A drone target aircraft catapult

Abstract

The utility model discloses an unmanned target aircraft ejector, including ejector body, the bottom of ejector body is installed with the rotary support seat, the bottom rotatoryly connected with the bottom plate of rotary support seat, the bottom installation of bottom plate has four support mechanisms, and the support mechanism includes horizontal telescopic stand and vertical telescopic stand, the horizontal telescopic stand is installed in the bottom of bottom plate, and the hole diameter difference and one -way valve's cooperation in the air cavity in -let hole and exhaust hole are installed between the horizontal telescopic stand with vertical telescopic stand, the horizontal telescopic stand is installed in the end portion of vertical telescopic stand, and vertical telescopic stand is installed in the bottom of connecting block, when the rebound force generates, forms effective damping buffer through the hole diameter difference and one -way valve's cooperation in the air cavity in -let hole and exhaust hole, and the overall tremor of device is weakened greatly, prevents each connecting part from appearing loose because of repeated tremor, reduces the shutdown overhaul frequency and maintenance cost, avoids target aircraft launch attitude deviation and device failure risk, improves the use stability and security of ejector.

Description

Technical Field

[0001] This utility model relates to the field of target drone catapult technology, specifically an unmanned target drone catapult. Background Technology

[0002] As a specialized device for launching unmanned target drones quickly, safely, and accurately from the ground to a designated initial position in the air, the core function of the unmanned target drone catapult is to replace the traditional runway takeoff method and effectively solve the takeoff requirements of unmanned target drones in short-distance, runway-less scenarios. It has been widely used in key areas such as military training and weapon system testing.

[0003] At the moment of launch and catapult release of a target drone, the catapult needs to provide sufficient initial kinetic energy to achieve stable ascent. During this process, the catapult is subjected to a reverse thrust generated by the target drone's reaction force. This reverse thrust causes significant downward pressure on the catapult itself, leading to overload and potential structural damage over time, shortening its lifespan and affecting launch reliability. To mitigate this issue, some target drone catapults now incorporate a buffer mechanism to absorb some of the impact force generated by the reverse thrust, thereby reducing the stress on the device itself.

[0004] However, after the existing buffer mechanism completes the force buffering, the internal elastic element will generate a rebound force due to deformation recovery. When this rebound force acts on the device body, it will cause the device to vibrate. This vibration will be continuously transmitted to the various connection parts of the device. Under long-term repeated action, it is easy to cause the connection parts to loosen. This not only requires frequent shutdowns for maintenance to retighten the connection parts, increasing maintenance costs and time, but may also cause the target drone to deviate in launch attitude or even malfunction during subsequent ejection. This seriously affects the stability and safety of the unmanned target drone ejector and makes it difficult to meet the requirements of efficient and reliable target drone launch.

[0005] Therefore, this utility model provides an unmanned target drone catapult. Utility Model Content

[0006] In view of the shortcomings of the existing technology, this utility model provides an unmanned target drone catapult to solve the above problems.

[0007] To achieve the above objectives, this utility model provides the following technical solution: an unmanned target drone catapult, comprising a catapult body, a rotating support base mounted on the bottom of the catapult body, a base plate rotatably connected to the bottom of the rotating support base, four support mechanisms mounted on the bottom of the base plate, each support mechanism including a horizontal telescopic frame and a vertical telescopic frame, the horizontal telescopic frame mounted on the bottom of the base plate, a connecting block mounted between the horizontal telescopic frame and the vertical telescopic frame, the connecting block mounted at the end of the horizontal telescopic frame, the vertical telescopic frame mounted at the bottom of the connecting block, a buffer mechanism provided at the bottom of each of the four connecting blocks, the buffer mechanism including an upper plate and a lower plate, a compression spring mounted between the upper plate and the lower plate, an air chamber mounted at the top of the lower plate, an arched column slidably connected to the inner wall of the air chamber, the arched column mounted at the bottom of the upper plate, air inlets on both sides of the air chamber, an inclined surface provided on the outer side of the air chamber to accommodate the air inlets, an exhaust port at the bottom of the air chamber, and a one-way valve mounted on the inner wall of the exhaust port.

[0008] Preferably, a guide rod is installed at the top of the lower plate, the guide rod passes through the top of the upper plate, and a limiting plate is installed at the top of the guide rod, the limiting plate being slidably connected to the inner wall of the vertical telescopic frame.

