Slew Control of Prolate Spinners Using Single Magnetorquer
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-...
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| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
| Published: |
American Institute of Aeronautics and Astronautics
2016
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| Subjects: | |
| Online Access: | http://ir.unimas.my/id/eprint/39136/5/Slew%20Control%20-%20Copy.pdf http://ir.unimas.my/id/eprint/39136/ https://arc.aiaa.org/journal/jgcd |
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| Summary: | 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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