This paper presents a new model for modifying the relative orbit of a deputy satellite with respect to a chief satellite in a near-circular orbit using continuous periodic thrust. This model is built on the Lovell-Spencer relative orbital elements (ROEs). The four linear ROEs (xr, yr, ar, and Az) can be linearly modified. The two angular ROEs (Er and ψ) can be set to advance at a desired, constant rate. Each ROE can be modified individually, but may cause intra-orbit variations in other ROEs which return to their original values at the end of a thrust cycle. Derivation of the model is presented. A method to easily calculate the periodic thrust parameters is developed. Finally, GMAT results are used to demonstrate how each ROE can be linearly modified.
Guidance for Spacecraft Relative Motion Using Continuous Periodic Thrust
J Astronaut Sci
2025-01-23
Article (Journal)
Electronic Resource
English
Guidance for Spacecraft Relative Motion Using Continuous Periodic Thrust
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