[0009] Preferably, the lower plate has an air passage that is spatially connected to the exhaust port, and the bottom of the lower plate has an anti-slip groove.

[0010] Preferably, an installation ring is installed on the outside of the air cavity, and the installation ring is detachably connected to the top of the lower plate by bolts, and the arched column is detachably connected to the bottom of the upper plate by bolts.

[0011] Preferably, an L-shaped lifting rod is slidably connected to the inner wall of the vertical telescopic frame, and a baffle is installed at the bottom of the L-shaped lifting rod, with the baffle contacting the top of the limiting plate.

[0012] Preferably, the L-shaped lifting rod extends outward from the vertical telescopic frame, and a screw is rotatably connected to the inner wall of the L-shaped lifting rod. A threaded fixing block is threadedly connected to the outer side of the screw, and the threaded fixing block is installed on the side wall corresponding to the vertical telescopic frame.

[0013] Compared with the prior art, the present invention has the following advantages: (1) The downward pressure generated by the reverse thrust is directly absorbed by the compression spring, avoiding structural damage caused by overload of the device body. The deformation of the compression spring absorbs most of the downward impact force, initially alleviating the overload of the catapult body.

[0014] (2) By using the difference in the diameter of the air inlet and outlet in the air chamber and the cooperation of the one-way valve, an effective damping buffer is formed when the rebound force is generated, which greatly reduces the overall vibration of the device, prevents the connection parts from becoming loose due to repeated vibration, reduces the frequency of shutdown and maintenance and maintenance costs, avoids the target machine's launch attitude deviation and the risk of device failure, and improves the stability and safety of the catapult. Attached Figure Description

[0015] Figure 1 This is a three-dimensional structural schematic diagram of the present invention; Figure 2 This is the utility model Figure 1 A magnified view of the structure at point A in the middle; Figure 3 This is a three-dimensional enlarged cross-sectional view of the buffer mechanism and other components in this utility model. Figure 1 ; Figure 4 This is a three-dimensional enlarged cross-sectional view of the buffer mechanism and other components in this utility model. Figure 2 .

[0016] In the diagram: 1. Catapult body; 11. Rotating support base; 12. Base plate; 2. Support mechanism; 21. Lateral telescopic frame; 22. Vertical telescopic frame; 23. Connecting block; 3. Buffer mechanism; 31. Upper plate; 32. Lower plate; 321. Air passage; 322. Anti-slip groove; 33. Compression spring; 34. Guide rod; 341. Limiting plate; 4. Air chamber; 41. Arched column; 411. Inclined surface; 42. Mounting ring; 43. Air inlet; 44. Exhaust port; 45. One-way valve; 5. L-shaped lifting rod; 51. Baffle; 52. Screw; 53. Threaded fixing block. Detailed Implementation

[0017] 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.

[0018] Please see Figure 1-4An unmanned target drone catapult includes a catapult body 1. A rotating support base 11 is installed at the bottom of the catapult body 1. A base plate 12 is rotatably connected to the bottom of the rotating support base 11. Four support mechanisms 2 are installed at the bottom of the base plate 12. Each support mechanism 2 includes a horizontal telescopic frame 21 and a vertical telescopic frame 22. The horizontal telescopic frame 21 is installed at the bottom of the base plate 12. A connecting block 23 is installed between the horizontal telescopic frame 21 and the vertical telescopic frame 22. The connecting block 23 is installed at the end of the horizontal telescopic frame 21, and the vertical telescopic frame 22 is installed at the bottom of the connecting block 23. A buffer mechanism 3 is provided at the bottom of each of the four connecting blocks 23.

[0019] The buffer mechanism 3 includes an upper plate 31 and a lower plate 32. A compression spring 33 is installed between the upper plate 31 and the lower plate 32. An air chamber 4 is installed at the top of the lower plate 32. An arched column 41 is slidably connected to the inner wall of the air chamber 4. The arched column 41 is installed at the bottom of the upper plate 31. Air inlets 43 are provided on both sides of the air chamber 4. An inclined surface 411 is provided on the outer side of the air chamber 4 to accommodate the air inlets 43. An exhaust port 44 is provided at the bottom of the air chamber 4. A one-way valve 45 is installed on the inner wall of the exhaust port 44.

