Efficient force eliminator

Abstract

The invention discloses an efficient force eliminator comprising a shell. An air chamber channel is formed in the center of the shell, and used for a piston cylinder to pass through; the bottom end ofthe air chamber channel is connected with a thrust terminating device, and a first-stage diversion channel, a second-stage diversion channel, a first-stage guide plate and a second-stage guide plateare sequentially and symmetrically arranged on the two sides of the air chamber channel in the moving direction of the piston cylinder, and a necking-down piston cylinder outlet is formed in the top of the air chamber channel. According to the force eliminator, the two- stage diversion channels are arranged, so that gas is divided into five parts; the gas flow at the outlet of the piston cylinderis reduced, and meanwhile the two-stage guide plates are used for forming counter-acting force, so that residual thrust is reduced; impact disturbance borne by a rocket engine at the moment of thrusttermination is reduced; and the actually-measured force eliminating efficiency can reach 50%; the efficient force eliminator is simple in structure, light in weight, convenient in disassembly; and thestructure size can be adjusted to adapt to the thrust terminating devices in different sizes. A new scheme is provided for reducing impact and residual thrust when thrust of a small solid rocket engine is terminated.

Description

technical field [0001] The invention relates to the field of solid rocket motors, in particular to a high-efficiency silencer installed at the outlet of a thrust termination device of a small solid rocket motor. Background technique [0002] Thrust termination is a mature and effective technology to realize separation between solid rocket motor stages, adjust missile range and control flight accuracy, and start or terminate flight multiple times. It has been widely used in various large and medium-sized solid rocket motors at home and abroad. The existing small solid rocket motors are restricted by space constraints and technical requirements such as depressurization rate and thrust output. The thrust termination scheme mainly adopts the decompression flameout method, but this scheme has the following problems: [0003] a) There is a case where the charge cannot be extinguished after the action of the thrust termination device, that is, there is still residual thrust output ...

AI Technical Summary

Problems solved by technology

[0003] a) There is a case where the charge cannot be extinguished after the action of the thrust termination device, that is, there is still residual thrust output after the thrust termination;

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