Active damping device of solid rocket engine

Abstract

The invention discloses an active damping device for a solid rocket engine, which comprises a test engine main body and an engine supporting structure, and the engine supporting structure supports the test engine main body; the main body of the test engine is a projectile body, the shell is of a porous sandwich layer structure and sequentially comprises an outer shell layer, a porous structure layer and an inner shell layer from outside to inside, and a heat insulation layer and a propellant are arranged in the inner shell layer; according to the engine supporting structure, one end of a sliding rail is connected with triangular leaning iron and installed on a base; one end of the thrust frame is connected with the triangular leaning iron, and the other end is connected with the front sealing head; the limiting stopper and the rear hanging bracket are connected with the sliding rail through the sliding block, one end of the spraying pipe of the shell is hung on the rear hanging bracket, and the limiting stopper is located between the thrust frame and the rear hanging bracket. Combustion chamber pressure and structural vibration caused by nonlinear excitation of an engine in a free trajectory can be weakened to a great extent, and the stability of the engine is enhanced.

Description

technical field [0001] The invention belongs to the technical field of rocket motor power systems, and in particular relates to an active vibration damping device for a solid rocket motor. Background technique [0002] The different stability characteristics of solid rocket motor test flight and ground stationary test show that the different experimental conditions between test flight test and ground stationary test affect the experimental study of engine instability. In the air test flight experiment, the engine moves with the projectile body and has six degrees of freedom. In the ground static test, due to the existence of constraints, the engine casing mode is different from that in the test flight test, resulting in different differences. the experimental results. Under free flight conditions, solid rocket motors are also affected by factors such as flight altitude, flight speed, and flight angle of attack. It will encounter typical nonlinear disturbances of outer ball...

AI Technical Summary

Problems solved by technology

under extreme conditions, some other components, such as the guidance system or the thrust vector control device, may fail, or even catastrophic failure of the launch mission

[0004] During the working process of the solid rocket motor, the engine will be affected by aerodynamic load, overload, and the response of the body structure, and its stability will be greatly weakened

At the same time, it is difficult to accurately reflect the working characteristics of the engine under free ballistics on the static test run on the ground

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