[0020] It should be noted that, in this embodiment, the upper plate of the air chamber 4 is connected to the upper plate 31, and the lower plate of the air chamber 4 is located inside the air chamber 4 to form a piston. When the arched column 41 descends with the upper plate 31, the one-way valve 45 opens. When the arched column 41 rises with the upper plate 31, the air chamber 4 takes in air through the air inlet 43. The diameter of the air inlet 43 is smaller than the diameter of the exhaust port 44.

[0021] Specifically, the catapult body 1 achieves angle changes through the rotating support base 11 and the base plate 12, making it flexible in use. After the unmanned target drone completes preparation on the catapult body 1, it initiates the catapult launch. At the moment of launch, the thrust generated by the target drone causes the catapult body 1 to bear downward pressure. This pressure is transmitted sequentially to the rotating support base 11 and the base plate 12, which in turn drives the horizontal telescopic frame 21 and the vertical telescopic frame 22 of the four support mechanisms 2 at the bottom of the base plate 12 to be simultaneously stressed. The pressure is transmitted to the buffer mechanism 3 through the connecting block 23. At this time, the upper plate 31 of the buffer mechanism 3 moves towards the lower plate 32 under the action of pressure, compressing the compression spring 33 between the upper plate 31 and the lower plate 32. At the same time, the arched column 41 at the bottom of the upper plate 31 slides downward along the inner wall of the air chamber 4. Because the lower plate of the air chamber 4 forms a piston structure, the air pressure inside the air chamber 4 increases when the arched column 41 moves downward, pushing the one-way valve 45 in the exhaust port 44 to open. Gas is quickly discharged from the exhaust port 44, and the deformation of the compression spring 33 absorbs most of the downward impact force, initially alleviating the overload of the catapult body 1. When the buffering process ends, the compression spring 33 generates an upward rebound force due to the recovery of its deformation, pushing the upper plate 31 and the arched column 41 to move upward. At this time, the one-way valve 45 closes, and a negative pressure is formed inside the air chamber 4. External gas enters the air chamber 4 through the air inlet 43. Because the diameter of the air inlet 43 is smaller than that of the exhaust port 44, the gas enters at a slower speed, forming a damping effect inside the air chamber 4, slowing down the upward speed of the arched column 41, thereby weakening the impact of the rebound force. Meanwhile, the inclined surface 411 on the outside of the air chamber 4 provides sufficient air intake space for the air intake port 43, ensuring smooth air intake. The horizontal telescopic frame 21 and the vertical telescopic frame 22 can be used in conjunction with the buffer mechanism 3 to adjust the support angle, while the rotating support seat 11 ensures that the catapult body 1 is stable in attitude during the buffering process.

[0022] This structure directly absorbs the downward pressure generated by the counter-thrust through the compression spring 33, avoiding structural damage caused by overload of the device body; at the same time, by utilizing the difference in diameter between the air inlet 43 and the exhaust port 44 in the air chamber 4 and the cooperation of the one-way valve 45, an effective damping buffer is formed when the rebound force is generated, which greatly reduces the overall vibration of the device, prevents the connection parts from loosening due to repeated vibration, reduces the frequency of downtime for maintenance and maintenance costs, avoids the target drone launch attitude deviation and device failure risk, and improves the stability and safety of the catapult.

[0023] In one embodiment of this utility model, such as Figures 1-4 As shown, a guide rod 34 is installed at the top of the lower plate 32. The guide rod 34 passes through the top of the upper plate 31. A limit plate 341 is installed at the top of the guide rod 34. The limit plate 341 is slidably connected to the inner wall of the vertical telescopic frame 22.

[0024] Specifically, when the upper plate 31 of the buffer mechanism 3 moves downward under pressure or upward under rebound force, the guide rod 34 moves synchronously along the through hole of the upper plate 31. The limiting plate 341 slides on the inner wall of the vertical telescopic frame 22, providing precise guidance for the movement of the guide rod 34 and the upper plate 31, ensuring that the upper plate 31 always stays on the preset movement trajectory when it approaches or moves away from the lower plate 32, so that the compression spring 33 can be evenly stressed, and the arched column 41 in the air chamber 4 can also slide smoothly along the inner wall of the air chamber 4, ensuring that the buffering and damping process is stable.

