Station-keeping method for libration point trajectories
Station-keeping method for libration point trajectories
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DOI：
10.2514/3.11440
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发表时间：
1993-02
影响因子：
2.6
通讯作者：
K. Howell;H. Pernicka
中科院分区：
文献类型：
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作者：
K. Howell;H. Pernicka
目前正在考虑将日-地/月重心系统内部平动点(LI)附近的三维轨道用于计划在1990年代进行的一些飞行任务。由于这种平动点轨迹通常是不稳定的，在这些路径上运动的航天器必须使用某种形式的轨迹控制，以保持接近其标称轨道。这项努力的主要目标是制定一项适用于此类轨迹的站位保持战略。提出了一种使用以离散时间间隔(脉冲)执行的机动的方法。该分析包括对影响总体机动成本的一些问题参数的一些调查。仿真的目的是提供航天器在平动点轨道上移动的代表性保持站成本，并总结了初步结果。计划在1990年代发射的一些科学计划包括可能使用L内部附近的三维日晕或李萨如轨道！太阳-地球/月球重心系统的平动点1这项工作旨在开发一种保持静止的战略，该战略可用于将航天器维持在这样的标称平动点附近。已经完成了相当多的分析，涉及地球围绕卫星轨道的站位保持方法；然而，将航天器维持在平动点轨道上受到的关注有限。在20世纪60年代末，Far-quhar2发展了一些可能的平动点轨道的站位保持策略。后来，在1974年，Breakwell等人发表了一种在地月平转点L2附近沿光环轨道运动的航天器的站位保持方法。3相反，特定的任务要求影响了第一次平动点任务的站位保持战略的设计。当国际太阳-地球探索者3号卫星被送入与地球内部有关的光晕轨道时，L！1978年，在太阳-地球系统的平动点，一系列大约每隔三个月执行一次的机动用于保持静止。4最近，一系列论文提出了使用Floquet和不变流形理论来发展晕型轨道的“松散”静止保持策略的研究结果。5“8与ISEE-3类似，该方法也使用离散的机动，以不同的时间间隔控制标称轨道附近的轨道。这项研究的一个重要目标是开发一种潜在的“紧”控制策略，用于光晕和李萨如轨迹(以及其他可能类型的振动点路径)。在这种方法中，实际弹道相对于标称弹道的允许偏差可以根据任务要求在很大范围内变化。当然，低成本也是可取的。
Three-dimensional orbits in the vicinity of the interior libration point (Li) of the Sun-Earth/Moon barycenter system are currently being considered for use with a number of missions planned for the 1990s. Since such libration point trajectories are, in general, unstable, spacecraft moving on these paths must use some form of trajectory control to remain close to their nominal orbit. The primary goal of this effort is the development of a Stationkeeping strategy applicable to such trajectories. A method is presented that uses maneuvers executed (impulsively) at discrete time intervals. The analysis includes some investigation of a number of the problem parameters that affect the overall maneuver costs. Simulations are designed to provide representative station- keeping costs for a spacecraft moving in a libration point trajectory, and preliminary results are summarized. RAJECTORY planning for a number of scientific mis- sions scheduled for launch in the 1990s includes the possi- ble use of three-dimensi onal halo or Lissajous orbits in the vicinity of the interior L! libration point of the Sun-Earth/ Moon barycenter system.1 This effort is directed toward the development of a Stationkeeping strategy that can be used to maintain spacecraft near such nominal libration point trajec- tories. A significant number of analyses have been completed that involve Stationkeeping methods for Earth orbiting satel- lites; maintaining a spacecraft on a libration point orbit, how- ever, has received limited attention. In the late 1960s, Far- quhar2 developed a number of possible Stationkeeping strat- egies for libration point orbits. Later, in 1974, a station- keeping method for spacecraft moving on halo orbits in the vicinity of the Earth-Moon translunar libration point L2 was published by Breakwell et al. 3 In contrast, specific mission requirements influenced the design of the Stationkeeping strat- egy for the first libration point mission. When the Interna- tional Sun-Earth Explorer-3 (ISEE-3) satellite was injected into a halo orbit associated with the interior L! libration point of the Sun-Earth system in 1978, a series of maneuvers exe- cuted at approximately three-month intervals was used for Stationkeeping.4 More recently, a series of papers have pre- sented results from studies that use Floquet and invariant manifold theories to develop a ''loose" Stationkeeping strat- egy for halo-type orbits.5"8 Similar to ISEE-3, the method also uses discrete maneuvers, applied at varying time intervals, that control the trajectory near the nominal path. A significant goal of this study is the development of a potentially ''tight" control strategy for Stationkeeping that can be applied to both halo and Lissajous trajectories (as well as other possible types of libration point paths). In this approach, the allowable deviation of the actual trajectory relative to the nominal path can be varied over a wide range depending on mission require- ments. Of course, low costs are desirable as well.