Electrically controlled solid propellant rocket engine adjustable in thrust and capable of being started several times

Abstract

Disclosed is an electrically controlled solid propellant rocket engine adjustable in thrust and capable of being started several times. The engine comprises a combustion chamber, a spring, a movable insulating plate, an electrically controlled solid propellant grain column, a coplanar electrode, a heat insulation layer, a spraying pipe and a wiring column; a grain containing structure of the electrically controlled solid propellant grain column is tubular, and the grain column is pushed by utilizing the elastic force of the spring; the coplanar electrode is in contact with the burning end surface of the electrically controlled solid propellant grain column; the coplanar electrode comprises two identical porous electrodes, the two porous electrodes are connected to the two ends of a power supply respectively, certain voltage is loaded between the two porous electrodes, and the engine can achieve irrigation; the power supply is switched off, and the engine is powered off automatically; the engine can be started several times continuously. By changing the voltage value between the two porous electrodes, the thrust of the engine can be actively controlled in real time. The engine can replace a liquid attitude-orbit control and terminal correction engine and is applied to power devices or auxiliary power devices with engines adjustable in thrust and capable of being started severaltimes for meeting the requirements of aircrafts.

Description

technical field [0001] The invention belongs to the field of special solid propellant rocket motors, and relates to a thrust-adjustable and multiple-start rocket motor using electronically controlled solid propellants, in particular to realizing the active and real-time adjustment of the thrust of the motor by controlling the voltage loaded on both ends of the electrodes. It can be started multiple times in succession. Background technique [0002] The traditional solid propellant rocket motor cannot be turned off after starting, and the thrust is difficult to control. At present, the thrust control schemes of solid rocket motors mainly include: solid motors with adjustable nozzle throat, solid pulse motors with segmented charges, and passive decompression flameout motors. These engine schemes only use passive control means in terms of thrust control, generally prefabricated multi-stage thrust or multi-pulse thrust, and cannot actively and real-time perform thrust control a...

AI Technical Summary

Problems solved by technology

These engine schemes only use passive control means in terms of thrust control, generally prefabricated multi-stage thrust or multi-pulse thrust, and cannot actively and real-time perform thrust control according to changes in flight conditions, and the thrust adjustment response is slow; the thrust of solid rocket motors is difficult to control. Multiple starts

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