of the slider 203, and a connecting rod 205 is fixedly connected to the bottom of the slider 203. A wedge block 206 is fixedly connected to the end of the connecting rod 205 away from the slider 203.

[0026] A locking block 207 is provided on the side of the wedge block 206 away from the slider 203. A long rod 208 is fixedly connected to the side of the locking block 207 away from the wedge block 206. A button plate 209 is fixedly connected to the end of the long rod 208 away from the locking block 207. A protective shell 210 is provided on the outside of the button plate 209. The above design is beneficial to protect the button plate 209 through the external protective shell 210, thereby effectively preventing dust and accidental touch, and ensuring the accuracy and durability of the mechanism operation.

[0027] The guard plate 202 has multiple grooves inside. The end of the spring telescopic rod 204 away from the slider 203 is fixedly connected to the inner wall surface of the groove inside the guard plate 202. The two ends of the connecting rod 205 are fixedly connected to the slider 203 and the wedge 206, respectively. The protective shell 210 has a cavity inside and is fixedly connected to the circumferential surface of the tail fin 101. The end of the locking plate 201 away from the guard plate 202 is fixedly connected to one end of the horizontal stabilizing plate 102. By setting the two ends of the connecting rod 205 to be fixedly connected to the slider 203 and the wedge 206, when the slider 203 slides, the wedge 206 can be driven to slide synchronously through the connecting rod 205.

[0028] A groove is provided on the circumferential surface of the tail fin 101, and an airbag 306 is installed inside the groove. A rotator is provided on the end of the horizontal stabilizer plate 102 away from the tail fin 101. A recess is provided on the side of the tail fin 101 near the button plate 209. A rudder 104 is fixedly connected to the side away from the tail fin 101. An elevator 105 is fixedly connected to the side of the horizontal stabilizer plate 102 near the vertical stabilizer plate 103. The above design is advantageous because a recess is provided on the side of the tail fin 101 near the button plate 209, and when the button plate 209 is pressed, it can be pressed into this recess.

[0029] Specifically: First, when the horizontal stabilizing plate 102 needs to be installed, the operator pushes the locking plate 201 fixed at its end along the circumference of the tail fin 101. Then, the locking plate 201 first contacts and pushes the slider 203, thereby compressing the spring telescopic rod 204 in the groove of the guard plate 202 and sliding it backward. This movement drives the wedge block 206 to move synchronously through the connecting rod 205. When the locking plate 201 is completely slid into the tail fin 101, the end of the locking plate 201 away from the tail fin 101 disengages from the slider 203. Then, the compressed spring telescopic rod 204 resets, pushing the slider 203 forward and making it tightly contact the end of the locking plate 201 near the tail fin 101. Finally, the top of the locking plate 201 and the end of the slider 203 abut against each other, forming a self-locking mechanism, so that it cannot be pulled out. When disassembly is required, the operator presses the button plate 209 located in the cavity of the protective shell 210. This, along with the long rod 208 fixedly connected to it, pushes the locking block 207 inwards. The locking block 207 displaces, causing the wedge block 206 to slide towards the spring telescopic rod 204. As the wedge block 206 slides, it drives the slider 203 to move in the same direction via the connecting rod 205 fixedly connected to the bottom. This disengages one end of the slider 203 from the end of the locking plate 201 near the tail fin 101, eliminating the contact between the top of the locking plate 201 and the end of the slider 203. This allows the locking plate 201 to be pulled out of the tail fin 101. Once the constraint is released, the compressed spring... The spring telescopic rod 204 releases elastic potential energy, pushing the slider 203 to reset, and then the connecting rod 205 drives the wedge block 206 to slide back to the initial position, completing the quick disassembly. The sliding groove inside the guard plate 202 provides precise guidance for the moving parts, and the protective shell 210 effectively prevents dust and accidental contact, ensuring the accuracy and durability of the mechanism operation. This solves the problem that the installation and disassembly of the tail fin 101 becomes complicated and time-consuming, requiring professional tools and personnel for tedious tightening and calibration, which seriously reduces maintenance efficiency and attendance rate, and may ultimately damage the aerodynamic integrity and reliability of the connection structure, increasing safety hazards and operating costs.

[0030] Example 2

[0031] Based on Example 1, the solution in Example 1 will be further described in detail below with reference to the specific working method, such as... Figures 1 to 5 As shown below, see details:

[0032] As a preferred embodiment, a detachable tail structure for an eVTOL aircraft includes a sealing device 3 that further includes a support plate 302. A cylindrical plate 303 runs through the interior of the support plate 302 and is rotatably connected to it. Both ends of the cylindrical plate 303 are fixedly connected to a fixed plate 304. A spring 305 is fixedly connected to the bottom of the support plate 302. An airbag 306 is fixedly connected to the side of the support plate 302 away from the spring 305. A protective cover 307 is fixedly connected to the circumferential surface of the airbag 306 away from the support plate 302.

[0033] In a preferred embodiment, a support plate 302 is fixedly connected to the bottom end of the slide plate 301, and a fixing plate 304 is fixedly connected to both ends of the cylindrical plate 303. Since the support plate 302 is fixedly connected to the bottom end of the slide plate 301, when the slide plate 301 descends, it will drive the support plate 302 at the end connected to the slide plate 301 to descend.

[0034] As a preferred embodiment, the protective cover 307 is made of carbon fiber composite material, and the airbag 306 is made of silicone rubber. In the above design, the protective cover 307 is made of carbon fiber composite material, which can effectively resist high-speed airflow, rain erosion and foreign object intrusion.

