WO2004071869B1 - Device for controlling the attitude of a satellite by means of gyroscopic actuators - Google Patents

Device for controlling the attitude of a satellite by means of gyroscopic actuators

Info

Publication number
WO2004071869B1
WO2004071869B1 PCT/FR2004/000264 FR2004000264W WO2004071869B1 WO 2004071869 B1 WO2004071869 B1 WO 2004071869B1 FR 2004000264 W FR2004000264 W FR 2004000264W WO 2004071869 B1 WO2004071869 B1 WO 2004071869B1
Authority
WO
WIPO (PCT)
Prior art keywords
attitude
platform
motor
actuator
satellite
Prior art date
Application number
PCT/FR2004/000264
Other languages
French (fr)
Other versions
WO2004071869A1 (en
Inventor
Celine Beugnon
Ange Defendini
Mehdi Ghezal
Julien Morand
Original Assignee
Eads Astrium Sas
Celine Beugnon
Ange Defendini
Mehdi Ghezal
Julien Morand
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Eads Astrium Sas, Celine Beugnon, Ange Defendini, Mehdi Ghezal, Julien Morand filed Critical Eads Astrium Sas
Priority to EP04708380A priority Critical patent/EP1590243A1/en
Publication of WO2004071869A1 publication Critical patent/WO2004071869A1/en
Publication of WO2004071869B1 publication Critical patent/WO2004071869B1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • B64G1/286—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using control momentum gyroscopes (CMGs)

Abstract

The device for controlling the attitude of a satellite by means of kinetic moment exchange comprises a cluster consisting of at least one gyroscopic actuator (10) having a gyro wheel (12) which turns about an axis (16), borne by a cardan drive (14), which can be oriented on the platform of the satellite by means of a stepper motor(22), and a system for controlling the attitude of the platform and the orbit inside an absolute reference mark, provided with sensors for sensing the orientation of the platform. The control system comprises a calculator (26) which is used to create a digital setpoint value for the orientation of the cardan drive (14) based on the differential between an attitude setpoint value of the platform and the current attitude. The actuator or the calculator (26) is provided with means for converting the digital oriental setpoint value to analog values of currents applied to the different phases of the stepper motor (22), whereby the resolution is such that the motor can be brought to and maintained in intermediate orientations between those corresponding to the mutual alignment of the poles of the stator (23) and the rotor (24).

