Interstage cold separation structure of carrier rocket

Abstract

The invention discloses an interstage cold separation structure of a carrier rocket. The interstage cold separation structure comprises a front cabin body, a rear cabin body, and a separation spring assembly. The tail end of the front cabin body is connected with a separation spring ejector rod support. The front end of the rear cabin body is connected with the tail end of the front cabin body through an interstage separation connection unlocking device; and the rear cabin body is connected with a separation spring support base corresponding to the position of a separation spring ejector rod bracket; the interstage separation connection unlocking device is used for locking the front cabin body and the rear cabin body and unlocking the front cabin body and the rear cabin body after receiving a separation instruction. The separation spring assembly is elastically supported between the separation spring support base and the separation spring ejector rod bracket and is provided with an elastic piece for providing a separation impulse for the front cabin body and the rear cabin body. Since the separation spring assembly is arranged between the front cabin body and the rear cabin body, when the interstage separation connection unlocking device is disconnected under fire work, the elastic piece of the separation spring assembly generates an acting force for driving the front cabin body and the rear cabin body to be away from each other, so that the separation speed of the front cabin body and the rear cabin body is increased, and the safety during rocket body separation is improved.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to an interstage cold separation structure of a launch vehicle. Background technique [0002] The launch vehicle is usually used as a vehicle to send payloads such as various satellites into space. The launch vehicle is usually composed of 2 to 4 stages, and each stage includes electrical equipment, load-bearing structures, and power systems. [0003] Whenever the lower stage completes the work, the launch vehicle must abandon the lower stage to improve the carrying capacity and ensure that the payload enters space, so the launch vehicle needs to design an inter-stage separation structure. [0004] Currently, there are two main methods of separation between stages of launch vehicles: thermal separation and cold separation. Hot separation means that when the upper stage engine is started and the rear cabin and the front cabin have not been separated, the thrust of the upper stage...

AI Technical Summary

Problems solved by technology

[0007] Therefore, the technical problem to be solved by the present invention is to overcome the problems of low separation speed and possible collision between the front and rear cabins of the carrier rocket in the prior art when the stage is separated, so as to provide a cold separation structure between the stages of the carrier rocket

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