Slew Control of Prolate Spinners Using Single Magnetorquer

Juntian, Si and Yang, Gao and Abadi, Chanik (2016) Slew Control of Prolate Spinners Using Single Magnetorquer. JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS, 39 (3). pp. 715-723. ISSN 1533-3884

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Abstract

E XISTING research [1–5] on the prolate spinning spacecraft attitude maneuver has developed a series of slew algorithms using a single thruster in two categories: half-cone derived algorithms and pulse-train algorithms. Half-cone derived algorithms consist of half-cone (HC), multi-half-cone, dual-half-cone, extended half-cone, sector arc slew, and multisector arc slew, using the precession behavior of a spinning prolate spacecraft. Pulse-train algorithms consist of rhumb line and spin-synch algorithms, which use a train of uniform torque pulses to achieve the attitude maneuver. Pulse-train algorithms can also be used for oblate spacecraft. The existing slew algorithms have been initially developed for specific prolate spacecraft such as penetrators proposed in MoonLITE missions [6]. In the MoonLITE mission, a mothership releases missile-shaped penetrators equipped with thrusters for hard landing on the lunar surface from 100 km altitude. Before impact, a 90 deg spin axis attitude maneuver is required after spinning up the penetrator. The aforementioned slew algorithms can provide low-cost solutions to meet the required 90 deg attitude maneuver and within a small mass budget of the penetrator.

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