抄録
Reusable spacecraft that are easy to maintain will be required for long term manned space activities. Generally solid propellants are better than liquid propellants in respect of thermal management and in their potential to harm the human body. Further, solid propellant rocket motors don't require special equipment for temperature controls or for countermeasures against harmful materials etc in space or lunar environments. Moreover, because of their simple structure maintenance can be easily undertaken. However, it is difficult to terminate and control the combustion of solid propellants once they are ignited in a conventional solid propellant rocket motor. The rocket motor I propose herein has ignition, combustion control, and extinction capabilities for solid propellants utilizing laser controls to overcome the inherent weaknesses with solid propellant rocket motors.
