首页>
外国专利>
method for satellites in non koplanare orbits using very excentrischen orbits and atmospheric resistance, at the same time, to bring
method for satellites in non koplanare orbits using very excentrischen orbits and atmospheric resistance, at the same time, to bring
展开▼
机译：同时使用非中心轨道和大气阻力的非科普兰轨道卫星的方法
展开▼
页面导航
摘要
著录项
相似文献
摘要
The method involves placing a first satellite virtually directly in its final orbit (15) using a launch vehicle. A second satellite carried by the same launcher is then transferred into a highly-elliptical parking orbit (12bis) with its longer orbit situated in the initial orbital plane (12). At a point close to the apogee (19) of the parking orbit, the orbit is changed to place the second satellite in an intermediate orbit (14) with a different angle of inclination. The second satellite's intermediate orbit is subjected to atmospheric braking close to its perigee (6a,6b) with a view to reducing the altitude of its apogee (19,19a,19b,19c), and it is then given a booster thrust at the lowest point of its apogee (19c) to lift the perigee and transform the intermediate orbit into a final orbit (11) with parameters substantially different from those of the first satellite's final orbit.
展开▼
