Adjustable double-pulse solid rocket engine jet pipe testing device

Abstract

The invention discloses an adjustable double-pulse solid rocket engine jet pipe testing device. The adjustable double-pulse solid rocket engine jet pipe testing device comprises a jet pipe base, a throat lining piece, an expanding section component, a safety pin, an upper shearing sleeve and a lower shearing sleeve, wherein the throat lining piece is arranged at the fuel gas inlet end of the jet pipe base, the expanding section component is arranged at the fuel gas outlet end of the jet pipe base, the throat lining piece is matched with an annular step surface in the jet pipe base in a positioned mode through an annular step surface in the axial direction of the throat lining piece, the safety pin penetrates through a pin hole in the wall of the jet pipe base to stretch into a pin hole in the expanding section component, the upper shearing sleeve is arranged between the safety pin and the jet pipe base, the lower shearing sleeve is arranged between the safety pin and the expanding section component, and matched threads are arranged at corresponding positions of the ends, close to the outer wall of the jet pipe base, of the safety pin and the jet pipe base. By the adoption of the adjustable double-pulse solid rocket engine jet pipe testing device, testing safety can be improved, and testing cost can be reduced.

Description

technical field [0001] The invention belongs to the field of solid rocket motor test research, in particular to an adjustable double-pulse solid rocket motor nozzle test device. Background technique [0002] With the continuous development of military science and technology, in order to improve the survival and penetration capabilities of missiles, the launch outside the defense zone and the variability of ballistics are emphasized. The pulse engine uses the isolation device to divide the combustion chamber into several parts. Through multiple shutdowns and ignitions, the thrust and each pulse time are reasonably distributed to achieve the optimal control of the flight trajectory and the optimal management of the engine energy. Taking the dual-pulse solid rocket motor as an example, compared with traditional single-thrust or single-chamber dual-thrust motors, it has a longer range, stronger maneuverability, and higher precision. [0003] Ground performance test research is ...

AI Technical Summary

Problems solved by technology

However, this method has some drawbacks

When the pressure relief hole set on the side of the head or the combustion chamber is working, the high-temperature and high-pressure gas ejected may damage the thrust sensor of the head and other data signal lines

In addition, when carrying out multiple tests, when the throat ablation is severe enough to fail to reach the design index, it is usually necessary to replace the entire nozzle assembly, which is not economical

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