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公开(公告)号：US20170129627A1
公开(公告)日：2017-05-11
申请号：US15318670
申请日：2015-06-19
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： VALERIO MORO , JEAN FISCHER
Abstract: A method for controlling the orbit of a satellite in earth orbit. The orbit of the satellite is controlled by commanding, according to a maneuver plan, a propulsion system having at least one thruster and a transporter to move the propulsion system. The maneuver plan includes at least two orbit-control maneuvers. The thrust powers of the propulsion system during the two orbit control maneuvers have respective thrust directions that are not parallel in an inertial frame of reference. Each thrust power is determined to simultaneously control the inclination and the position of the orbit of the satellite as well as to form a momentum that is suitable for unloading a device for storing angular momentum of the satellite in a plane orthogonal to the direction of thrust of the thrust power.
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公开(公告)号：US20180072435A1
公开(公告)日：2018-03-15
申请号：US15563271
申请日：2016-03-31
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： NICOLAS CUILLERON , PHILIPPE LAURENS , VALERIO MORO
CPC classification number: B64G1/283 , B64G1/244 , B64G1/26 , B64G1/286 , B64G2001/245
Abstract: A method of controlling the attitude of a spacecraft in spinning around itself with a non-zero total angular momentum HTOT. The spacecraft includes a set of inertia flywheels configured to form an internal angular momentum HACT. The axis of the total angular momentum HTOT is aligned with a principal axis of inertia of the spacecraft, in the course of which the inertia flywheels are controlled to form an internal angular momentum HACT. The following expression, in which J is the inertia matrix of the spacecraft: Hact×J−1(HtotJ−1Htot) is negative if the principal axis of inertia targeted is the axis of maximum inertia of the spacecraft and is positive if the principal axis inertia targeted is the axis of minimum inertia of the spacecraft.
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