公开(公告)号：FR2699701B1

公开(公告)日：1995-03-24

申请号：FR9215231

申请日：1992-12-17

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  MOLINA-COBOS MIGUEL

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08

Abstract: A method for control of the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a reference frame tied to the satellite, the instantaneous angular velocity vector @ of the satellite is detected, and torques defined by a control law are applied to the satellite, via an actuation unit (16), so as to rotate the satellite about this direction whilst orienting a pointing axis @ tied to the satellite along this direction, characterised in that this direction of the predetermined celestial object in the reference frame tied to the satellite is defined by a first magnitude representative of a first angle ( alpha , alpha ') measured between an aiming axis (Zs, Zs') and the projection of this direction onto a first reference plane containing this aiming axis and by a second magnitude representative of a second angle ( beta ') defined by this aiming axis and the projection of this direction onto a second reference plane containing this aiming axis, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite.

公开(公告)号：CA2111602A1

公开(公告)日：1994-06-18

申请号：CA2111602

申请日：1993-12-16

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  MOLINA-COBOS MIGUEL

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08

Abstract: METHOD FOR CONTROLLING THE ATTITUDE OF A SATELLITE AIMED TOWARDS A CELESTIAL OBJECT AND A SATELLITE SUITABLE FOR IMPLEMENTING IT A method of controlling the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a frame of reference related to the satellite, the instantaneous angular velocity vector (.omega.) of the satellite is detected and, by means of an actuating assembly (16), torques are applied to the satellite which are defined by a control law as as to rotate the satellite about this direction whilst orienting an aiming axis (SR) related to the satellite in this direction, involves defining this direction of the predetermined celestial object in a frame of reference related to the satellite by a first quantity representing a first angle (.alpha.,.alpha.') measured between an axis of sight (Zs, Zs') and the projection of this direction onto a first reference plane containing this axis of sight and by a second quantity representing a second angle (.beta.') defined by this axis of sight and the projection of this direction onto a second reference plane containing this axis sight, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite, whilst a satellite for implementing the method includes a body (11); a sensor (13a, 13b) having the axis of sight (Zs); the actuating assembly (16); an attitude control unit (20) for generating signals for applying the said torques to the satellite; a unit (15) for measuring the rotation velocity; and a processing unit (21) calculating the said second quantity.

公开(公告)号：DE69309015T2

公开(公告)日：1997-07-03

申请号：DE69309015

申请日：1993-12-14

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  MOLINA-COBOS MIGUEL

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08 ,  G05D1/10

Abstract: A method for control of the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a reference frame tied to the satellite, the instantaneous angular velocity vector @ of the satellite is detected, and torques defined by a control law are applied to the satellite, via an actuation unit (16), so as to rotate the satellite about this direction whilst orienting a pointing axis @ tied to the satellite along this direction, characterised in that this direction of the predetermined celestial object in the reference frame tied to the satellite is defined by a first magnitude representative of a first angle ( alpha , alpha ') measured between an aiming axis (Zs, Zs') and the projection of this direction onto a first reference plane containing this aiming axis and by a second magnitude representative of a second angle ( beta ') defined by this aiming axis and the projection of this direction onto a second reference plane containing this aiming axis, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite.

公开(公告)号：ES2099928T3

公开(公告)日：1997-06-01

申请号：ES93403018

申请日：1993-12-14

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  MOLINA-COBOS MIGUEL

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08 ,  G05D1/10

Abstract: A method for control of the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a reference frame tied to the satellite, the instantaneous angular velocity vector @ of the satellite is detected, and torques defined by a control law are applied to the satellite, via an actuation unit (16), so as to rotate the satellite about this direction whilst orienting a pointing axis @ tied to the satellite along this direction, characterised in that this direction of the predetermined celestial object in the reference frame tied to the satellite is defined by a first magnitude representative of a first angle ( alpha , alpha ') measured between an aiming axis (Zs, Zs') and the projection of this direction onto a first reference plane containing this aiming axis and by a second magnitude representative of a second angle ( beta ') defined by this aiming axis and the projection of this direction onto a second reference plane containing this aiming axis, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite.

公开(公告)号：DE69309015D1

公开(公告)日：1997-04-24

申请号：DE69309015

申请日：1993-12-14

Applicant: AEROSPATIALE

Inventor： FLAMENT PATRICK ,  MOLINA-COBOS MIGUEL

IPC: B64G1/24 ,  B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  G05D1/08 ,  G05D1/10

Abstract: A method for control of the attitude of a satellite (11) according to which the direction (S) of a predetermined celestial object is defined in a reference frame tied to the satellite, the instantaneous angular velocity vector @ of the satellite is detected, and torques defined by a control law are applied to the satellite, via an actuation unit (16), so as to rotate the satellite about this direction whilst orienting a pointing axis @ tied to the satellite along this direction, characterised in that this direction of the predetermined celestial object in the reference frame tied to the satellite is defined by a first magnitude representative of a first angle ( alpha , alpha ') measured between an aiming axis (Zs, Zs') and the projection of this direction onto a first reference plane containing this aiming axis and by a second magnitude representative of a second angle ( beta ') defined by this aiming axis and the projection of this direction onto a second reference plane containing this aiming axis, this second angle being calculated from this first angle and from the instantaneous angular velocity vector of the satellite.