Unmanned aerial vehicle booster rocket launching separation mechanism

Abstract

The utility model discloses an unmanned aerial vehicle booster rocket launching separation mechanism, and relates to the technical field of unmanned aerial vehicle design, the unmanned aerial vehicle booster rocket launching separation mechanism comprises a rocket connecting piece, one end of the rocket connecting piece is used for installing a rocket body, and the other end of the rocket connecting piece is provided with a push rod; the push rod is of a hollow structure, a pressure spring is installed in the push rod, and the end, away from the rocket connecting piece, of the push rod is movably sleeved with a driving guide head. The rocket mounting base is used for being connected with the unmanned aerial vehicle, a second hook is mounted above one end of the rocket mounting base, and the lower portion of one end of the rocket mounting base is connected with the driving guide head through a rotating disengaging mechanism. The push rod is placed in the driving guide head after the compression spring is placed in the push rod, thrust is generated after a rocket is ignited and launched to compress the compression spring, the first hook and the second hook are separated, the spring pin arranged on the driving guide head is bounced into the guide groove of the push rod, the first hook and the second hook are hooked again, and therefore it is guaranteed that the launching disengaging mechanism is smoothly disengaged from a machine body.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle (UAV) design, in particular to a UAV booster rocket launch and separation mechanism. Background Art

[0002] The main reason drones use rocket-assisted takeoff is to shorten takeoff distance and improve takeoff efficiency. Rocket-assisted takeoff uses the additional thrust provided by the rocket engine during takeoff to help the drone reach the necessary flight speed and altitude quickly, thereby shortening takeoff distance and improving takeoff efficiency.

[0003] Currently, rocket-assisted takeoffs for drones are efficient and fast. However, if the booster structure remains fixed to the aircraft after takeoff, it will significantly affect various performance indicators such as the aircraft's range and maneuverability. The existing mechanism uses a rocket mounting base fixed to the aircraft structure. The cone head, push rod, and hook inserted into it are connected to the rocket via pins. The hooks are hooked to the fixed hooks on the mounting base to achieve the installation of the entire structure. During launch, the rocket drives the push rod to shorten the pin, causing the cone head to move to the top of the structural guide groove. After launch, the push rod and rocket rotate forward along the pin on the mounting base under gravity and fall off. However, this mechanism carries the risk that the pin cannot be shortened under certain conditions, and assembly is relatively difficult. Therefore, it is particularly important to design a practical new rocket-assisted separation mechanism that is technically safe, reliable, and low-cost. Utility Model Content

[0004] The purpose of the present utility model is to provide a UAV booster rocket launch separation mechanism to solve the problems raised in the above background technology.

[0005] To achieve the above-mentioned object, the present invention provides the following technical solution: a UAV booster rocket launch and release mechanism, comprising: a rocket connector, one end of which is used to mount a rocket body, and the other end of which is mounted with a push rod; the push rod is a hollow structure, a compression spring is mounted inside the push rod, a drive guide head is movably sleeved on the end of the push rod away from the rocket connector, and a hook is mounted on the surface of the push rod;

[0006] It also includes: a rocket mounting seat, which is used to connect a drone. A hook 2 is installed above one end of the rocket mounting seat. The lower end of the rocket mounting seat is connected to the driving guide head through a rotating disengagement mechanism. Before disengagement, the hook 2 is connected to the hook 1.

[0007] Optionally, the rotational disengagement mechanism includes: a disengagement shaft arranged below one end of the rocket mounting seat, and a disengagement slot arranged at one end of the drive guide head, and before disengagement, the disengagement shaft is located in the disengagement slot.

[0008] Optionally, a movable groove is provided at one end of the driving guide head facing the rocket connector, and the hook 1 is located in the movable groove.

[0009] Optionally, a guide groove is provided on the surface of the push rod, and a spring pin is installed on the driving guide head. When disengaged, the spring pin enters the guide groove.

[0010] Optionally, the hook is mounted on the surface of the push rod by means of screws.

[0011] Optionally, a threaded cavity is provided at one end of the rocket connector, and one end of the push rod is threadedly connected to the inside of the threaded cavity.

[0012] Optionally, both ends of the compression spring are in contact with the rocket connector and the drive guide head respectively.

[0013] Compared with the prior art, the beneficial effects of the present invention are:

[0014] 1. The UAV booster rocket launch separation mechanism of the present invention uses screws to install hook 1 and push rod as a whole. A compression spring is placed inside the push rod and then placed in the drive guide head. After the rocket is ignited and launched, the thrust generated compresses the compression spring, causing hook 1 and hook 2 to separate. The spring pin set on the drive guide head bounces into the push rod guide groove to prevent the push rod from being pushed by the compression spring, causing hook 1 and hook 2 to hook again, thereby ensuring that the launch separation mechanism can be smoothly separated from the body.

