摘要
电动力绳系离轨技术属于被动离轨方式,适用于火箭末级、失效卫星等废弃飞行器快速离轨。针对这项新颖的离轨技术,通过建立多场耦合摄动下的离轨动力学模型,研究并分析了该技术的离轨性能和适用的离轨任务类型,用于指导工程实践及控制方案设计。首先建立多场耦合摄动下的电动力绳系离轨动力学模型,基于数值仿真,验证该项技术的有效性及优越性,并重点研究了不同影响因素下的离轨性能,据此提出了系统参数的设置原则。再通过设置合理的系统参数,分析电动力绳系离轨技术的可适用任务类型。分析结果表明,电动力绳系离轨技术适用于非极轨道的废弃飞行器离轨任务。
The electrodynamics tethered deorbit technology is a novel way to remove abandoned spacecraft like upper stages or unusable satellites. The deorbit performance and applicability of the electrodynamics tethered deorbit system are analyzed. The electrodynamics tethered deorbit dynamics with multi-perturbation is formulated. Furthermore, the key impact factors, including mission parameters and system parameters, are analyzed. The following numerical simulations are undertaken to show the influence of the impact factors to the deorbit performance, based on which the applicability of the electrodynamics tethered deorbit technology are further analyzed. The analysis concludes that this technology shows a better deorbit performance for missions with non-polar orbits.
作者
张烽
申麟
吴胜宝
王小锭
王书廷
Zhang Feng Shen Lin Wu Sheng-bao Wang Xiao-ding Wang Shu-ting(R＆D Center, China Academy of Launch Vehicle Technology, Beijing, 100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2017年第3期6-11,共6页
Missiles and Space Vehicles
关键词
电动力绳系离轨技术
动力学模型
性能分析
任务适应性
The electrodynamics tethered deorbit technology
Dynamics modeling
Deorbit performance analysis
Applicability analysis
