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1. (WO1992009479) METHOD FOR CONTROLLING THE PITCH ATTITUDE OF A SATELLITE BY MEANS OF SOLAR RADIATION PRESSURE, AND A SATELLITE, FOR IMPLEMENTING SAME
Latest bibliographic data on file with the International Bureau

Pub. No.: WO/1992/009479 International Application No.: PCT/FR1991/000938
Publication Date: 11.06.1992 International Filing Date: 26.11.1991
IPC:
B64G 1/24 (2006.01) ,B64G 1/26 (2006.01) ,B64G 1/28 (2006.01) ,B64G 1/32 (2006.01) ,B64G 1/34 (2006.01) ,B64G 1/36 (2006.01) ,B64G 1/40 (2006.01) ,B64G 1/44 (2006.01)
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
24
Guiding or controlling apparatus, e.g. for attitude control
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
24
Guiding or controlling apparatus, e.g. for attitude control
26
using jets
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
24
Guiding or controlling apparatus, e.g. for attitude control
28
using inertia or gyro effect
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
24
Guiding or controlling apparatus, e.g. for attitude control
32
using earth's magnetic field
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
24
Guiding or controlling apparatus, e.g. for attitude control
34
using gravity gradient
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
24
Guiding or controlling apparatus, e.g. for attitude control
36
using sensors, e.g. sun-sensors, horizon sensors
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
40
Arrangements or adaptations of propulsion systems
B PERFORMING OPERATIONS; TRANSPORTING
64
AIRCRAFT; AVIATION; COSMONAUTICS
G
COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
1
Cosmonautic vehicles
22
Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
42
Arrangements or adaptations of power supply systems
44
using radiation, e.g. deployable solar arrays
Applicants:
AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE [FR/FR]; 37, boulevard de Montmorency F-75016 Paris, FR (AllExceptUS)
FLAMENT, Patrick [FR/FR]; FR (UsOnly)
PERDU, Michel [FR/FR]; FR (UsOnly)
PORTIER, Jean [FR/FR]; FR (UsOnly)
BRUNET, Pierre [FR/FR]; FR (UsOnly)
Inventors:
FLAMENT, Patrick; FR
PERDU, Michel; FR
PORTIER, Jean; FR
BRUNET, Pierre; FR
Agent:
RINUY, SANTARELLI; 14, avenue de la Grande-Armée F-75017 Paris, FR
Priority Data:
90/1505030.11.1990FR
Title (EN) METHOD FOR CONTROLLING THE PITCH ATTITUDE OF A SATELLITE BY MEANS OF SOLAR RADIATION PRESSURE, AND A SATELLITE, FOR IMPLEMENTING SAME
(FR) PROCEDE DE CONTROLE D'ATTITUDE EN TANGAGE D'UN SATELLITE GRACE A LA PRESSION DE RADIATION SOLAIRE ET SATELLITE ADAPTE A SA MISE EN ×UVRE
Abstract:
(EN) 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.
(FR) Un satellite comporte au moins une surface (4, 5) destinée principalement à être soumise au rayonnement solaire et s'étendant à partir du satellite selon une direction donnée (Y), un calculateur de bord (8) et, connectés à ce dernier, un système (7) de détection d'attitude, des moyens de contrôle d'orbite adaptés à appliquer au satellite des poussées selon des axes donnés et des moyens de contrôle d'attitude. Ce satellite comporte en outre des moyens (6') de commande en basculement de ladite surface parallèlement à une pluralité de plans contenant ladite direction donnée (donc notamment parallèlement au plan d'une aile de générateur solaire lorsque celle-ci constitue ladite surface). Ces moyens de commande en basculement étant commandés par ledit calculateur de bord. Ce basculement peut servir à générer un couple de tangage ou à amener le centre de gravité sur l'axe des moyens de contrôle d'orbite.
Designated States: CA, JP, SU, US
European Patent Office (AT, BE, CH, DE, DK, ES, FR, GB, GR, IT, LU, NL, SE)
Publication Language: French (FR)
Filing Language: French (FR)
Also published as:
EP0519038RU02114770US5312073US5626315US5850992JP3220142
JPH05504118CA2074959DE000069111437FR2669887