A single-chamber double-thrust solid rocket motor and rocket

Abstract

The application provides a single-chamber double-thrust solid rocket motor and the rocket, wherein the motor includes a combustion chamber casing, a thermal insulation layer attached to the inner surface of the combustion chamber casing, a propellant grain located in the combustion chamber casing, and a The igniter at one end of the casing and the nozzle assembly arranged at the other end of the combustion chamber casing; the propellant grain is provided with an inner hole passing through both ends; The front wing slot extending to the direction, and the end of the inner hole close to the nozzle assembly is evenly provided with a radially extending tail slot; the ratio of the wing slot depth of the front wing slot and the tail slot to the maximum thickness of the propellant grain is greater than or equal to 0.81; The slope range of the axial slope of the rear wing of the grain column is 160-170 degrees. The present invention has a large thrust variation range and stable grain structure. When the thrust mode of the engine is switched, the combustion surface of the grain changes at a low speed, which can effectively reduce the pressure change speed of the combustion chamber and ease the thrust change speed.

Description

technical field [0001] The invention relates to aerospace power technology, in particular to a single-chamber double-thrust solid rocket motor and a rocket. Background technique [0002] Solid rocket motors have been widely used in various types of spacecraft due to their simple structure, reliable performance, and no maintenance, such as the Long March 11. A solid rocket motor generally consists of a combustion chamber casing, a propellant grain, a thermal insulation layer, a nozzle and an igniter. In general, single-chamber dual-thrust solid engines have a sharp change in thrust in order to achieve rapid conversion of braking force. The buffer transition for the change of the combustion surface of the grain is small, and the pressure in the combustion chamber changes rapidly. It will cause a sharp change in the dynamic pressure balance, resulting in a sharp change in the attitude of the rocket body, which will bring a great burden to the control system. In severe cases, ...

AI Technical Summary

Problems solved by technology

In general, single-chamber dual-thrust solid engines have a sharp change in thrust in order to achieve rapid conversion of braking force. The buffer transition for the change of the combustion surface of the grain is small, and the pressure in the combustion chamber changes rapidly. It will cause a sharp change in the dynamic pressure balance, resulting in a sharp change in the attitude of the rocket body, which will bring a great burden to the control system

In severe cases, the flight mission will fail

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