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。

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.

公开(公告)号：FR2669887B1

公开(公告)日：1995-06-02

申请号：FR9015050

申请日：1990-11-30

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  PERDU MICHEL ,  PORTIER JEAN

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00 ,  G05D1/08

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.

公开(公告)号：FR2669887A1

公开(公告)日：1992-06-05

申请号：FR9015050

申请日：1990-11-30

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  PERDU MICHEL ,  PORTIER JEAN

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/32 ,  B64G1/34 ,  B64G1/36 ,  B64G1/40 ,  B64G1/44 ,  F03H1/00 ,  G05D1/08

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.

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.

公开(公告)号：DE69004790D1

公开(公告)日：1994-01-05

申请号：DE69004790

申请日：1990-12-12

Applicant: AEROSPATIALE

Inventor： PERDU MICHEL

IPC: B64G1/40 ,  F02K9/44 ,  F02K9/50 ,  G01F23/24

Abstract: A liquid ergol supply system for a satellite comprises an upstream conduit (5) connected to a pressurisation gas source by way of a valve (8), a downstream conduit (10) connected to an ergol distributing manifold (11), and a main volume (2) connected at an upstream orifice (4) to this upstream conduit and at a downstream orifice (9) to this downstream conduit; this volume contains at its outlet a capilliary action ergol retention device (13). On the downstream conduit, from the main volume, this feed device also comprises a gas test device (14) capable of detecting the presence in the downstream conduit of an appreciable quantity of gas, then an auxiliary volume (15) appreciably smaller than the main volume and having a second capilliary action ergol retention device (16) separating the inside of this auxiliary volume and the distributing manifold.

公开(公告)号：FR2620421A1

公开(公告)日：1989-03-17

申请号：FR8712631

申请日：1987-09-11

Applicant: AEROSPATIALE

Inventor： PERDU MICHEL

IPC: G01F9/00 ,  B64G1/40

Abstract: Process for continuously monitoring fuel consumption of a space vehicle (1) equipped with a plurality of propulsion units (2), operation of which is brought about by activation means (3) dependent upon activation orders applied to them, characterised in that, starting from a reference instant, the number N of activation orders applied to each of the propulsion units, and their summed duration S are stored, and the mass of fuel M consumed by each propulsion unit since the reference instant is deduced therefrom through the formula: M = f(N) + g(S> where f and g are independent predetermined functions, and the masses consumed by each propulsion unit are summed. Preferably M is calculated by M = @S + m0N.

公开(公告)号：CA2032589A1

公开(公告)日：1991-06-23

申请号：CA2032589

申请日：1990-12-18

Applicant: AEROSPATIALE

Inventor： PERDU MICHEL

IPC: B64G1/40 ,  F02K9/44 ,  F02K9/50 ,  G01F23/24 ,  B64G1/10

Abstract: A liquid propellant supply device for satellites comprises an inlet pipe connected to a source of pressurizing gas, an outlet pipe connected to a propellant distribution manifold and a main storage tank connected at an inlet orifice to the inlet pipe and at an outlet orifice to the outlet pipe. The main storage tank contains a capillary action propellant retention device between the interior of the main storage tank and the outlet pipe. The device further comprises, on the outlet pipe, starting from the main storage tank, a gas test device adapted to detect the presence in the outlet pipe of a significant quantity of gas followed by an auxiliary storage tank substantially smaller than the main storage tank and including a second capillary action propellant retention device separating the interior of the auxiliary storage tank and the distribution manifold.

公开(公告)号：DE3861508D1

公开(公告)日：1991-02-14

申请号：DE3861508

申请日：1988-09-08

Applicant: AEROSPATIALE

Inventor： PERDU MICHEL

IPC: G01F9/00 ,  B64G1/40

Abstract: Process for continuously monitoring fuel consumption of a space vehicle (1) equipped with a plurality of propulsion units (2), operation of which is brought about by activation means (3) dependent upon activation orders applied to them, characterised in that, starting from a reference instant, the number N of activation orders applied to each of the propulsion units, and their summed duration S are stored, and the mass of fuel M consumed by each propulsion unit since the reference instant is deduced therefrom through the formula: M = f(N) + g(S> where f and g are independent predetermined functions, and the masses consumed by each propulsion unit are summed. Preferably M is calculated by M = @S + m0N.

公开(公告)号：FR2620421B1

公开(公告)日：1990-01-19

申请号：FR8712631

申请日：1987-09-11

Applicant: AEROSPATIALE

Inventor： PERDU MICHEL

IPC: G01F9/00 ,  B64G1/40

Abstract: Process for continuously monitoring fuel consumption of a space vehicle (1) equipped with a plurality of propulsion units (2), operation of which is brought about by activation means (3) dependent upon activation orders applied to them, characterised in that, starting from a reference instant, the number N of activation orders applied to each of the propulsion units, and their summed duration S are stored, and the mass of fuel M consumed by each propulsion unit since the reference instant is deduced therefrom through the formula: M = f(N) + g(S> where f and g are independent predetermined functions, and the masses consumed by each propulsion unit are summed. Preferably M is calculated by M = @S + m0N.