Limiting device for rocket boosting unmanned aerial vehicle launcher

Abstract

The utility model relates to the technical field of unmanned aerial vehicle launchers, and discloses a rocket boosted unmanned aerial vehicle launcher limiting device which comprises a support and an aircraft body, a rocket booster is fixedly connected to the right end of the bottom of the support, a propeller is fixedly connected to the right end of the support, and U-shaped seats are fixedly connected to the front end and the rear end of the left side of the top of the support. Ratchet wheels are rotationally connected to the outer sides of the interiors of the two U-shaped seats, first springs are rotationally connected to the middles of the interiors of the two U-shaped seats, and triangular seats are fixedly connected to the front side and the rear side of the left end of the top of the support. According to the utility model, the pawl is pressed down through the pressurizing spring, the left end of the pawl is clamped at the top of the ratchet wheel, the front supporting arm is rotationally connected to the inner side of the U-shaped seat, and the top end of the front supporting arm is attached to the aircraft body, so that the aircraft body is accurately limited and stably supported on the launcher, the front supporting arm is effectively prevented from rebounding due to external force, and the safety and reliability of launching operation are improved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) launcher technology, and in particular to a rocket-assisted UAV launcher limiting device. Background Technology

[0002] A drone launcher is a specialized device used to assist drones in taking off. It helps drones that lack sufficient power or have limited take-off and landing sites to take off smoothly, effectively expanding the application scenarios of drones. Whether it is reconnaissance and surveillance missions in the military field or geographic mapping and material delivery work in the civilian field, drone launchers provide guarantees for the efficient and safe take-off of drones.

[0003] A search revealed Chinese Patent Publication No. CN117755555A, which discloses a top-rod adjustable dual-rocket booster UAV launch device, belonging to the field of UAV launch technology. The device includes a platform with a pair of top-rod mechanisms for supporting the rocket boosters. Each top-rod mechanism includes a top-rod head, a first top-rod, and a second top-rod. The top-rod head is hinged to the first top-rod and can swing up and down relative to the first top-rod, with a limit position. The top-rod head supports the tail of the rocket booster. The first top-rod is connected to the second top-rod, and the first top-rod can rotate freely relative to the second top-rod. The second top-rod can move axially and be positioned. The booster rocket bracket was eliminated, and the bracket and booster rocket were integrated into a single design. An adjustable push rod mechanism was used to fix the rocket to the launch pad, eliminating the need for on-site rocket assembly and effectively reducing the overall weight of the booster rocket. The push rod mechanism is easy to adjust and has a wide adjustment range, which significantly reduces the precision requirements and can adapt to UAV launches in different scenarios. However, due to the large recoil force generated by the rocket during launch, it is difficult to completely counteract the effect of the recoil force by relying solely on the adjustable push rod mechanism to fix the rocket. Under the action of this strong recoil force, the launch pad will be displaced, causing the UAV launch position to deviate from the predetermined trajectory, affecting launch accuracy and safety, and requiring the trajectory to be readjusted during flight. Utility Model Content

[0004] To overcome the above shortcomings, this utility model provides a rocket-assisted UAV launcher limiting device, which aims to improve the problem in the prior art where the launcher will be displaced due to the large recoil force generated by the rocket during launch.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a rocket-assisted unmanned aerial vehicle (UAV) launcher limiting device, comprising a support and an aircraft body. A rocket booster is fixedly connected to the bottom right end of the support, and a propeller is fixedly connected to the right end of the support. U-shaped seats are fixedly connected to the front and rear ends of the top left side of the support. Ratchets are rotatably connected to the inner and outer sides of the two U-shaped seats, and springs are rotatably connected to the inner middle of the two U-shaped seats. Triangular seats are fixedly connected to the front and rear sides of the top left end of the support. Pawls are rotatably connected to the inside of the two triangular seats, and pressure springs are fixedly connected to the inside of the two pawls. The left ends of the two pawls are respectively engaged with the tops of the two ratchet wheels. Front support arms are rotatably connected to adjacent sides of the inside of the two U-shaped seats. The top ends of the two front support arms are respectively attached to the front and rear left ends of the aircraft body. A rocket support mechanism is provided on the right side of the inside of the support.

