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Two-impulse Rendezvous Planning about Thrusting Spacecraft on $\mathrm{SE}_2(3)$
The classical Hill--Clohessy--Wiltshire equations assume an unforced Keplerian reference trajectory, an assumption that is violated by missions requiring continuous thrust. We address this limitation with a relative motion framework on the $\mathrm{SE}_2(3)$ Lie group that encodes position, velocity
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