In this paper, the fuel-optimal control problem of multiple spacecraft formation flying with relative motion constaints is addressed via the indirect optimization method. As opposed to the most existing works where the formation deployment/reconfiguration problem is formulated on the chief-deputy topology or the total fuel consumption is optimized in the $\ell _{2}$-norm sense, the presented methodology manages to identify the $\ell _{1}$-optimal control law for a distributed formation structure, in which each spacecraft satisfies the periodicity (or energy-matching) condition and relative geometry requirement. In particular, the homotopic approach in conjunction with a linearization method is adopted so as to reduce the inherent sensitivity of the two-point boundary-value problem, and the fuel-optimal solution can be successfully targeted. The results are validated in Laser Interferometer Space Antenna, a project initiated for gravitational wave detection.
Fuel-Optimal Control for Multiple Spacecraft Formation Flying With Relative Motion Constraints
IEEE Transactions on Aerospace and Electronic Systems ; 60 , 6 ; 8569-8582
2024-12-01
2024999 byte
Article (Journal)
Electronic Resource
English
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