Station-keeping for a solar sail during lander/probe deployment using feedback control

Due to its propellantless nature, a solar sail can provide the primary propulsion system for high energy mission, such as that of multiple asteroid rendezvous. Upon arrival at an asteroid, it is often desirable interact with surface body, sample extraction. The deployment lander from carries difficulty instantaneous, and sometimes considerable, change dynamics point separation. This paper investigates effects changing performance during release “ChipSat” probes well large MASCOT-type control into positional hold equilibrium or periodic orbit. In one scenario, 20 ChipSat are released, one-hour spacing between each release. then controlled maintain sailcraft close initial point. Linear Quadratic Regulator (LQR) compared maintaining fixed attitude after deployment. second separation larger lander, there will be considerable instantaneous in characteristic acceleration, opposed gradual small staggered probes. It shown Time-Delayed Feedback Control (TDFC) method effective controlling orbit this converges same region phase space when made both lower higher inclination