[0006] The above technical solution involves pressing down the pawl with a pressure spring, causing its left end to engage with the top of the ratchet. The front support arm is rotatably connected to the inside of the U-shaped seat, with its top end fitting against the aircraft body. This achieves precise positioning and stable support of the aircraft body on the launch pad, effectively preventing the front support arm from rebounding due to external forces. It ensures the stability of the rocket-assisted UAV's position during launch preparation, launch, and post-launch stages, avoiding safety accidents caused by support component displacement and improving the safety and reliability of launch operations.

[0007] As a further description of the above technical solution:

[0008] The rocket support mechanism includes a base, which is fixedly connected to the inside right side of the bracket. A fixing component is provided on the right side of the base. A portal-shaped mounting seat is fixedly connected to the top of the base. A crossbar is fixedly connected inside the portal-shaped mounting seat. Two springs are rotatably connected to the outside of the crossbar. The same portal frame is rotatably connected to the front and rear ends of the outer side of the crossbar. A rocket support arm is fixedly connected to the top of the portal frame. The top of the rocket support arm is attached to the bottom end of the rocket booster. Limit hook mounting seats are fixedly connected to the front and rear ends of the top left side of the base. L-shaped limit hooks are rotatably connected inside the two limit hook mounting seats. The top ends of the two L-shaped limit hooks are respectively engaged with the front and rear sides of the top of the portal frame.

[0009] The above technical solution achieves stable support for the rocket booster by fixing the base to the bracket and forming a triangular support with the fixing components. When the rocket booster is placed, the second spring is compressed to provide cushioning. After placement, the L-shaped limit hook engages with the gantry frame. During launch, the second spring buffers the recoil force, and the L-shaped limit hook prevents displacement. After launch, the engagement is released, and the components are reset. This achieves stable support for the rocket booster in all directions and throughout the entire process, effectively buffering impact forces, resisting reaction forces, and limiting displacement, ensuring the stable operation of the rocket booster and reducing the risk of failure.

[0010] As a further description of the above technical solution:

[0011] The fixing component includes two protrusions, which are respectively fixedly connected to the rear front and rear ends of the base. The right ends of the two protrusions are rotatably connected to U-shaped connectors, and the bottom ends of the two U-shaped connectors are fixedly connected to support rods. The bottoms of the two support rods are fixedly connected to the same fixing base plate.

[0012] The above technical solution provides two protrusions as rotation fulcrums for the U-shaped connector. The U-shaped connector is connected to the support rod and the fixed base plate to form a stable triangular support structure. The fixed base plate is fixed to the ground, which stabilizes the rocket support mechanism, disperses the force generated by the rocket booster during operation, and ensures the stability of the entire launch pad foundation.

[0013] As a further description of the above technical solution:

[0014] The bottom of the fixed base plate has multiple fixing holes, all of which are designed to be equidistant.

[0015] The above technical solution involves multiple equidistant fixing holes at the bottom of the fixed base plate, which can be used with rivets or expansion screws to firmly install the fixed base plate on the ground or foundation platform. The equidistant distribution design ensures that the fixed base plate is subjected to uniform force and enhances the stability of the connection with the ground.

[0016] As a further description of the above technical solution:

[0017] Multiple diagonal braces are fixedly connected to the outside of both support rods, and the bottom ends of the multiple diagonal braces are respectively fixedly connected to the front and rear sides of the top of the fixed base plate.

[0018] The above technical solution involves multiple diagonal braces connecting the support rod to the fixed base plate, forming a triangular reinforcement structure. During launch, the diagonal braces share the vertical and lateral forces on the support rod, improving its resistance to compression and bending, and preventing it from deforming due to excessive stress.

[0019] As a further description of the above technical solution:

[0020] Each of the four corners at the bottom of the bracket is fixedly connected with a foot pad, and each of the foot pads has a fixing hole at its top.