[0025] In one embodiment of this utility model, such as Figures 1-4 As shown, an air passage 321 is provided on the lower plate 32, and the air passage 321 is spatially connected with the exhaust hole 44. An anti-slip groove 322 is provided at the bottom of the lower plate 32.

[0026] Specifically, when the one-way valve 45 inside the air chamber 4 opens, the gas discharged from the exhaust port 44 will circulate through the air passage 321, which is connected to the exhaust port 44. This guides the gas, helping it to be discharged more orderly and assisting in the stable realization of the damping effect within the air chamber 4. At the same time, the anti-slip groove 322 at the bottom of the lower plate 32 increases the friction between the lower plate 32 and the placement surface, improving the stability of the entire catapult during operation and preventing sliding displacement of the catapult due to factors such as thrust or rebound force.

[0027] In one embodiment of this utility model, such as Figures 1-4 As shown, an installation ring 42 is installed on the outside of the air chamber 4. The installation ring 42 is detachably connected to the top of the lower plate 32 by bolts, and the arched column 41 is detachably connected to the bottom of the upper plate 31 by bolts.

[0028] Specifically, the air chamber 4 is detachably connected to the top of the lower plate 32 via bolts through its outer mounting ring 42. This allows the air chamber 4 to be stably installed in a predetermined position. It also facilitates quick removal from the lower plate 32 for inspection, replacement, or maintenance should wear, leakage, or internal one-way valve 45 malfunction occur. Similarly, the arched column 41 is detachably connected to the bottom of the upper plate 31 via bolts. This ensures that the arched column 41 moves synchronously with the upper plate 31 to cooperate with the air chamber 4 in providing damping and buffering. Furthermore, it allows for easy disassembly and replacement when the arched column 41 experiences surface wear or structural damage due to long-term sliding, without requiring extensive disassembly of the entire buffer mechanism 3. This detachable connection design ensures the assembly stability of the air chamber 4 and the arched column 41, while significantly improving the convenience of component maintenance and ensuring the continuous and efficient operation of the buffer mechanism 3.

[0029] In one embodiment of this utility model, such as Figures 1-4As shown, an L-shaped lifting rod 5 is slidably connected to the inner wall of the vertical telescopic frame 22. A baffle 51 is installed at the bottom of the L-shaped lifting rod 5, and the baffle 51 contacts the top of the limiting plate 341.

[0030] Specifically, by using the L-shaped lifting rod 5 to drive the baffle 51 to move up and down, the vertical movement range of the limit plate 341 can be dynamically constrained, and the buffer range can be adjusted to meet different UAV launch requirements.

[0031] In one embodiment of this utility model, such as Figures 1-4 As shown, the L-shaped lifting rod 5 extends outward from the vertical telescopic frame 22. The inner wall of the L-shaped lifting rod 5 is rotatably connected to a screw 52. The outer side of the screw 52 is threadedly connected to a threaded fixing block 53, which is installed on the side wall of the corresponding vertical telescopic frame 22.

[0032] Specifically, the L-shaped lifting rod 5 is precisely positioned by the threaded engagement of the screw 52 and the threaded fixing block 53, ensuring that the baffle 51 can be stably maintained in the adjusted position. Thus, the buffer range of the buffer mechanism 3 can be flexibly adjusted according to the magnitude of the thrust and the strength of the rebound force when different target drones are launched, so that the buffer effect can adapt to diverse launch requirements. At the same time, the movement stability of the limit plate 341, guide rod 34 and upper plate 31 is maintained during the buffering process, avoiding the problem of increased device vibration or component overload caused by the inappropriate buffer range.

[0033] Furthermore, any content not described in detail in this specification is existing technology known to those skilled in the art.

[0034] Working Principle: When this unmanned target drone catapult is in operation, the angle of the catapult body 1 is first adjusted by rotating the support base 11 to adapt to the launch requirements. After the unmanned target drone is ready on the catapult body 1, the launch is initiated. At the moment of launch, the recoil force generated by the target drone is transmitted sequentially to the rotating support base 11 and the base plate 12, driving the horizontal telescopic frame 21 and vertical telescopic frame 22 of the four support mechanisms 2 to bear force, and then transmitted to the buffer mechanism 3 through the connecting block 23. At this time, the upper plate 31 of the buffer mechanism 3 is pressed and moves towards the lower plate 32, compressing the compression spring 33. At the same time, the arched column 41 at the bottom of the upper plate 31 slides down the inner wall of the air chamber 4, the air pressure in the air chamber 4 increases, causing the one-way valve 45 to open, and the gas is discharged through the exhaust port 44 and the connected air passage 321. The compression spring 33 deforms to absorb the impact force and relieve the overload of the device.