[0015] 2. The UAV booster rocket launch and separation mechanism of the present invention is realized by installing a separation shaft on the rocket mounting seat and providing a separation slot on the drive guide head. After the rocket is completed, the rocket and part of the launch separation will rotate downward around the separation shaft under the action of gravity. When the rocket rotates to a nearly vertical state, the separation shaft will automatically fall off from the inside of the separation slot, so that the rocket and part of the launch separation mechanism will automatically separate from the UAV body. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the structure of the utility model in an unignited state;

[0017] Figure 2 This is a schematic diagram of the structure of the utility model in the state after ignition and before separation;

[0018] Figure 3 This is a schematic diagram of the structure of the utility model in the disengagement state after ignition;

[0019] Figure 4 This is a structural schematic diagram of the utility model in which the drive guide head and the rocket mounting seat are separated.

[0020] In the figure: 1. Rocket body; 2. Rocket connecting part; 3. Push rod; 4. Compression spring; 5. Drive guide head; 6. Hook 1; 7. Rocket mounting seat; 8. Hook 2; 9. Disengagement shaft; 10. Disengagement slot; 11. Moving slot; 12. Guide slot; 13. Spring pin; 14. Threaded cavity. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is 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 used to explain the present invention and are not intended to limit the present invention.

[0022] like Figures 1 to 4 As shown, the UAV booster rocket launch and separation mechanism of this embodiment includes a rocket connector 2, one end of the rocket connector 2 is used to mount the rocket body 1, and the other end of the rocket connector 2 is mounted with a push rod 3; the push rod 3 is a hollow structure, and a compression spring 4 is mounted inside the push rod 3. The end of the push rod 3 away from the rocket connector 2 is movably sleeved with a drive guide head 5, and a hook 6 is mounted on the surface of the push rod 3;

[0023] It also includes: a rocket mounting seat 7, which is used to connect to a UAV. A hook 2 8 is installed above one end of the rocket mounting seat 7. The lower end of the rocket mounting seat 7 is connected to the drive guide head 5 through a rotating disengagement mechanism. Before disengagement, the hook 2 8 is hooked with the hook 1 6. The hook 2 8 and the hook 1 6 can be hooked with each other, so as to realize the connection between the push rod 3 and the rocket mounting seat 7. After the compression spring 4 is placed inside the push rod 3 and placed in the drive guide head 5, the rocket body 1 is ignited and launched to generate thrust to compress the compression spring 4, so that the hook 1 6 and the hook 2 8 are disengaged, and the spring pin 13 on the drive guide head 5 bounces into the guide groove 12 on the push rod 3, and finally the entire mechanism is separated from the body.

[0024] Optionally, the rotational disengagement mechanism includes: a disengagement shaft 9 arranged below one end of the rocket mounting seat 7, and a disengagement slot 10 arranged at one end of the drive guide head 5. Before disengagement, the disengagement shaft 9 is located in the disengagement slot 10. After the rocket body 1 completes its work, the rocket body 1 will be in a vertical state under the action of gravity, and the disengagement shaft 9 will fall off from the inside of the disengagement slot 10, thereby realizing the disengagement of the entire mechanism from the UAV body.

[0025] Optionally, a movable groove 11 is provided at one end of the driving guide head 5 facing the rocket connector 2, and the hook 1 6 is located in the movable groove 11. The movable groove 11 guides and limits the movement of the hook 1 6, so that the hook 1 6 and the hook 2 8 are hooked with each other, thereby avoiding misalignment when the hook 1 6 and the hook 2 8 are hooked.

[0026] Optionally, a guide groove 12 is provided on the surface of the push rod 3, and a spring pin 13 is installed on the driving guide head 5. When disengaging, the spring pin 13 enters the guide groove 12. After the rocket is ignited and launched, the thrust generated by the rocket drives the rocket connector 2 and the push rod 3 to compress the compression spring 4. When the push rod 3 moves, the spring pin 13 can be stuck into the inside of the guide groove 12, which plays a limiting role to prevent the compression spring 4 from recovering and re-hooking the hook 1 6 and the hook 2 8 after the thrust of the rocket disappears, thereby avoiding the failure of the rocket mounting seat 7 and the driving guide head 5 to disengage.

[0027] Optionally, the hook 1 6 is mounted on the surface of the push rod 3 by screws, so as to facilitate assembly of the hook 1 6 and the push rod 3 .

[0028] Optionally, a threaded cavity 14 is provided at one end of the rocket connector 2, and one end of the push rod 3 is threadedly connected to the inside of the threaded cavity 14 to achieve the connection between the push rod 3 and the rocket connector 2.

[0029] Optionally, both ends of the compression spring 4 are in contact with the rocket connector 2 and the drive guide head 5 respectively, ensuring that the compression spring 4 can be effectively compressed when the rocket connector 2 moves.