[0021] The above technical solution involves fixing the foot pads to the ground through the second fixing hole, which can distribute the weight and force borne by the support. The foot pads can also play a shock absorption role, reducing the vibration transmission during the operation of the rocket booster, and preventing the support from directly contacting the ground and causing wear.

[0022] As a further description of the above technical solution:

[0023] The bracket has a tilted design with the left side higher than the right side, and the bracket has a symmetrical design.

[0024] The above technical solution involves a left-high, right-low tilt design of the support frame, which is beneficial for the angle of the aircraft body during launch. This, combined with the rocket booster and propeller, allows the aircraft to reach takeoff speed more quickly. The symmetrical design ensures that the support frame is subjected to balanced forces, avoiding stress concentration caused by structural asymmetry and improving the overall strength and stability of the launch pad.

[0025] As a further description of the above technical solution:

[0026] The top of the rocket support arm has an arc-shaped design, and the bottom of the rocket booster matches the size of the top of the rocket support arm.

[0027] The above technical solution involves an arc-shaped design at the top of the rocket support arm that matches the size of the bottom of the rocket booster, increasing the contact area between the two and making the rocket booster fit more snugly and stably. During launch, the arc-shaped structure can evenly distribute the pressure on the rocket booster and prevent excessive local stress.

[0028] This utility model has the following beneficial effects:

[0029] 1. In this utility model, the pawl is pressed down by a pressure spring, so that its left end is engaged with the top of the ratchet. The front support arm is rotatably connected to the inside of the U-shaped seat and its top end is attached to the aircraft body. This achieves precise positioning and stable support of the aircraft body on the launch pad, effectively preventing the front support arm from rebounding due to external force. This ensures the stability of the rocket-assisted UAV's position during launch preparation, launch process, and post-launch stages, avoids safety accidents caused by the displacement of the support components, and improves the safety and reliability of launch operations.

[0030] 2. In this utility model, the base is fixed to the bracket, and the fixing components form a triangular support to enhance stability. When the rocket booster is placed, the second spring is compressed to provide cushioning. After being placed in place, the L-shaped limit hook engages with the gantry frame. During launch, the second spring buffers the recoil force, and the L-shaped limit hook prevents displacement. After launch, the engagement is released, and the components are reset. This achieves stable support for the rocket booster in all directions and throughout the entire process, effectively buffering impact force, resisting reaction force, and limiting displacement, ensuring the stable operation of the rocket booster and reducing the risk of failure. Attached Figure Description

[0031] Figure 1 This is a perspective view of a rocket-assisted unmanned aerial vehicle launcher limiting device proposed in this utility model;

[0032] Figure 2 for Figure 1 Enlarged view of the structure at point A in the middle;

[0033] Figure 3 This is a front view of a rocket-assisted unmanned aerial vehicle launcher limiting device proposed in this utility model;

[0034] Figure 4 This is a schematic diagram of the rocket support mechanism in a rocket-assisted UAV launcher limiting device proposed in this utility model;

[0035] Figure 5 This is a schematic diagram of the fixing component in a rocket-assisted unmanned aerial vehicle launcher limiting device proposed in this utility model.

[0036] Legend:

[0037] 1. Bracket; 2. Rocket support mechanism; 201. Base; 202. Portal mounting seat; 203. Crossbar; 204. Spring II; 205. Portal frame; 206. Rocket support arm; 207. Limit hook mounting seat; 208. L-shaped limit hook; 3. Aircraft body; 4. U-shaped seat; 5. Ratchet; 6. Spring I; 7. Triangular seat; 8. Pawl; 9. Compression spring; 10. Front support arm; 11. Rocket booster; 12. Propeller; 13. Protrusion; 14. U-shaped connector; 15. Support rod; 16. Fixed base plate; 17. Fixing hole I; 18. Diagonal brace; 19. Foot pad; 20. Fixing hole II. Detailed Implementation

[0038] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. 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.

