-
公开(公告)号：DE69206204D1
公开(公告)日：1996-01-04
申请号：DE69206204
申请日：1992-07-01
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
Abstract: For the method for controlling the roll and yaw attitude of a three-axes stabilised satellite comprising a wheel system generating a permanent kinetic moment substantially parallel to the pitch axis and having a variable component at least approximately parallel to the roll-yaw plane and a continuously acting actuation system, the attitude of the satellite is detected (21) in roll and/or in yaw, control signals derived by a fast servocontrol loop (24) according to a known fast servocontrol law are applied to the wheel system and second control signals derived by a slow servocontrol loop (25) according to a known slow servocontrol law are applied to the continuously-acting actuation system. This continuously-acting actuation system is activated in a fixed direction of the satellite, parallel to this variable component if the latter is fixed in direction, and at least one first complementary control signal TW is furthermore applied to the wheel system, the signal being chosen so as to bring the component of the kinetic moment along this fixed direction to a value suitable for compensating, in the long term, for the drift of the kinetic moment along a second fixed direction, and a second complementary control signal is applied to the continuously-acting actuation system, produced so as to cancel out the effect of the first signal on the attitude along this second fixed direction.
-
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.
-
13.发明专利
公开(公告)号：CA2057731A1
公开(公告)日：1992-06-22
申请号：CA2057731
申请日：1991-12-16
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
Abstract: TITRE de L'INVENTION Procédé de réacquisition d'attitude par reconnaissance d'étoile pour satellite stabilisé 3-axes" TEXTE de L' Pour la réacquisition de l'attitude d'un satellite en tout ou partie stabilisé 3-axes, on teste si un détecteur terrestre détecte la Terre (test 1) et si un détecteur d'étoile détecte une étoile de magnitude au moins approximativement égale à celle d'une étoile de référence donnée (test 2) : * cas a : si les tests 1 et 2 sont positifs, on capture la Terre et ladite étoile, et on teste la cohérence au cours du temps des informations de roulis fournies par les détecteurs de Terre et d'étoile : en cas d'incohérence on passe au cas b ; * cas b : si seul le test 1 est positif, on capture la Terre et on commande en rotation en lacet du satellite jusqu'à vérification du test 2 ; on capture ladite étoile et on procède au test de cohérence prévu au cas a ; * cas c et d : si le test 1 est négatif, on inverse la vitesse en tangage pendant au plus un temps donné ; si le test 1 devient positif, on fait le test 2 : si le test 2 est resté négatif, on passe au cas b, sinon on procède au test de cohérence ; à défaut on passe en mode d'acquisition du Soleil. (Pas de figure)
-
14.发明专利
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
-
公开(公告)号：DE69206204T2
公开(公告)日：1996-10-10
申请号：DE69206204
申请日：1992-07-01
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
Abstract: For the method for controlling the roll and yaw attitude of a three-axes stabilised satellite comprising a wheel system generating a permanent kinetic moment substantially parallel to the pitch axis and having a variable component at least approximately parallel to the roll-yaw plane and a continuously acting actuation system, the attitude of the satellite is detected (21) in roll and/or in yaw, control signals derived by a fast servocontrol loop (24) according to a known fast servocontrol law are applied to the wheel system and second control signals derived by a slow servocontrol loop (25) according to a known slow servocontrol law are applied to the continuously-acting actuation system. This continuously-acting actuation system is activated in a fixed direction of the satellite, parallel to this variable component if the latter is fixed in direction, and at least one first complementary control signal TW is furthermore applied to the wheel system, the signal being chosen so as to bring the component of the kinetic moment along this fixed direction to a value suitable for compensating, in the long term, for the drift of the kinetic moment along a second fixed direction, and a second complementary control signal is applied to the continuously-acting actuation system, produced so as to cancel out the effect of the first signal on the attitude along this second fixed direction.
-
Patent Agency Ranking
公开(公告)号：DE69022203T2
公开(公告)日：1996-05-02
申请号：DE69022203
申请日：1990-11-20
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
-
公开(公告)号：DE69108702T2
公开(公告)日：1995-08-17
申请号：DE69108702
申请日：1991-12-20
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
Abstract: For reacquisition of the attitude of a satellite wholly or partly three-axis stabilised, the method tests whether an Earth detector detects the Earth (test 1) and whether a star detector detects a star of magnitude at least approximately equal to that of a given reference star (test 2): …… * case a : if tests 1 and 2 are positive, the Earth and the said star are captured, and the method tests the coherence over time of the roll information supplied by the Earth and star detectors : in the case of non-coherence it passes to case b; … * case b : if only test 1 is positive, the Earth is captured and the satellite is commanded in rotation in yaw until test 2 is satisfied; the said star is captured and the method proceeds to the coherence test provided for in case a; … * cases c and d : if test 1 is negative, the pitch speed is reversed during a given time at most; if test 1 becomes positive, test 2 is carried out: if test 2 remains negative, the method passes to case b, or else it passes to the coherence test; in default it passes to sun acquisition mode. …… …
-
公开(公告)号：ES2070468T3
公开(公告)日：1995-06-01
申请号：ES91403497
申请日：1991-12-20
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
Abstract: For reacquisition of the attitude of a satellite wholly or partly three-axis stabilised, the method tests whether an Earth detector detects the Earth (test 1) and whether a star detector detects a star of magnitude at least approximately equal to that of a given reference star (test 2): …… * case a : if tests 1 and 2 are positive, the Earth and the said star are captured, and the method tests the coherence over time of the roll information supplied by the Earth and star detectors : in the case of non-coherence it passes to case b; … * case b : if only test 1 is positive, the Earth is captured and the satellite is commanded in rotation in yaw until test 2 is satisfied; the said star is captured and the method proceeds to the coherence test provided for in case a; … * cases c and d : if test 1 is negative, the pitch speed is reversed during a given time at most; if test 1 becomes positive, test 2 is carried out: if test 2 remains negative, the method passes to case b, or else it passes to the coherence test; in default it passes to sun acquisition mode. …… …
-
公开(公告)号：CA2074959A1
公开(公告)日：1992-05-31
申请号：CA2074959
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 comprises at least one surface intended mainly for exposure to solar radiation and extending away from the satellite in a predetermined direction, an on-board 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. Said satellite further comprises a device 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：CA2031097A1
公开(公告)日：1991-05-30
申请号：CA2031097
申请日：1990-11-29
Applicant: AEROSPATIALE
Inventor： FLAMENT PATRICK
-
-
-
-
-
-
-
-
-
Search Results
27
records
(took 0.018 seconds)