[0035] The working process of this utility model is as follows: First, after the snap-fit ​​device 2 completes the docking and locking, the slide plate 301, which is slidably connected to the groove surface of the tail wing 101, is squeezed by the snap-fit ​​plate 201, which drives the support plate 302 fixedly connected to the bottom of the slide plate 301 and the connection point of the slide plate 301 to move downwards synchronously. When the connection point of the support plate 302 and the slide plate 301 is displaced, the cylindrical plate 303 passing through the inside of the support plate 302 is rotated, thereby causing one end of the spring 305 fixedly connected to the support plate 302 to rise. When the support plate 302 moves downwards, it pushes the airbag 306 fixedly connected to its top to press tightly against the connection gap. Then, the airbag 306 undergoes elastic deformation after being squeezed, adaptively filling the small irregular gaps caused by manufacturing tolerances or vibrations, forming the first airtight barrier, and further improving the sealing reliability and environmental protection. Furthermore, a protective cover 307 made of carbon fiber composite material is fixedly connected to the circumferential surface of the airbag 306 away from the support plate 302. Under the pre-tightening force of the spring 305, the protective cover 307 tightly covers the outside of the connection. It not only serves as a second physical barrier to effectively resist high-speed airflow, rainwater erosion, and foreign object intrusion, but its lightweight and high-strength characteristics also ensure the durability of the structure without adding significant weight. In addition, the support plate 302 is rotatably connected to the fixed plate 304 through the cylindrical plate 303, so that the sealing device 3 can adapt to a certain range of angular deviations during docking, ensuring uniform pressure on the sealing surface. This effectively prevents high-speed airflow, rainwater, dust, and other environmental media from intruding into the connection mechanism, avoiding corrosion of key components and signal interference, and significantly improving the operational reliability of eVTOL under different weather conditions.

[0036] The above describes the working principle of the detachable tail structure of this eVTOL aircraft.

Claims

1. A detachable tail structure for an eVTOL aircraft, comprising a flight stabilization device (1), the flight stabilization device (1) comprising a tail fin (101), wherein a horizontal stabilizing plate (102) is symmetrically provided at one end of the tail fin (101), and a vertical stabilizing plate (103) is fixedly connected to the circumferential surface of the other end; characterized in that, It also includes a snap-fit ​​device (2) for installing and removing the horizontal tail fin; A sealing device (3) is used to seal the connection between the tail fin (101) and the horizontal tail fin; The clamping device (2) comprises a clamping plate (201), and the lower portion of the clamping plate (201) is provided with a sliding plate (301) ， The clamping device (2) further comprises a guard plate (202), and the inner portion of the guard plate (202) is provided with a sliding block (203), one end of the sliding block (203) is fixedly connected with a spring telescopic rod (204), the bottom of the sliding block (203) is fixedly connected with a connecting rod (205), and the end, away from the sliding block (203), of the connecting rod (205) is fixedly connected with a wedge block (206).

2. A detachable tail structure for an eVTOL aircraft according to claim 1, characterized in that: A locking block (207) is provided on the side of the wedge (206) away from the slider (203). A long rod (208) is fixedly connected to the side of the locking block (207) away from the wedge (206). A button plate (209) is fixedly connected to the end of the long rod (208) away from the locking block (207). A protective shell (210) is provided on the outside of the button plate (209).

3. A detachable tail wing structure of an eVTOL aircraft according to claim 2, characterized in that: The guard plate (202) has multiple grooves inside. The end of the spring telescopic rod (204) away from the slider (203) is fixedly connected to the inner wall surface of the groove inside the guard plate (202). The two ends of the connecting rod (205) are respectively fixedly connected to the slider (203) and the wedge (206). The protective shell (210) has a cavity inside and is fixedly connected to the circumferential surface of the tail fin (101). The end of the clamping plate (201) away from the guard plate (202) is fixedly connected to one end of the horizontal stabilizing plate (102).

4. The detachable tail structure of an eVTOL aircraft according to claim 1, characterized in that: The sealing device (3) further includes a support plate (302), through which a cylindrical plate (303) passes and is rotatably connected to the support plate (302). The two ends of the cylindrical plate (303) are fixedly connected to a fixing plate (304). A spring (305) is fixedly connected to the bottom of the support plate (302). An airbag (306) is fixedly connected to the side of the support plate (302) away from the spring (305). A protective cover (307) is fixedly connected to the circumferential surface of the airbag (306) away from the support plate (302).

5. A detachable tail wing structure for an eVTOL aircraft as claimed in claim 4, characterized in that: The bottom end of the slide plate (301) is fixedly connected to a support plate (302), and the two ends of the cylindrical plate (303) are fixedly connected to fixing plates (304).

6. A detachable tail wing structure of an eVTOL aircraft according to claim 4, characterized in that: The protective cover (307) is made of carbon fiber composite material, and the airbag (306) is made of silicone rubber.

7. A detachable tail wing structure of an eVTOL aircraft according to claim 1, characterized in that: The tail fin (101) has a groove on its circumferential surface, and an airbag (306) is installed inside the groove. A rotator is installed at the end of the horizontal stabilizer plate (102) away from the tail fin (101). A recess is provided on the side of the tail fin (101) near the button plate (209). A rudder (104) is fixedly connected to the side away from the tail fin (101). An elevator (105) is fixedly connected to the side of the horizontal stabilizer plate (102) near the vertical stabilizer plate (103).

Images