[0039] Reference Figure 1 , Figure 2 and Figure 3An embodiment of this utility model provides a rocket-assisted unmanned aerial vehicle launcher limiting device, including a bracket 1 and an aircraft body 3. A rocket booster 11 is fixedly connected to the bottom right end of the bracket 1, and a propeller 12 is fixedly connected to the right end of the bracket 1. U-shaped seats 4 are fixedly connected to the front and rear ends of the top left side of the bracket 1. Ratchets 5 are rotatably connected to the inner and outer sides of the two U-shaped seats 4. Springs 6 are rotatably connected to the middle of the inner side of the two U-shaped seats 4. Triangular seats 7 are fixedly connected to the front and rear sides of the top left end of the bracket 1. Pads 8 are rotatably connected to the inside of the two triangular seats 7. Compression springs 9 are fixedly connected to the inside of the two pawls 8. The left ends of the two pawls 8 are respectively engaged with the tops of the two ratchet 5. Front support arms 10 are rotatably connected to the adjacent sides of the inside of the two U-shaped seats 4. The top ends of the two front support arms 10 are respectively attached to the front and rear left ends of the aircraft body 3. A rocket support mechanism 2 is provided on the right side of the inside of the bracket 1.

[0040] Specifically, in the initial state, the aircraft body 3 is placed on the front support arm 10 at the top of the bracket 1. The top of the front support arm 10 is attached to the left end of the front and rear sides of the aircraft body 3, forming a preliminary support relationship. At this time, the spring 6, which is rotatably connected to the middle of the inner side of the U-shaped seat 4, is in its natural state. The rocket support mechanism 2, which is set on the right side inside the bracket 1, firmly supports the rocket booster 11 fixedly connected to the bottom right end of the bracket 1. At the same time, the propeller 12, which is fixedly connected to the right end of the bracket 1, is in a ready-to-start state. When it is necessary to limit and fix the aircraft body 3, the pressure spring 9 is fixedly connected to the inside of the pawl 8. Under its elastic force, the pawl 8 is pressed down with the triangular seat 7 as the rotation fulcrum, so that the left end of the pawl 8 is firmly engaged with the top of the ratchet 5. Ratchets 5 are rotatably connected to the inner and outer sides of the two U-shaped seats 4, while the front support arm 10 is rotatably connected to the adjacent side inside the U-shaped seat 4. When the aircraft body 3 is launched, it will cause the front support arm 10 to move. The front support arm 10 will drive the ratchet 5 to rotate. However, due to the engagement structure between the pawl 8 and the ratchet 5, the ratchet 5 cannot rotate in the engagement restriction direction, thus restricting the movement of the front support arm 10. This restriction, from a mechanical principle, prevents the aircraft body 3 from sliding back and forth on the support 1, especially preventing the front support arm 10 from rebounding backward due to external force reaction, ensuring the stability of the aircraft body 3 on the launch pad. During the rocket-assisted UAV launch, the rocket booster 11 generates a powerful force at the moment of activation. The rocket propeller 12 also begins to rotate at high speed to provide continuous power. During this process, the huge force can easily cause the support components of the launch pad to shift or rebound. However, at this time, the engagement structure of the pawl 8 and ratchet 5 in the limiting mechanism continuously limits the front support arm 10. Even if the aircraft body 3 generates a rearward reaction force due to the strong thrust, attempting to drive the front support arm 10 to rebound, the front support arm 10 cannot rebound due to the restriction of the ratchet 5 by the pawl 8. This ensures that the aircraft body 3 is always in the predetermined launch trajectory and position. During the launch process, the rocket support mechanism 2 also provides stable support for the rocket booster 11, preventing the rocket booster 11 from swaying or deviating due to recoil. The positioning mechanism works together to ensure the safety and stability of the launch process. When the launch is complete and the limit needs to be released, the operator applies external force to lift the pawl 8 upward, overcoming the pressure of the compression spring 9, so that the pawl 8 separates from the ratchet 5. After the pawl 8 is no longer restricted, the ratchet 5 can rotate freely, and the front support arm 10 can rotate around the inside of the U-shaped seat 4, thereby releasing the limit on the aircraft body 3. This facilitates subsequent inspection, maintenance and reuse of the launch pad. Through this set of mechanical structures and workflows, the limiting mechanism comprehensively prevents safety problems caused by the rebound of the launch pad support components from the pre-launch preparation, stable control during the launch process and the release of the limit after launch, ensuring the safe and smooth launch of the rocket-assisted UAV.

