吸气式激光推力器概念设计

推进技术 ›› 2009, Vol. 30 ›› Issue (6): 745-750.

吸气式激光推力器概念设计

洪延姬,文明,曹正蕊

装备指挥技术学院;装备指挥技术学院;装备指挥技术学院

发布日期:2021-08-15
基金资助:
国家“九七三”(61328);国家自然科学基金(10672184)

Concept design of the air-breathing laser thruster

Inst. of Equipment Command and Technology, Beijing 101416, China;Inst. of Equipment Command and Technology, Beijing 101416, China;Inst. of Equipment Command and Technology, Beijing 101416, China

Published:2021-08-15

摘要/Abstract

摘要： 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。

关键词: 激光推进;吸气式+;激光推力器+;概念设计+;设计循环+

Abstract: 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 analysis 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.

Key words: Laser propulsion;Air-breathing mode+;Laser thruster+;Concept design+;Design cycle+

洪延姬,文明,曹正蕊. 吸气式激光推力器概念设计[J]. 推进技术, 2009, 30(6): 745-750.