Rendezvous guidance trajectories via multiple-subarc sequential gradient-restoration algorithm

被引：0
|
作者：
Miele, A. [1 ]
Ciarcì, M. [1 ]
Weeks, M.W. [2 ]
机构：
[1] Rice Univ., Houston, TX 77005, United States
[2] NASA-Johnson Space Center, Houston, TX 77005, United States
来源：
Journal of Aerospace Engineering | 2009年 / 22卷 / 02期
关键词：
We consider the three-dimensional rendezvous between a target spacecraft in a circular orbit and a chaser spacecraft with an initial separation distance and an initial separation velocity. We assume that the chaser spacecraft has variable mass and that its trajectory is governed by three controls; one determining the thrust magnitude and two determining the thrust direction. We employ the Clohessy-Wiltshire equations; describing the relative motion of the chaser vis--vis the target; and the multiple-subarc sequential gradient-restoration algorithm to produce first optimal trajectories and then guidance trajectories for the following problems: P1-minimum time; fuel free; P2-minimum fuel; time free; P3-minimum time; fuel given; P4-minimum fuel; time given; and P5-minimum timefuel; time and fuel free. Clearly; P1 and P2 are basic problems; while P3; P4; and P5 are compromise problems. Problem P1 leads to a two-subarc solution including a max-thrust subarc followed by another max-thrust subarc. Problem P2 leads to a four-subarc solution including two coasting subarcs alternating with two max-thrust subarcs. Problems P5 leads to a three-subarc solution including two max-thrust subarcs alternating with one coasting subarc. Problems P3 and P4 include P1; P2; and P5 as particular cases and lead to two-; three-; or four-subarcs solutions depending on the prescribed value of fuel or time. For all problems; the thrust magnitude control is saturated at one of its extreme values: in optimization studies; we determine the best thrust direction controls; in guidance studies; we force the thrust direction controls to be constant in each subarc and determine the best thrust direction parameters. Of course; the time lengths of all the subarcs must also be determined. The computational results show that; for Problems P1-P5; the performance index of the multiple-subarc guidance trajectory approximates well the performance index of the multiple-subarc optimal trajectory: the pairwise relative differences in performance index are less than 1100 in all cases. To sum up; the produced guidance trajectories are highly efficient and yet quite simple in implementation. © 2009 ASCE;
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页码：160 / 172
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