[0041] Reference Figure 1 , Figure 4 and Figure 5 The rocket support mechanism 2 includes a base 201, which is fixedly connected to the inside right side of the bracket 1. A fixing component is provided on the right side of the base 201, including two protrusions 13. The two protrusions 13 are fixedly connected to the front and rear ends of the rear side of the base 201, respectively. A U-shaped connector 14 is rotatably connected to the right end of each of the two protrusions 13. A support rod 15 is fixedly connected to the bottom end of each of the two U-shaped connectors 14. The same fixing base plate 16 is fixedly connected to the bottom of each of the two support rods 15. A portal-shaped mounting seat 202 is fixedly connected to the top of the base 201. The portal-shaped mounting seat 202 has an internal fixing... A crossbar 203 is fixedly connected. Two springs 204 are rotatably connected to the outside of the crossbar 203. The front and rear ends of the outer side of the crossbar 203 are rotatably connected to the same portal frame 205. A rocket support arm 206 is fixedly connected to the top of the portal frame 205. The top of the rocket support arm 206 is attached to the bottom end of the rocket booster 11. The front and rear ends of the left side of the top of the base 201 are fixedly connected to limit hook mounting seats 207. L-shaped limit hooks 208 are rotatably connected inside the two limit hook mounting seats 207. The top ends of the two L-shaped limit hooks 208 are respectively engaged with the front and rear sides of the top of the portal frame 205.

[0042] Specifically, during the installation phase, the base 201 is fixedly connected to the inside right side of the bracket 1, serving as the basic load-bearing component of the entire support mechanism. Two protrusions 13 in the fixing assembly are fixedly connected to the front and rear ends of the base 201, providing connection points for subsequent components. The U-shaped connector 14 rotatably connected to the right ends of the two protrusions 13, together with the support rod 15 fixedly connected to the bottom end and the fixed base plate 16 fixedly connected to the bottom, form a stable triangular support structure. The fixed base plate 16 is fixed to the ground or mounting surface, enhancing the stability of the entire rocket support mechanism 2 and preventing displacement of the base 201 during rocket booster 11 operation. When the rocket booster 11 needs to be installed, the operator first places the rocket booster 11 on... The top of the portal frame 205 is fixedly connected to the rocket support arm 206. At this time, the top of the rocket support arm 206 is in contact with the bottom of the rocket booster 11. The portal frame 205 is rotatably connected to the outside of the crossbar 203 through its internal structure, allowing it to rotate at a certain angle along the crossbar 203. The crossbar 203 is fixedly connected inside the portal mounting base 202, providing the portal frame 205 with a rotation axis. Two springs 204 are rotatably connected to the outside of the crossbar 203 and are sleeved on the crossbar 203. During the placement of the rocket booster 11, the springs 204 are compressed by the pressure generated by the downward pressure of the portal frame 205, generating an upward supporting force through their own elastic deformation. This force acts on the portal frame 205 and the rocket support arm 206, providing support for the rocket booster. The device 11 provides a buffer support to absorb the impact force generated when the rocket booster 11 is placed. After the rocket booster 11 is placed in position, the operator rotates the L-shaped limit hooks 208 inside the limit hook mounting seat 207, which is fixedly connected to the front and rear ends of the top left side of the base 201. This causes the top ends of the two L-shaped limit hooks 208 to engage with the front and rear sides of the top of the gantry frame 205, respectively. The L-shaped limit hooks 208 use the limit hook mounting seat 207 as a fulcrum for rotation, and lock the position of the gantry frame 205 through the engaging structure. This prevents the gantry frame 205 from rotating or shifting due to vibration and reaction force when the rocket booster 11 is working, ensuring that the rocket booster 11 is stably supported. During the launch process of the rocket booster 11, the powerful reaction force it generates... The force is transmitted downwards to the rocket support arm 206 and the gantry 205. At this time, the compressed spring 204 continuously provides elastic support force to buffer the recoil of the rocket booster 11. Meanwhile, the locking structure between the L-shaped limit hook 208 and the gantry 205, combined with the stable support of the fixing components, restricts the rocket support mechanism 2 from multiple angles, ensuring that the rocket booster 11 remains stable during launch. After the rocket booster 11 completes its launch mission, the operator rotates the L-shaped limit hook 208 to release its locking restriction on the gantry 205. The elastic restoring force of the spring 204 resets the gantry 205 and the rocket support arm 206, facilitating subsequent inspection and maintenance of the rocket support mechanism 2 and the rocket booster 11.

