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.