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1.发明申请公开(公告)号：US20220402633A1
公开(公告)日：2022-12-22
申请号：US17791903
申请日：2020-02-26
发明人： Kenji KITAMURA , Takeya SHIMA , Katsuhiko YAMADA
摘要： In an orbital attitude control device (1150), an ideal thrust axis direction calculator (1505) calculates an ideal thrust axis direction based on information of a predetermined orbit, an ideal attitude calculator (1506) calculates an ideal attitude of the satellite based on the ideal thrust axis direction and a solar direction, and a control torque calculator (1510) calculates an ideal control torque that makes the attitude of the satellite follow the ideal attitude and a torque restraint plane in which the solar direction is orthogonal to a rotational axis of the solar array panel, defines an evaluation function obtained by weighting a distance from the ideal control torque and a distance from the torque restraint plane and then summing the weighted distances, and calculates the control torque that allows the drive constraint to be satisfied and the evaluation function to be minimized.
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公开(公告)号：US20170369192A1
公开(公告)日：2017-12-28
申请号：US15540726
申请日：2016-01-06
CPC分类号： B64G1/242 , B64G1/244 , B64G1/26 , B64G2001/245 , G05D1/08
摘要： A satellite comprises thrusters disposed with the firing directions each facing away from the mass center of satellite and different from each other. A control amount calculator calculates control amounts of the mean orbital elements from the mean orbital elements and the temporal change rates of the mean orbital elements set by an orbit determiner, and the target values. A distributor calculates firing timings and firing amounts of the thrusters for realizing the control amounts of the mean orbital elements by expressing a motion of satellite with orbital elements, solving an equation taking into account coupling of an out-of-plane motion and an in-plane motion due to thruster disposition angles and thruster firing amounts at multiple times, and combining one or more thruster firings controlling mainly an out-of-the-orbit-plane direction and one or more thruster firings controlling mainly an in-the-orbit-plane direction.
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公开(公告)号：US20210245901A1
公开(公告)日：2021-08-12
申请号：US17263552
申请日：2019-09-13
发明人： Kenji KITAMURA , Takeya SHIMA , Katsuhiko YAMADA
摘要： An attitude control apparatus (20) includes an ideal thrust direction calculator (22), an ideal attitude calculator (24), a target attitude calculator (26), and a torque calculator (28). The ideal thrust direction calculator (22) calculates an ideal thrust direction of a thruster. The target attitude calculator (26) calculates a target attitude that is the attitude of a satellite in which a deviation from an ideal attitude is minimized within a movement limitation of an attitude control actuator (14) while a panel surface faces the sun. The torque calculator (28) calculates a torque for turning the satellite from an actual attitude to the target attitude and transmits a torque instruction to the attitude control actuator (14).
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公开(公告)号：US20190202582A1
公开(公告)日：2019-07-04
申请号：US16329012
申请日：2017-09-05
发明人： Kenji KITAMURA , Takeya SHIMA , Katsuhiko YAMADA
摘要： When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setter 2131 of the ground station 21, a gimbal angle trajectory calculator 2132 calculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle θ0i of a start time and a gimbal angle θci of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle θci of the fixed interval and a gimbal angle θfi of a completion time of the attitude change. The obtained θ0i, θci, θfi and an attitude change period τ are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.
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