Separation mechanism of oriented rocket nose body

Abstract

The invention relates to a separation mechanism of an oriented rocket nose body. The separation mechanism comprises four explosive bolts, a mounting plate, a support lug, four spring guide rods, four compression springs and a bottom plate, and is characterized by also comprising a top cylinder, four guide rods and four top plates; one end of the top cylinder is fixedly connected to the middle part of the mounting plate, and the other end of the top cylinder is provided with two boss structures; the four guide rods pass through a through hole of a boss in the end part and are fixedly connectedto the other boss; the top plates are arranged at one end of each of the compression springs; and the four top plates compress the four compression springs and are clamped on the boss on the end partof the top cylinder. By the separation mechanism, the rocket nose body can be connected reliably during flight, a combination body of a cabin body and a rocket body can be cast quickly and stably along the axial direction after a deblocking instruction is received, and effective loads inside the cabin body are impacted, damaged and polluted in the separation process so as to provide an excellent installation environment for the subsequent operation of the effective loads.

Description

technical field [0001] The invention relates to a rocket head body separation mechanism, in particular to a guided rocket head body separation mechanism, which is suitable for reliable connection before the separation of the rocket head body, and ensures a stable movement posture of the rocket body after separation. A separation mechanism that does not contaminate the internal payload. Background technique [0002] The separation mechanism requires reliable connection and separation, small interference, simple structure, safety and reliability. Commonly used connection and unlocking devices include mechanical type, tandem device of clasp belt and explosive bolt, non-fragment explosive bolt, linear explosive cable, etc., which often use the compression potential energy of gunpowder explosion gas, spring compression potential energy and engine thrust as the separation impulse device. According to the technical requirements of the payload carried by the rocket, the payload ca...

AI Technical Summary

Problems solved by technology

In section 6-5 of "Missile and Spacecraft Structural Analysis and Design" (Northwestern Polytechnical University Press, first edition in October 1995), a spring-type separation device is mentioned, but the device is unlocked by gunpowder force and spring force Separation, synchronization is difficult to guarantee, reliability is low, and the attitude of the separated part cannot be guaranteed

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