吸气式激光推力器概念设计

以发射10kg级微小卫星为航天任务背景,基于地面推力1000N的设计指标,分析了吸气式激光推进的主要性能参数,依据所建立的激光推进能量相似律理论和数值计算研究结果,对激光参数、聚焦系统和喷管子系统进行设计,完成了封闭的吸气式激光推力器概念设计循环。所提出的二次反射聚焦系统与抛物形喷管组合的吸气式激光推力器概念模型经数值计算程序验证,可以获得地面500N/MW的冲量耦合系数。所提出的设计理论和方法对激光推力器概念设计有一定的参考价值,是研制激光推力器模型的重要基础。

Concept design of the air-breathing laser thruster

In order to launch a 10-kg micro satellite and acquire a 1000-N ground thrust, the main propulsion performance parameters for air-breathing laser propulsion were analyzed. According to the research results of energy law of similitude by a-nalysis and simulation, a closed concept design cycle for air-breathing laser thruster was accomplished, including incident laser parameters, focusing system and nozzle subsystem. Combining a twice reflection focusing system with a parabolic nozzle, the air-breathing thruster concept model presented here can gain a 500-N/MW ground impulse coupling coefficient validated by numerical simulation. The design theory and method presented here provides some valuable reference for concept design of laser thruster, and become an important basis for developing model for laser thruster.