Optimal Projected Circular Orbit for Spacecraft Formation Flying Near a Slowly Rotating Asteroid
Optimal Projected Circular Orbit for Spacecraft Formation Flying Near a Slowly Rotating Asteroid
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DOI：
10.1109/taes.2022.3173247
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发表时间：
2022-12
影响因子：
4.4
通讯作者：
Wei Wang;Di Wu;Ran Sun;H. Baoyin
中科院分区：
文献类型：
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作者：
Wei Wang;Di Wu;Ran Sun;H. Baoyin
在航天器编队飞行任务中，投影圆（相对）轨道（PCO）沿着名义主航天器的天顶-天底方向看呈圆形，适合于构造合成孔径雷达。研究了航天器编队近飞慢转小行星时的PCO问题。通过匹配面内和面外相对运动频率，确定表征PCO的初始相位角的临界值，从而使相对轨道进动最小。然后，利用分析开发的燃料最优控制律，建立一个目标PCO。特别是，采用间接方法解决燃料最优问题，其中采用同伦方法，并使用缩放技术计算初始（未知）共态向量，从而减轻了对初始猜测问题的敏感性。
In spacecraft formation flying missions, the projected circular (relative) orbit (PCO), which appears circular when viewed along the zenith-nadir direction of the nominal chief spacecraft, is suitable for constructing a synthetic aperture radar. In this paper, the analysis of a PCO for spacecraft formation flying near a slowly rotating asteroid is conducted. By matching the in-plane and out-of-plane relative motion frequency, the critical values of the initial phase angle that characterizes the PCO are identified, resulting in the minimum precession of relative orbit. The analysis is then utilized to develop the fuel-optimal control law for establishing a target PCO. In particular, the fuel-optimal problem is addressed with an indirect method, where a homotopy approach is adopted, and the initial (unknown) costate vector is calculated with a scaling technique, so that the sensitivity to the initial guess problem is mitigated.