Surface-contact-based force transfer structure for launching rocket by unmanned aerial vehicle

Abstract

Compared with a connection mode of point connection in the prior art, the force transmission structure of the launching rocket of the unmanned aerial vehicle based on the surface contact is creatively changed into a connection mode of surface connection, thrust of the launching rocket is transmitted to the unmanned aerial vehicle in a surface load mode, the contact range is large, the mass center is easy to cover, and the force transmission effect is good. The machining precision requirements of the connecting structure and the rocket are greatly reduced, and the control difficulty of a control system is also reduced. The thrust of the rocket is directly transmitted to the force transmission cylinder through the skirt, so that the thrust is prevented from being transmitted to the front sealing head or the front top cover, and the thickness of the front sealing head or the front top cover can be reduced. The thrust is also transmitted to the cylindrical section of the combustion chamber shell of the launching rocket through the skirt, so that the cylindrical section is stressed, the pressure counteracts tensile stress generated by internal pressure applied to the cylindrical section of the combustion chamber shell when the launching rocket works, the stress level of the cylindrical section of the combustion chamber shell of the rocket is reduced, and the stability of the launching rocket is improved. The method is suitable for large-scale industrial use and popularization.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) launch technology, and specifically relates to a force transmission structure for UAV launch rockets based on surface contact. Background Technology

[0002] The main launch methods for drones include rocket-assisted launch, manual drop, vehicle-mounted launch, and gas ejection. Among these, rocket-assisted launch is currently the most widely used drone launch method.

[0003] In existing technology, the launch rocket and the drone are connected by a conical rod. One end of the conical rod is fixed to the front end cap or front top cover of the launch rocket, and the other end is a pointed tip that is connected to the conical hole of the drone fuselage with a clearance fit, which is a point contact.

[0004] In the existing technology, in order to ensure the stability of the UAV fuselage during launch, the extension line of the connecting cone rod must pass through the center of mass of the UAV. Otherwise, once a deviation occurs, the thrust of the launching rocket will bring a rotational torque to the UAV, which will cause the UAV to roll.

[0005] To avoid this situation, the requirements for the size and shape deviation of the cone rod are very high. At the same time, the requirements for the thrust deviation and offset of the launching rocket are also relatively high, which increases the difficulty and cost of processing, and also adds extra difficulty to the control of the drone, further increasing the cost of the drone.

[0006] Furthermore, one end of the cone-shaped rod is fixed to the front head or front top cover of the launching rocket, so the thrust of the launching rocket naturally acts on the front head or front top cover. The front head or front top cover is generally an ellipsoid or a sphere, which has poor stability under external loads. In order to ensure stability under thrust, the thickness of the front head or front top cover must be increased, resulting in unnecessary material waste, weight increase, and cost increase. Summary of the Invention

[0007] The purpose of this invention is to provide a force transmission structure for UAV launch rockets based on surface contact, so as to solve the problem of poor stability of launch rockets in the prior art.

[0008] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0009] A force transmission structure for a drone-launched rocket based on surface contact includes a drone and a launch rocket for boosting the drone, wherein a force transmission cylinder is coaxially and fixedly connected to the launch skirt at the top of the launch rocket.

[0010] The force transmission cylinder is cylindrical, and its outer diameter is equal to that of the launching rocket. Multiple weight-reducing grooves are evenly distributed along the circumference of the force transmission cylinder, and an adapter plate is fixedly connected to the top of the force transmission cylinder.

[0011] The adapter plate matches the shape of the lower part of the unmanned aerial vehicle, and the projection of the contact surface of the adapter plate along the central axis of the force transmission cylinder covers the center of mass of the unmanned aerial vehicle.

[0012] The utility model still has the following characteristics:

[0013] Further, the weight reduction groove is a through strip-shaped groove, and the weight reduction groove extends along the length direction of the force transmission cylinder.

[0014] Further, the force transmission cylinder and the adapter plate are fixedly connected through welding.

[0015] Further, the force transmission cylinder and the launch rocket are fixedly connected through bolt connection, welding or flange connection.

[0016] Compared with the prior art, the utility model has the following technical effects:

[0017] Compared with the connection form of point connection in the prior art, the utility model discloses a force transmission structure of a launch rocket of an unmanned aerial vehicle based on surface contact, which is innovatively changed into surface connection, the thrust of the launch rocket is transmitted to the unmanned aerial vehicle in the form of surface load, the contact range is large, and the center of mass can be easily covered, so that the machining precision requirement of the connection structure and the rocket is greatly reduced, and the control difficulty of the control system is also reduced.

[0018] Compared with the prior art in which the thrust acts on the front head or the front top cover of the launch rocket, the utility model discloses that the force transmission cylinder is connected with the skirt of the launch rocket, the thrust of the launch rocket is directly transmitted to the force transmission cylinder through the skirt, the thrust is avoided to be transmitted to the front head or the front top cover, and the thickness of the front head or the front top cover can be reduced. In addition, the thrust is also transmitted to the cylindrical segment of the combustion chamber shell of the launch rocket through the skirt, so that the cylindrical segment is subjected to pressure, the pressure and the tensile stress generated by the internal pressure applied to the cylindrical segment of the combustion chamber shell of the launch rocket during operation are offset to each other, the stress level of the cylindrical segment of the combustion chamber shell of the launch rocket is reduced, the stability of the launch rocket is improved, and the utility model is suitable for large-scale use and popularization in industry. BRIEF DESCRIPTION OF DRAWINGS

[0019] Fig. 1 is the connection structure diagram of the force transmission cylinder and the unmanned aerial vehicle in the utility model;

[0020] Fig. 2 is the force transmission structure diagram of the launch rocket of the unmanned aerial vehicle based on surface contact in the utility model;

[0021] Fig. 3 is the force transmission cylinder structure diagram in the utility model.