[0035] After the buffering is complete, the compression spring 33 pushes the upper plate 31 and the arched column 41 upwards, the one-way valve 45 closes, and the air chamber 4 ensures air intake space through the air inlet 43 and the inclined surface 411. The slow air intake forms damping, reducing the impact of the rebound force. During the process, the guide rod 34 and the limiting plate 341 ensure the smooth movement of the upper plate 31, and the anti-slip groove 322 at the bottom of the lower plate 32 prevents the device from sliding. The position of the L-shaped lifting rod 5 is adjusted by rotating the screw 52, ​​which drives the baffle 51 to constrain the range of motion of the limiting plate 341, so that the buffering range is adjustable. The detachable connection of the air chamber 4 and the arched column 41 facilitates maintenance, ensures the stability of the ejection as a whole, and solves the problems of device overload, vibration and loose connection.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0037] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A catapult for an unmanned target drone, comprising a catapult body (1), characterized in that, The bottom of the catapult body (1) is equipped with a rotating support base (11), and the bottom of the rotating support base (11) is rotatably connected to a base plate (12). The bottom of the base plate (12) is equipped with four support mechanisms (2). The support mechanism (2) includes a horizontal telescopic frame (21) and a vertical telescopic frame (22). The horizontal telescopic frame (21) is installed at the bottom of the base plate (12). A connecting block (23) is installed between the horizontal telescopic frame (21) and the vertical telescopic frame (22). The connecting block (23) is installed at the end of the horizontal telescopic frame (21), and the vertical telescopic frame (22) is installed at the bottom of the connecting block (23). A buffer mechanism (3) is provided at the bottom of each of the four connecting blocks (23). The buffer mechanism (3) includes an upper plate (31) and a lower plate (32). A compression spring (33) is installed between the upper plate (31) and the lower plate (32). An air chamber (4) is installed at the top of the lower plate (32). An arched column (41) is slidably connected to the inner wall of the air chamber (4). The arched column (41) is installed at the bottom of the upper plate (31). An air inlet (43) is provided on both sides of the air chamber (4). An inclined surface (411) is provided on the outer side of the air chamber (4) to give way to the air inlet (43). An exhaust hole (44) is provided at the bottom of the air chamber (4). A one-way valve (45) is installed on the inner wall of the exhaust hole (44).

2. The unmanned target drone catapult according to claim 1, characterized in that, A guide rod (34) is installed at the top of the lower plate (32). The guide rod (34) passes through the top of the upper plate (31). A limiting plate (341) is installed at the top of the guide rod (34). The limiting plate (341) is slidably connected to the inner wall of the vertical telescopic frame (22).

3. The unmanned target drone catapult according to claim 1, characterized in that, An air passage (321) is provided on the lower plate (32), the air passage (321) is spatially connected to the exhaust hole (44), and an anti-slip groove (322) is provided at the bottom of the lower plate (32).

4. The unmanned target drone catapult according to claim 1, characterized in that, An installation ring (42) is installed on the outside of the air chamber (4). The installation ring (42) is detachably connected to the top of the lower plate (32) by bolts. The arched column (41) is detachably connected to the bottom of the upper plate (31) by bolts.

5. The unmanned target drone catapult according to claim 2, characterized in that, The vertical telescopic frame (22) has an L-shaped lifting rod (5) slidably connected to its inner wall. A baffle (51) is installed at the bottom of the L-shaped lifting rod (5), and the baffle (51) contacts the top of the limiting plate (341).

6. The unmanned target drone catapult according to claim 5, characterized in that, The L-shaped lifting rod (5) extends out of the outside of the vertical telescopic frame (22). The inner wall of the L-shaped lifting rod (5) is rotatably connected to a screw (52). The outer side of the screw (52) is threadedly connected to a threaded fixing block (53). The threaded fixing block (53) is installed on the side wall corresponding to the vertical telescopic frame (22).

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