摘要
空间碎片减缓的积极措施之一是要求近地卫星在使命完成以后进行离轨机动,然后依靠大气阻力作用使卫星在不到25年的时间内自行消失．对此,研究了离轨机动的代价与使命后寿命的关系,提出并解决了正问题和逆问题;介绍了计算卫星寿命的高效率方法．为近地轨道卫星的设计提供了处理离轨机动问题的实用方法．
One of the measures of Space Debris Mitigation is to execute a deorbit maneuver after the mission of LEO completed, and the satellites die out gradually by the drag of atmosphere in 25 years. Some fuels are needed in deorbit maneuver, so deorbit maneuver must be considered in the phase of satellite overall design. The relations of orbital parameters of LEO, cost of deorbit maneuver and existent lifetime must be studied deeply. The theories and methods of solving deorbit maneuver are explained. A highly effective method of calculating orbit lifetime is introduced： method of differential-integral, and its correctness and validity are validated. The relation of aftermission orbit lifetime and expense of deorbit maneuver is studied. The positive question and the contrary question are presented and solved. The infections of other factors such as F10.7 and s acting on those relations are studied, and estimate values are provided. Some computing results are provided, and are analyzed and summarized. An applied method dealing with question of deorbit maneuver is provided for the design of LEO.
出处
《空间科学学报》
CAS
CSCD
北大核心
2006年第2期155-160,共6页
Chinese Journal of Space Science
基金
国家航天局空间碎片行动计划资助
关键词
空间碎片
使命后寿命
轨道机动
轨道动力学
Space debris, Postmission orbit lifetime, Orbit maneuver, Orbit dynamics
