Single-compartment dual-thrust solid rocket engine and rocket

Abstract

The invention provides a single-compartment dual-thrust solid rocket engine and a rocket. The engine comprises a combustion chamber housing, a heat insulating layer attached to the inner surface of the combustion chamber housing, a propellant grain positioned in the combustion chamber housing, an igniter arranged at one end of the combustion chamber housing and a spray tube assembly arranged at the other end of the combustion chamber housing, wherein the propellant grain is provided with an inner hole which penetrates through the two ends of the propellant grain; the position, at one end closeto the igniter, of the inner hole, of the propellant grain is uniformly provided with a front wing slot which extends in a radial direction, and the position, at one end close to the spray tube assembly, of the inner hole, of the propellant grain is provided with a tail wing slot which extends in the radial direction; a ratio of wing slot depth of the front wing slot and the tail wing slot to thebiggest thickness of the propellant grain is greater than or equal to 0.81; and the slope range of the rear wing axial slope of the grain ranges from 160 degrees to 170 degrees. The single-compartment dual-thrust solid rocket engine is great in thrust change range, is stable in grain structure, is small in grain combustion surface change speed while an engine thrust mode is converted, can effectively reduce pressure intensity change speed of the combustion chamber, and enables thrust change speed to be gentle.

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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