CN-114684364-B - Missile and unmanned aerial vehicle organism separator and unmanned aerial vehicle

CN114684364BCN 114684364 BCN114684364 BCN 114684364BCN-114684364-B

Abstract

The invention discloses a missile and unmanned aerial vehicle body separation device and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles and missiles, wherein the device comprises a missile body flange, a missile body and a missile body connecting device, wherein one side of the missile body flange is used for being connected with the tail of the missile body; the unmanned aerial vehicle comprises a body flange, a wrapping belt assembly, a separating spring, a pulling spring and a separating device, wherein one side of the body flange is used for being connected with the end part of an unmanned aerial vehicle body, the wrapping belt assembly comprises a wrapping belt and a plurality of clamping blocks, the wrapping belt is connected through a cutting structure to form an annular structure, when the wrapping belt forms the annular structure, the clamping blocks are circumferentially distributed on the inner side of the annular structure, clamping grooves are formed in the inner periphery of the clamping blocks, the separating spring is arranged between the body flange and the body flange, after the separating spring is compressed, the body flange and the body flange can be accommodated in the clamping grooves, the pulling spring is arranged between the wrapping belt assembly and the end part of the unmanned aerial vehicle body, and the separating device can realize rapid separation of a missile and the unmanned aerial vehicle body through the cutting structure, so that a rapid striking function of the missile and the unmanned aerial vehicle integrated aircraft is realized.

Inventors

WANG YANWEI
WANG ZONGHUI
SHI XUDONG
MA CUNWANG

Assignees

彩虹无人机科技有限公司

Dates

Publication Date: 20260512
Application Date: 20220325

Claims (7)

1. A missile and unmanned aerial vehicle body separator, characterized by comprising: the missile body flange is used for connecting one side of the missile body flange with the tail of the missile; the unmanned aerial vehicle comprises a body flange, wherein one side of the body flange is used for being connected with the end part of an unmanned aerial vehicle body; The belt assembly comprises a belt and a plurality of clamping blocks, wherein the belt is connected through a cuttable structure to form an annular structure, the clamping blocks are circumferentially distributed on the inner side of the annular structure when the belt forms the annular structure, and clamping grooves are formed in the inner periphery of the clamping blocks; the separating spring is arranged between the elastomer flange and the engine body flange, and after the separating spring is compressed, the elastomer flange and the engine body flange can be accommodated in the clamping groove; a pulling spring disposed between the strap assembly and an end of the unmanned aerial vehicle body; A plurality of clamping blocks are arranged on the inner side of the wrapping belt, and one side, close to the end part of the unmanned aerial vehicle body, between two adjacent clamping blocks is connected with the pulling spring; The fairing is tubular, two ends of the fairing are respectively used for connecting the tail periphery of the missile with the periphery of the end part of the unmanned aerial vehicle body, and the missile body flange, the body flange and the belting assembly are arranged in the fairing; the fairing comprises two sub fairings, the cross section of each sub fairing is semicircular, and the two sub fairings are detachably connected.
2. The missile and unmanned aerial vehicle body separation device of claim 1, wherein the severable structure includes an explosive bolt, the explosive bolt having respective ends connected to a perforated pin, the perforated pin being connected to an end of the strap.
3. The missile and unmanned aerial vehicle body separation device according to claim 2, wherein two straps are provided, each strap is semi-circular, pin sleeves are arranged at two ends of each strap, the perforated pins are arranged in the pin sleeves in a penetrating mode, and adjacent perforated pins are connected through explosion bolts.
4. The missile and unmanned aerial vehicle body separation device according to claim 2 wherein the perforated pin is provided with a through hole, and the end of the explosive bolt is threaded through the through hole and extends to the outside of the strap.
5. The missile and unmanned aerial vehicle body separation device of claim 1, wherein the missile body flange and the body flange are hollow annular flanges.
6. The missile and unmanned aerial vehicle body separation device of claim 1, wherein the other side of the missile body flange and the other side of the body flange are attached to form a V-shaped surface structure with a 60-degree cross section.
7. Unmanned aerial vehicle, characterized by comprising a missile and unmanned aerial vehicle body separation device according to any of claims 1-6.

