RELATIVE 6 FREEDOM CONTROL METHOD OF ARTIFICIAL SATELLITE

Japanese Patent JP3880405

B2

PROBLEM TO BE SOLVED: To solve a problem that a mountable amount of a thrust agent determines a life of a mission since a thrust system actuator has controlled a relative attitude and a relative position, that a risk such as explosion of the thrust agent is generated and that an orientation or a mounted position of a thruster becomes a problem.
SOLUTION: This artificial satellite A controls its attitude so that an instructed orientation is held against an inertial space using an attitude detection sensor 11a and a wheel 12a and generates an alternating current magnetic field to be a standard of an alternating current magnetic field generating device 13a. An artificial satellite B generates a rectilinear force and a rotary force of the satellite B against the satellite A by synchronizing or displacing the phase or magnitude of an alternating current magnetic field generating device 13b according to the distance and angle of an identification plate 14 on the satellite A measured using a relative position/relative attitude detection sensor 15 so that they become specified distance and angle in order to give feedback control. The satellite B uses attitude control using both the attitude detection sensor 11b and the wheel 12b in order to control the relative attitude.

Toru Saito
Ken Maeda

JP2002010937A

February 14, 2007

January 21, 2002

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NEC Aerospace Systems Co., Ltd.
nec Toshiba Space Systems Co., Ltd.

B64G1/32; (IPC1-7): B64G1/32

JP61200100A
JP3031100A
JP4293698A
JP5338598A
JP4071999A
JP5124569A
JP61006099A

US6089510
US3794270

Kaneyuki Matsuura

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