[0043] Reference Figure 1 , Figure 4 and Figure 5 The bottom of the fixed base plate 16 has multiple fixing holes 17, all of which are equidistant. Multiple diagonal braces 18 are fixedly connected to the outside of the two support rods 15, and the bottom ends of the multiple diagonal braces 18 are fixedly connected to the front and rear sides of the top of the fixed base plate 16 respectively. Foot pads 19 are fixedly connected to the four corners of the bottom of the bracket 1, and the top of the multiple foot pads 19 has fixing holes 20. The bracket 1 has a left-high-right-low tilt design and a symmetrical design. The top of the rocket support arm 206 has an arc design, and the bottom of the rocket booster 11 matches the top size of the rocket support arm 206.

[0044] Specifically, the two protrusions 13 provide rotation fulcrums for the U-shaped connector 14. The U-shaped connector 14 is connected to the support rod 15 and the fixed base plate 16, forming a stable triangular support structure. The fixed base plate 16 is fixed to the ground, stably anchoring the rocket support mechanism 2 and dispersing the force generated by the rocket booster 11 during operation, ensuring the stability of the entire launch pad foundation. Multiple equidistant fixing holes 17 at the bottom of the fixed base plate 16 can be used with rivets or expansion bolts to firmly install the fixed base plate 16 on the ground or foundation platform. The equidistant distribution design ensures that the fixed base plate 16 is evenly stressed and enhances the stability of the connection with the ground. Multiple diagonal braces 18 connect the support rod 15 and the fixed base plate 16, forming a triangular reinforcement structure. During launch, the diagonal braces 18 share the vertical and lateral forces on the support rod 15, improving the support rod 15's resistance to compression and bending, and preventing its... Due to excessive force and deformation, the foot pad 19 is fixed to the ground through the fixing hole 20, which can distribute the weight and force borne by the support 1. The foot pad 19 can also play a shock absorption role, reducing the vibration transmission during the operation of the rocket booster 11, and at the same time preventing the support 1 from directly contacting the ground and causing wear. The tilt design of the support 1 with the left side higher than the right side is beneficial to the angle of the aircraft body 3 during launch. Together with the rocket booster 11 and the propeller 12, it enables the aircraft to reach the takeoff speed faster. The symmetrical design ensures that the support 1 is evenly stressed, avoiding stress concentration caused by structural asymmetry, and improving the overall strength and stability of the launch pad. The arc design at the top of the rocket support arm 206 matches the size of the bottom of the rocket booster 11, which can increase the contact area between the two, making the rocket booster 11 fit more closely and stably. During the launch, the arc structure can evenly distribute the pressure of the rocket booster 11 and prevent excessive local stress.

