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    METHOD FOR CONTROLLING THE PITCH ATTITUDE OF A SATELLITE BY MEANS OF SOLAR RADIATION PRESSURE, AND A SATELLITE, FOR IMPLEMENTING SAME
    1.
    发明申请
    METHOD FOR CONTROLLING THE PITCH ATTITUDE OF A SATELLITE BY MEANS OF SOLAR RADIATION PRESSURE, AND A SATELLITE, FOR IMPLEMENTING SAME 审中-公开
    通过太阳辐射压力控制卫星的俯仰姿态的方法和用于实现相同的卫星的方法

    公开(公告)号：WO9209479A3

    公开(公告)日：1992-11-26

    申请号：PCT/FR9100938

    申请日：1991-11-26

    Applicant: AEROSPATIALE

    Inventor： FLAMENT PATRICK ,  PERDU MICHEL ,  PORTIER JEAN ,  BRUNET PIERRE

    IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00

    CPC classification number: B64G1/407 ,  B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/283 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/44 ,  B64G2001/245 ,  Y10S136/292

    Abstract: A satellite comprises at least one surface (4, 5) intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an on-board computer (8) having connected thereto an attitude sensing system (7), an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. Said satellite further comprises a device (6') for controlling the tilt of said surface in parallel with a plurality of planes containing said predetermined direction (and therefore particularly in parallel with the plane of a solar panel forming said surface). Said tilt control device is controlled by said on-board computer. Said tilting can generate a moment of pitch or relocate the centre of gravity onto the axis of the orbit control system.

    Abstract translation: 卫星包括至少一个主要用于暴露于太阳辐射并在预定方向上远离卫星延伸的表面（4,5），其上连接有姿态感测系统（7）的车载计算机（8） ），沿预定轴向卫星施加推力的轨道控制系统，以及姿态控制系统。 所述卫星进一步包括用于控制所述表面与包含所述预定方向（因此特别是与形成所述表面的太阳能电池板的平面平行）的多个平面平行的装置（6'）。 所述倾斜控制装置由所述车载计算机控制。 所述倾斜可以产生俯仰的力矩或将重心重新定位到轨道控制系统的轴线上。

    3.
    发明专利
    未知

    公开(公告)号：DE69111437D1

    公开(公告)日：1995-08-24

    申请号：DE69111437

    申请日：1991-11-26

    Applicant: AEROSPATIALE

    Inventor： FLAMENT PATRICK ,  PERDU MICHEL ,  PORTIER JEAN ,  BRUNET PIERRE

    IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00

    Abstract: A satellite embodying at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an onboard computer having connected thereto an attitude sensing system, an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. The satellite further embodies a device for controlling the tilt of the surface in parallel with a plurality of planes containing the predetermined direction; and, therefore, particularly in parallel with the plane of a solar panel forming the surface. The tilt control device is controlled by the onboard computer. The tilting can generate a moment of pitch or relocate the center of gravity onto the axis of the orbit control system.

    SATELLITE WITH THREE-AXIS ATTITUDE STABILIZATION AND METHOD OF CONTROL OF THIS SATELLITE
    4.
    发明专利
    SATELLITE WITH THREE-AXIS ATTITUDE STABILIZATION AND METHOD OF CONTROL OF THIS SATELLITE 未知

    公开(公告)号：RU2114770C1

    公开(公告)日：1998-07-10

    申请号：SU5052468

    申请日：1991-11-26

    Applicant: AEROSPATIALE

    Inventor： FLAMENT PATRICK ,  PERDU MICHEL ,  PORTIER JEAN ,  BRUNET PIERRE

    IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00

    Abstract: FIELD: construction and control of satellites stabilized in geostationary orbit in three axes. SUBSTANCE: satellite has at least one surface intended for perception of solar radiation; this surface extends from satellite in preset direction (Y); satellite is also provided with on-board computer and position detection system connected with this computer; satellite includes also orbit monitoring devices for applying thrust to satellite in way of preset axes and position control devices. Besides that, satellite includes units for control of swinging of above-mentioned surface in parallel with set of places having above-mentioned preset direction (consequently, in parallel with plane of one of winds of solar generator when it forms above-mentioned surface). Swinging control devices are operated with the aid of the above-mentioned on-board computer. Swinging may be used for creating pitching moment or for bringing the center of gravity to axis of action of orbit monitoring devices. EFFECT: reduction of mass; enhanced reliability of satellite systems; reduction of disturbances and enhanced efficiency of control. 23 cl, 16 dwgi

    6.
    发明专利
    未知

    公开(公告)号：DE69111437T2

    公开(公告)日：1996-01-04

    申请号：DE69111437

    申请日：1991-11-26

    Applicant: AEROSPATIALE

    Inventor： FLAMENT PATRICK ,  PERDU MICHEL ,  PORTIER JEAN ,  BRUNET PIERRE

    IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00

    Abstract: A satellite embodying at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction (Y), an onboard computer having connected thereto an attitude sensing system, an orbit control system for imparting thrust to the satellite along predetermined axes, and an attitude control system. The satellite further embodies a device for controlling the tilt of the surface in parallel with a plurality of planes containing the predetermined direction; and, therefore, particularly in parallel with the plane of a solar panel forming the surface. The tilt control device is controlled by the onboard computer. The tilting can generate a moment of pitch or relocate the center of gravity onto the axis of the orbit control system.

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