[0030] The method of using this embodiment is as follows: first, the rocket mounting seat 7 is installed on the load-bearing structure of the UAV, and the hook 2 8 is connected to the rocket mounting seat 7, and the disengagement shaft 9 on the rocket mounting seat 7 is inserted into the disengagement slot 10 on the drive guide head 5, and then the hook 1 6 is installed on the surface of the push rod 3 by means of screws, and after the compression spring 4 is placed inside the push rod 3, the push rod 3 is placed inside the drive guide head 5, and then the rocket connector 2 and one end of the push rod 3 are connected by rotating to prevent the rocket connector 2 from falling, and then the rocket connector 2 is pushed, and the rocket connector 2 compresses the compression spring 4 to hook the hook 1 6 and the hook 2 8, and then rotate again. Rocket connector 2, tighten it, and then install the rocket body 1 on the rocket connector 2. The preparation work is completed. After the rocket body 1 is ignited and launched, the powerful thrust generated compresses the compression spring 4, and one end of the push rod 3 is located inside the driving guide head 5, so that the hook 1 6 and the hook 2 8 are disengaged from each other. At the same time, one end of the spring pin 13 on the driving guide head 5 is inserted into the guide groove 12 to limit the push rod 3. Finally, under the action of gravity, the rocket body 1 after the work is completed drives the entire mechanism to rotate around the disengagement shaft 9, so that the rocket body 1 is in a vertical state, and the disengagement shaft 9 on the driving guide head 5 is disengaged from the disengagement slot 10, so that the overall mechanism is separated from the UAV body.

[0031] The above is only an embodiment of the present invention, and the common knowledge such as the specific technical solutions and / or characteristics in the solution are not described in detail here. The conformal design details for the inflatable wing proposed in the solution are just special cases of fixation by pull ropes. It should be pointed out that for technical personnel in related fields, without departing from the technical design ideas of the present invention, adjustments or improvements can be made to the specific details in the solution, such as changing the percentage of the pull points along the span direction and the number of pull points at different positions. This case is the application of inflatable wings to the conformal design of UAVs. This method can also be used in airships, large aspect ratio flexible aircraft and other aircraft. These should also be included in the scope of protection of the present invention and are all effects that can be achieved by the present invention. In order to reduce the additional resistance brought by the attached components on the surface of the conformal design of the inflatable wing, the components are treated with a rectifier to reduce resistance. This solution should also be a technical extension of the present invention and should also be protected.

[0032] The present invention is further described above in conjunction with the embodiments, but the present invention is not limited to the above embodiments. Various changes can be made within the knowledge of ordinary technicians in this field without departing from the purpose of the present invention.

Claims

1. A UAV booster rocket launch and release mechanism, characterized by: include: A rocket connector (2), one end of the rocket connector (2) is used to install the rocket body (1), and the other end of the rocket connector (2) is installed with a push rod (3); the push rod (3) is a hollow structure, a compression spring (4) is installed inside the push rod (3), and a driving guide head (5) is movably sleeved on one end of the push rod (3) away from the rocket connector (2), and a hook (6) is installed on the surface of the push rod (3); The invention also includes: a rocket mounting seat (7), wherein the rocket mounting seat (7) is used to connect to a UAV, a hook 2 (8) is installed above one end of the rocket mounting seat (7), and a lower end of the rocket mounting seat (7) is connected to the driving guide head (5) through a rotating disengagement mechanism, and before disengagement, the hook 2 (8) is connected to the hook 1 (6).

2. The UAV booster rocket launch and release mechanism according to claim 1, characterized in that: The rotational disengagement mechanism comprises: a disengagement shaft (9) arranged below one end of the rocket mounting seat (7), and a disengagement slot (10) arranged at one end of the driving guide head (5); before disengagement, the disengagement shaft (9) is located in the disengagement slot (10).

3. The UAV booster rocket launch and release mechanism according to claim 1 or 2, characterized in that: A movable groove (11) is provided at one end of the driving guide head (5) facing the rocket connecting member (2), and the hook 1 (6) is located in the movable groove (11).

4. The UAV booster rocket launch and release mechanism according to claim 1 or 2, characterized in that: A guide groove (12) is provided on the surface of the push rod (3), and a spring pin (13) is installed on the driving guide head (5). When disengaged, the spring pin (13) enters the guide groove (12).

5. The UAV booster rocket launch and release mechanism according to claim 1 or 2, characterized in that: The hook 1 (6) is mounted on the surface of the push rod (3) by means of screws.

6. The UAV booster rocket launch and release mechanism according to claim 1 or 2, characterized in that: One end of the rocket connector (2) is provided with a threaded cavity (14), and one end of the push rod (3) is threadedly connected to the inside of the threaded cavity (14).

7. The UAV booster rocket launch and release mechanism according to claim 1 or 2, characterized in that: The two ends of the compression spring (4) are in contact with the rocket connecting piece (2) and the driving guide head (5) respectively.

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