[0045] Working principle: The aircraft body 3 is placed on the front support arm 10 at the top of the bracket 1. The top of the front support arm 10 is attached to the left end of the front and rear sides of the aircraft body 3, forming a preliminary support relationship. At this time, the spring 6 rotatably connected to the middle of the inner side of the U-shaped seat 4 is in a natural state. The rocket support mechanism 2 set on the right side inside the bracket 1 stably supports the rocket booster 11 fixedly connected to the bottom right end of the bracket 1. At the same time, the propeller 12 fixedly connected to the right end of the bracket 1 is in a ready-to-start state. When it is necessary to limit and fix the aircraft body 3, the pressure spring 9 is fixedly connected to the inside of the pawl 8. Under its elastic force, the pawl 8 is pressed down with the triangular seat 7 as the rotation fulcrum, so that the pawl... The left end of pawl 8 is firmly engaged with the top of ratchet 5. The two ratchet wheels 5 are rotatably connected to the inner and outer sides of the two U-shaped seats 4, respectively. The front support arm 10 is rotatably connected to the adjacent side inside the U-shaped seat 4. When the aircraft body 3 is launched, it will cause the front support arm 10 to move. The front support arm 10 will drive the ratchet 5 to rotate, but due to the engaging structure between the pawl 8 and the ratchet 5, the ratchet 5 cannot rotate in the engaging restriction direction, thus restricting the movement of the front support arm 10. This restriction, from a mechanical perspective, prevents the aircraft body 3 from sliding back and forth on the support 1, especially preventing the front support arm 10 from rebounding backward due to external force, ensuring the safety of the aircraft body. 3. With its position stable on the launch pad, during the launch of the rocket-assisted UAV, the rocket booster 11 generates a powerful backward thrust upon activation, while the propeller 12 also begins to rotate at high speed to provide continuous power. During this process, the enormous force can easily cause displacement or rebound of the support components of the launch pad. However, at this time, the engagement structure of the pawl 8 and ratchet 5 in the limiting mechanism continuously limits the front support arm 10. Even if the aircraft body 3 generates a backward reaction force due to the powerful thrust, attempting to cause the front support arm 10 to rebound backward, the front support arm 10 cannot rebound due to the restriction of the ratchet 8 on the ratchet 5, thus ensuring that the aircraft body 3 remains in a stable position on the launch pad. At the predetermined launch trajectory and position, the rocket support mechanism 2 also provides stable support for the rocket booster 11 during launch, preventing the rocket booster 11 from swaying or deviating due to recoil. Together with the limiting mechanism, it ensures the safety and stability of the launch process. When the launch is completed and the limiting needs to be released, the operator applies external force to lift the pawl 8 upward, overcoming the pressure of the pressure spring 9, so that the pawl 8 separates from the ratchet 5. After the limitation of the pawl 8 is removed, the ratchet 5 can rotate freely, and the front support arm 10 can rotate around the inside of the U-shaped seat 4, thereby releasing the limitation on the aircraft body 3, which facilitates the subsequent inspection, maintenance and reuse of the launch pad.

[0046] Furthermore, the base 201 is fixedly connected to the inside right side of the bracket 1, serving as the basic load-bearing component of the entire support mechanism. When the rocket booster 11 needs to be installed, the operator first places the rocket booster 11 on the rocket support arm 206 fixedly connected to the top of the portal frame 205. At this time, the top of the rocket support arm 206 is in contact with the bottom of the rocket booster 11. The portal frame 205, through its internal rotatable connection to the outside of the crossbar 203, can rotate at a certain angle along the crossbar 203. The crossbar 203 is fixedly connected inside the portal mounting base 202, forming the portal frame 205. A rotating axis is provided, and two springs 204, externally rotatably connected to the crossbar 203, are sleeved on the crossbar 203. During the placement of the rocket booster 11, the springs 204 are compressed by the pressure generated by the downward pressure of the gantry frame 205, and generate an upward supporting force through their own elastic deformation. This force acts on the gantry frame 205 and the rocket support arm 206, providing buffer support for the rocket booster 11 and absorbing the impact force generated during the placement of the rocket booster 11. After the rocket booster 11 is placed in position, the operator rotates the limit hooks fixedly connected to the front and rear ends of the top left side of the base 201 to install... The L-shaped limiting hooks 208 inside the mounting base 207 engage with the tops of the two L-shaped limiting hooks 208 on the front and rear sides of the top of the portal frame 205, respectively. The L-shaped limiting hooks 208 use the limiting hook mounting base 207 as a fulcrum for rotation, locking the position of the portal frame 205 through the engaging structure. This prevents the portal frame 205 from rotating or shifting due to vibration and reaction forces during the operation of the rocket booster 11, ensuring the rocket booster 11 is stably supported. During the launch process of the rocket booster 11, the powerful reaction force generated is transmitted downwards to the rocket support arm 206 and the portal frame 205. At this time, the compressed spring 204 continues to provide elastic support force, buffering the recoil force of the rocket booster 11. At the same time, the locking structure of the L-shaped limit hook 208 and the gantry 205, combined with the stable support of the fixing components, restricts the rocket support mechanism 2 from multiple angles, ensuring that the rocket booster 11 is always in a stable state during the launch process. After the rocket booster 11 completes the launch mission, the operator rotates the L-shaped limit hook 208 to release its locking restriction on the gantry 205. The elastic restoring force of the spring 204 resets the gantry 205 and the rocket support arm 206.

