A device for accelerating the separation of aircraft head and body

An aircraft and head-body technology, applied in the field of devices for accelerating the separation of the aircraft head and body, can solve the problems of slow head-body separation and easy structural interference, and achieve the effects of low cost, simple structure, and convenient operation

Inactive Publication Date: 2017-05-10
BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem of the present invention is: to overcome the deficiencies of the prior art, the present invention provides a head-body separation device for an accelerated aircraft to solve the problems of slow head-body separation and easy structural interference in the prior art

Method used

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  • A device for accelerating the separation of aircraft head and body
  • A device for accelerating the separation of aircraft head and body
  • A device for accelerating the separation of aircraft head and body

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Embodiment Construction

[0015] The present invention will be further described below in conjunction with accompanying drawing description and specific embodiment:

[0016] The present invention is a device for accelerating the separation of the aircraft head and body. By providing separation mechanical force to the warhead body 1 in the separation process, and guiding at the same time, it plays the role of assisting the separation of the head and body; wherein, the force is through the compression spring 3- 4, for different aircraft, different compression springs 3-4 can be used as required to provide different separation forces. The body 3-1 of the separation device 3 is a symmetrical structure, and an inner hole is arranged on each symmetrical structure, the front end of the inner hole (that is, the end that is docked with the aircraft warhead body 1) is a guide hole, and the other end of the inner hole is an internal thread. hole, the diameter of the internally threaded hole is greater than the di...

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Abstract

A device for accelerating separation of the head and the body of an aircraft comprises a device body (3-1), a central spindle (3-2), a compression spring (3-4) and a blanking cap (3-3), wherein two inner holes are symmetrically formed in the device body (3-1), one end of each inner hole serves as a guiding hole, the other end of each inner hole serves as an internal threaded hole, the diameter of each guiding hole is smaller than that of the corresponding internal threaded hole, one end of the central spindle (3-2) is connected with the blanking cap (3-3), an outer stud is arranged at one end of the blanking cap (3-3), a positioning flange is arranged at the other end of the blanking cap (3-3), a through hole is formed in the axial center of the blanking cap (3-3), an outer stud of the central spindle (3-2) extends out of the through hole after the outer stud of the blanking cap (3-3) is screwed into one internal threaded hole of the device body, and the compression spring (3-4) is arranged between the blanking cap (3-3) and the central spindle (3-2). By the adoption of the device (3), the head and the body of the aircraft can be separated quickly and reliably.

Description

technical field [0001] The invention relates to a separation device, in particular to a device for accelerating the separation of aircraft head and body. Background technique [0002] In modern warfare, missile weapons are playing an increasingly important role. It can be said that they are the key to affecting the entire war situation, and they are also a symbol of a country’s military strength. At the end of the flight, missile weapons often need to separate the head and body to reduce the impact of missiles. Weight, to achieve the greatest attack effect; missile weapons need to overcome air resistance at the moment of separation of the head and body. At present, the existing energy sources that can provide separation power are reverse thrust rockets, gas generators, electric boosters, etc., and there is not enough space And reasons such as higher cost, all can not satisfy the demand of product. Contents of the invention [0003] The technical problem of the present inv...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/36
Inventor 李京苑吴学森孙向春刘宁刘文伶
Owner BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE
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