[0022] The meanings of various reference numerals in the drawings are as follows: 1, unmanned aerial vehicle; 2, launch rocket; 3, force transmission cylinder; 4, weight reduction groove; 5, adapter plate. DETAILED DESCRIPTION

[0023] It should be noted that all components in the utility model, such as no special description, all adopt the components known in the prior art.

[0024] The following gives the specific embodiments of the utility model, it should be noted that the utility model is not limited to the following specific embodiments, and equivalent transformations made on the basis of the technical solutions of the application all fall within the protection scope of the utility model.

[0025] As shown in Figs. 1 to 3 A surface contact based unmanned aerial vehicle launch rocket force transmission structure, comprising an unmanned aerial vehicle 1 and a launch rocket 2 for boosting the unmanned aerial vehicle 1, and a transmission cylinder 3 coaxially fixedly connected to the launch skirt at the top end of the launch rocket 2.

[0026] The transmission cylinder 3 is cylindrical, and the outer diameter of the transmission cylinder 3 is equal to the outer diameter of the launch rocket 2; a plurality of lightening grooves 4 are uniformly provided on the transmission cylinder 3 in the circumferential direction, and an adapter plate 5 is fixedly connected to the top end of the transmission cylinder 3.

[0027] The adapter plate 5 is matched in shape with the lower part of the unmanned aerial vehicle 1, and when the adapter plate 5 supports the lower part of the unmanned aerial vehicle 1, the projection of the contact surface of the adapter plate 5 along the central axis of the transmission cylinder 3 covers the center of mass of the unmanned aerial vehicle 1.

[0028] The outer shape of the adapter plate 5 is matched with the fuselage of the unmanned aerial vehicle 1, and the adapter plate 5 serves to connect the unmanned aerial vehicle 1 and the transmission cylinder 3, and to transmit the force transmitted by the launch rocket 2 to the fuselage of the unmanned aerial vehicle 1, while dispersing the force.

[0029] The lightening grooves 4 are uniformly distributed on the transmission cylinder 3 in the circumferential direction, thereby reducing the weight of the transmission cylinder 3.

[0030] In the surface contact based unmanned aerial vehicle launch rocket force transmission structure of the embodiment, the connection between the adapter plate 4 and the unmanned aerial vehicle 1 is surface contact, and the thrust of the launch rocket 2 is transmitted to the unmanned aerial vehicle 1 in the form of surface load, so that the contact range is large and the center of mass is more easily covered, thereby achieving higher stability.

[0031] The transmission cylinder 3 is connected to the launch skirt of the launch rocket 2, and the thrust of the launch rocket 2 is directly transmitted to the transmission cylinder 3 through the skirt, thereby avoiding the transmission of the thrust to the front head or the front top cover. In addition, the thrust also transmits the force to the combustion chamber shell cylindrical segment of the launch rocket 2 through the skirt, so that the cylindrical segment is subjected to pressure, and this pressure and the tensile stress generated by the internal pressure applied to the combustion chamber shell cylindrical segment when the launch rocket 2 is working are offset to each other, thereby reducing the stress level of the combustion chamber shell cylindrical segment.

[0032] As a preferred solution, the weight-reducing groove 4 is a through strip-shaped groove, and the weight-reducing groove 4 extends along the length direction of the force transmission cylinder 3. Such a distribution manner makes the force transmission cylinder 3 bear the force more uniformly while reducing the mass of the force transmission cylinder 3, and further ensures the stability.

[0033] Specifically, the force transmission cylinder 3 and the adapter plate 5 are fixedly connected through welding.

[0034] The force transmission cylinder 3 and the launch rocket 2 are fixedly connected through bolt connection, welding or flange connection.

Claims

1. A force transmission structure for a drone launch rocket based on surface contact, comprising a drone (1) and a launch rocket (2) for boosting the drone (1), characterized in that, The launch skirt at the top end of the launch rocket (2) is coaxially fixedly connected with the force transmission cylinder (3); The force transmission cylinder (3) is cylindrical, the outer diameter of the force transmission cylinder (3) is equal to the outer diameter of the launch rocket (2); a plurality of lightening grooves (4) are uniformly formed on the force transmission cylinder (3) in the circumferential direction; and the top end of the force transmission cylinder (3) is fixedly connected with the adapter plate (5). The adapter plate (5) is matched with the shape of the lower part of the unmanned aerial vehicle (1); when the adapter plate (5) supports the lower part of the unmanned aerial vehicle (1), the projection of the contact surface of the adapter plate (5) and the unmanned aerial vehicle (1) along the central axis of the force transmission cylinder (3) covers the center of mass of the unmanned aerial vehicle (1).

2. The face contact based transfer of forces structure for unmanned aerial vehicle launch rocket as claimed in claim 1, wherein, The lightening groove (4) is a through strip-shaped groove, and the lightening groove (4) extends along the length direction of the force transmission cylinder (3).

3. The face contact based transfer of forces structure for unmanned aerial vehicle launch rocket as claimed in claim 1, wherein, The force transmission cylinder (3) and the adapter plate (5) are fixedly connected through welding.

4. The face contact based transfer of forces structure for unmanned aerial vehicle launch rocket as claimed in claim 3, wherein, The force transmission cylinder (3) and the launch rocket (2) are fixedly connected through bolt connection, welding or flange connection.

Images