[0047] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A rocket-assisted unmanned aerial vehicle (UAV) launcher limiting device, comprising a support (1) and an aircraft body (3), characterized in that: A rocket booster (11) is fixedly connected to the bottom right end of the bracket (1). A propeller (12) is fixedly connected to the right end of the bracket (1). U-shaped seats (4) are fixedly connected to the front and rear ends of the top left side of the bracket (1). Ratchets (5) are rotatably connected to the inner and outer sides of the two U-shaped seats (4). Springs (6) are rotatably connected to the inner middle of the two U-shaped seats (4). Triangular seats (7) are fixedly connected to the front and rear sides of the top left end of the bracket (1). Pawls (8) are rotatably connected to the inside of the two triangular seats (7). Pressure springs (9) are fixedly connected to the inside of the two pawls (8). The left ends of the two pawls (8) are respectively engaged with the tops of the two ratchet wheels (5). Front support arms (10) are rotatably connected to the adjacent sides of the inside of the two U-shaped seats (4). The top ends of the two front support arms (10) are respectively attached to the front and rear left ends of the aircraft body (3). A rocket support mechanism (2) is provided on the inner right side of the bracket (1).

2. The rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 1, characterized in that: The rocket support mechanism (2) includes a base (201), which is fixedly connected to the inside right side of the bracket (1). A fixing component is provided on the right side of the base (201). A gate-shaped mounting seat (202) is fixedly connected to the top of the base (201). A crossbar (203) is fixedly connected inside the gate-shaped mounting seat (202). Two springs (204) are rotatably connected to the outside of the crossbar (203). The same gate is rotatably connected to the front and rear ends of the outer side of the crossbar (203). A portal frame (205) is fixedly connected to a rocket support arm (206) at its top. The top of the rocket support arm (206) is attached to the bottom of the rocket booster (11). The front and rear ends of the top left side of the base (201) are fixedly connected to limit hook mounting seats (207). The interior of the two limit hook mounting seats (207) is rotatably connected to L-shaped limit hooks (208). The top ends of the two L-shaped limit hooks (208) are respectively engaged with the front and rear sides of the top of the portal frame (205).

3. The rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 2, characterized in that: The fixing component includes two protrusions (13), which are fixedly connected to the rear front and rear ends of the base (201) respectively. The right ends of the two protrusions (13) are rotatably connected to U-shaped connectors (14), and the bottom ends of the two U-shaped connectors (14) are fixedly connected to support rods (15). The bottoms of the two support rods (15) are fixedly connected to the same fixing base plate (16).

4. The rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 3, characterized in that: The bottom of the fixed base plate (16) is provided with multiple fixing holes (17), and the multiple fixing holes (17) are all designed to be equidistant.

5. The rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 3, characterized in that: Multiple diagonal braces (18) are fixedly connected to the outside of both support rods (15), and the bottom ends of the multiple diagonal braces (18) are fixedly connected to the front and rear sides of the top of the fixed base plate (16).

6. The rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 1, characterized in that: The bracket (1) has foot pads (19) fixedly connected at the four corners of its bottom, and the top of each foot pad (19) has a fixing hole (20).

7. The rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 1, characterized in that: The bracket (1) has an angled design with the left side higher than the right side, and the bracket (1) has a symmetrical design.

8. A rocket-assisted unmanned aerial vehicle launcher limiting device according to claim 2, characterized in that: The top of the rocket support arm (206) is designed with an arc shape, and the bottom of the rocket booster (11) matches the top size of the rocket support arm (206).

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