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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。
In order to launch 10kg micro-satellites for space mission background, the main performance parameters of aspirated laser propulsion are analyzed based on the design indexes of ground thrust 1000N. According to the established laser propulsion energy similarity law theory and numerical calculation results, , The focusing system and the nozzle subsystem were designed to complete the concept of a closed aspirating laser thruster cycle. The proposed conceptual model of the aspirating laser thruster combining the secondary reflective focusing system with the parabola nozzle was verified by numerical calculation program to obtain an impulse coupling coefficient of 500 N / MW on the ground. The proposed design theory and method have certain reference value for the conceptual design of laser thruster, which is an important foundation for the development of laser thruster model.