摘要
研究了各种摄动因素对低月球卫星轨道的影响,通过建立环月轨道的计算模型,编制了相应的计算程序;分析了各种状态下低高度月球卫星圆轨道的摄动情况,并对极圆轨道月球卫星的摄动情况进行研究。通过算例及求解结果分析,验证了文中方法的可行性和正确性。该方法对于我国探月工程的轨道设计和计算具有重要的理论意义和参考价值。
It is well known that the orbit of lunar satellite varies considerably due to perturbation. We now present our results on analyzing and computing the orbit variations of low-altitude lunar satellite due to various perturbation forces. In the full paper, we explain what we do in detail; in the abstract we just add some pertinent remarks to listing the three topics of explanation： （1） the forces acting on low-altitude lunar satellite; under topic 1, we give the orders of magnitude of 11 perturbation forces; （2） the motion equation of low-altitude lunar satellite; under topic 2, we give eq. （1） in the full paper, which takes into consideration five main perturbation forces in addition to lunar gravitation; （3） the influence of five main perturbation forces on orbit of low-altitude lunar satellite; the subtopics are the influence of non-spherical perturbation force （subtopic 3.1）, the influence of the perturbation force due to the gravitation of earth （subtopic 3. 2）, the influence of the perturbation force due to the gravitation of sun（subtopic 3.3）, the influence of the perturbation force due to pressure of sunlight （subtopic 3. 4）, the influence of the perturbation force due to lunar tide （subtopic 3.5）, and the combined effect of all five above-mentioned perturbation forces（subtopic 3.6）; under subtopic 3.6, Fig. 1 in the full paper shows orbit variations due to all five perturbation forces. The calculation results indicate preliminarily that： （1） when all five perturbation forces are considered, the semi-major axis changes by up to about 1.4 km periodically and very frequently, 1.4 km being a little bigger than that for the case of considering only the influence of non- spherical perturbation forces; （2） eccentricity increases monotonically and the satellite impacts the moon surface on the 178th day; （3） orbit inclination changes by up to about 1.0° periodically every 14 days, 1.0° being a little bigger than that for the case of considering only the influence of non-spherical perturbation force; （4） the longitude of the ascending node also changes periodically and the biggest change within 178 days is about 1.5°, which is bigger than that for the case of considering only the non-spherical perturbation force; （5） when all five perturbation forces are considered, the change of argument of perigee resembles that for the case of only considering the non-spherical perturbation force; in both cases, it approaches a fixed value of about --40°.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2006年第5期649-652,共4页
Journal of Northwestern Polytechnical University
基金
西北工业大学科技创新基金(M450213)资助
作者简介
和兴锁（1952-），西北工业大学教授，主要从事航天器动力学与控制的研究。