Description

Missile and unmanned aerial vehicle organism separator and unmanned aerial vehicle Technical Field The invention belongs to the technical field of unmanned aerial vehicles and missiles, and particularly relates to a missile and unmanned aerial vehicle body separation device and an unmanned aerial vehicle. Background Unmanned aerial vehicle and guided missile are widely used, and small unmanned aerial vehicle has advantages such as portable, reconnaissance ability is strong, environmental suitability is strong, long duration, but also has the shortcoming that has the striking ability weaker. If a small missile is to be equipped on the unmanned plane, the striking capability is improved, but the striking distance is short and the reconnaissance capability is lacking. Therefore, how to simultaneously consider the advantages of the unmanned aerial vehicle and the missile can realize the integrated function of the small aircraft, and the research and development of the aircraft is a technical difficulty. Disclosure of Invention The invention aims at overcoming the defects in the prior art, provides a missile and unmanned aerial vehicle body separating device and an unmanned aerial vehicle, the separation device can realize the quick separation of the missile and the unmanned aerial vehicle body through the cut-off structure, and realize the quick striking function of the integrated missile and the unmanned aerial vehicle. In order to achieve the above object, the present invention provides a missile and unmanned aerial vehicle body separation device, including: the missile body flange is used for connecting one side of the missile body flange with the tail of the missile; the unmanned aerial vehicle comprises a body flange, wherein one side of the body flange is used for being connected with the end part of an unmanned aerial vehicle body; The belt assembly comprises a belt and a plurality of clamping blocks, wherein the belt is connected through a cuttable structure to form an annular structure, the clamping blocks are circumferentially distributed on the inner side of the annular structure when the belt forms the annular structure, and clamping grooves are formed in the inner periphery of the clamping blocks; the separating spring is arranged between the elastomer flange and the engine body flange, and after the separating spring is compressed, the elastomer flange and the engine body flange can be accommodated in the clamping groove; And the pulling spring is arranged between the wrapping belt combination body and the end part of the unmanned aerial vehicle body. Optionally, the severable structure includes an explosive bolt, two ends of the explosive bolt are respectively connected with a hole pin, and the hole pins are connected with the end parts of the wrapping belt. Optionally, the strap is provided with two, the strap is semi-circular, both ends of strap all are provided with the round pin cover, foraminiferous round pin wears to establish in the round pin cover, adjacent foraminiferous round pin passes through explosion bolted connection. Optionally, the inboard of band is provided with a plurality of fixture blocks, adjacent two between the fixture block be close to one side of the tip of unmanned aerial vehicle organism with draw the spring coupling. Optionally, the pin with holes is provided with a via hole, and the end part of the explosion bolt penetrates through the via hole and extends to the outer side of the wrapping belt. Optionally, the missile body comprises a shell body flange, a strap assembly and a shell body flange, wherein the shell body flange is arranged on the shell body, the strap assembly is arranged on the shell body, and the strap assembly is arranged on the shell body. Optionally, the fairing comprises two sub fairings, the cross section of each sub fairing is semicircular, and the two sub fairings are detachably connected. Optionally, the elastomeric flange and the body flange are hollow annular flanges. Optionally, the other side of the elastomer flange is jointed with the other side of the engine body flange to form a V-shaped surface structure with a section of 60 degrees. The invention also provides an unmanned aerial vehicle, which comprises the missile and unmanned aerial vehicle body separation device. The invention provides a missile and unmanned aerial vehicle body separation device and an unmanned aerial vehicle, which have the beneficial effects that the separation device is simple in structure, a missile body flange and a body flange are respectively arranged on the missile and unmanned aerial vehicle body, a V-shaped structure is formed after the missile body and the unmanned aerial vehicle body are in butt joint, a belting assembly is used for connection, movement of a belting to the unmanned aerial vehicle body in the belting separation process is realized by using a pulling spring, separation of the missile and the unmanned aerial vehicle body is realized by us