Claims

REVENDICATIONS MODIFIEES reçues par le Bureau international le 04 août 2004 (04.08.2004) revendications originales 1 à 4 remplacées par revendications amendées 1 à 4 (2 pages ).REVENDI CAT I ONS AMENDED CLAIMS received by the International Bureau on 04 August 2004 (04.08.2004) original claims 1 to 4 replaced by claims amended 1 to 4 (2 pages) .REVENDI CAT I ONS
1. Dispositif de pilotage d'attitude de satellite par échange de moments cinétiques, comprenant une grappe (40) de plusieurs organes de génération de moment cinétique parmi lesquels au moins un actionneur gyroscopique (10) ayant une toupie (12) tournant sur un axe (16) porté par un cardan (14) orientable sur la plate-forme du satellite par un moteur pas à pas (22) autour d'au moins un axe (18) orthogonal à l'axe (16) de rotation de la toupie (12) et ayant un système de commande d' attitude de la plate-forme et d' orbite dans un repère absolu, muni de capteurs (48) d'orientation de la plate-forme, caractérisé en ce que : le système de commande d' attitude et d' orbite de la plate-forme comporte un calculateur (26) prévu pour élaborer une consigne numérique (58) d'orientation du cardan (14) dudit actionneur gyroscopique (10) à partir de l'écart (44) entre une consigne d'attitude (28) de la plate-forme et de l'attitude courante (30) et sans boucle locale de contrôle de la position dudit actionneur gyroscopique (10) avec codeur angulaire rebouclé sur un moteur pas à pas (22) ou un moteur couple du cardan (14) correspondant, et le dit actionneur (10) ou le calculateur (26) est muni deApparatus for satellite attitude control by kinetic moment exchange, comprising a cluster (40) of a plurality of kinetic moment generating members among which at least one gyroscopic actuator (10) having a rotor (12) rotating on an axis (16) carried by a gimbal (14) orientable on the platform of the satellite by a stepper motor (22) around at least one axis (18) orthogonal to the axis (16) of rotation of the spindle (12) and having an attitude control system of the platform and orbit in an absolute reference, provided with sensors (48) for orienting the platform, characterized in that: the control system platform attitude and orbit system includes a computer (26) for developing a digital gimbal orientation setpoint (58) (14) of said gyro actuator (10) from the gap (44). between an attitude command (28) of the platform and the current attitude (30) and without a local control loop of the position of said gyroscopic actuator (10) with loopback encoder on a stepper motor (22) or a corresponding gimbal torque motor (14), and said actuator (10) or calculator (26) is provided with
• moyens (60) de conversion de la consigne numérique (58) d'orientation en valeurs analogiques de courants (64) appliqués aux différentes phases du moteur pas à pas (22), avec une résolution telle que le moteur (22) 11 • means (60) for converting the digital set (58) of orientation into analog current values (64) applied to the different motor phases of the step (22), with a resolution such that the motor (22) 11
puisse être amené et maintenu dans des orientations intermédiaires entre celles qui correspondent à l'alignement mutuel des pôles du stator (23) et du rotor (24) . can be brought and maintained in intermediate orientations between those which correspond to the mutual alignment of the poles of the stator (23) and the rotor (24).
2. Dispositif suivant la revendication 1, caractérisé en ce que, dans le cas d'un moteur (22) biphasé, les courants de maintien Iχ et I2 fournis aux deux phases sont Ii = I0. cos (p. θ) I2 = Io.sin(p.θ) où I0 est un courant de consigne moteur, p le nombre de pôles du moteur (22) et θ la consigne de position issue du calculateur (26, 41) du système de commande d'attitude et d'orbite. 2. Device according to claim 1, characterized in that, in the case of a two-phase motor (22), the holding currents Iχ and I 2 supplied to the two phases are Ii = I 0 . cos (p θ) I 2 = I o .sin (p.θ) where I 0 is a motor setpoint current, p the number of motor poles (22) and θ the position setpoint from the computer (26, 41) of the attitude and orbit control system.
3. Dispositif suivant la revendication 2, caractérisé en ce que les courants Iχ et I2 sont générés par des amplificateurs linéaires (60) à gain commandé par des valeurs analogiques fournies par conversion de valeurs fournies par au moins une table en mémoire morte (62) de cosinus et sinus.3. Device according to claim 2, characterized in that the currents Iχ and I 2 are generated by linear gain amplifiers (60) controlled by analog values provided by conversion of values provided by at least one table in read-only memory (62). ) of cosine and sinus.
4. Dispositif suivant la revendication 1, 2 ou 3, caractérisé en ce que la grappe comporte uniquement des actionneurs gyroscopiques (10) . 4. Device according to claim 1, 2 or 3, characterized in that the cluster comprises only gyroscopic actuators (10).
PCT/FR2004/000264 2003-02-07 2004-02-05 Device for controlling the attitude of a satellite by means of gyroscopic actuators WO2004071869A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04708380A EP1590243A1 (en) 2003-02-07 2004-02-05 Device for controlling the attitude of a satellite by means of gyroscopic actuators

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0301472A FR2850948B1 (en) 2003-02-07 2003-02-07 DEVICE FOR CONTROLLING THE ATTITUDE OF A SATELLITE BY GYROSCOPIC ACTUATORS
FR03/01472 2003-02-07

Publications (2)

Publication Number Publication Date
WO2004071869A1 WO2004071869A1 (en) 2004-08-26
WO2004071869B1 true WO2004071869B1 (en) 2005-01-06

Family

ID=32731871

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2004/000264 WO2004071869A1 (en) 2003-02-07 2004-02-05 Device for controlling the attitude of a satellite by means of gyroscopic actuators

Country Status (3)

Country Link
EP (1) EP1590243A1 (en)
FR (1) FR2850948B1 (en)
WO (1) WO2004071869A1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7364120B2 (en) 2004-08-26 2008-04-29 Honeywell International, Inc. Quantized control-moment gyroscope array
CN100441483C (en) * 2006-12-14 2008-12-10 北京航空航天大学 Integrated magnetically suspended control moment gyroscope control platform
RU2013112756A (en) * 2013-03-22 2014-09-27 Вячеслав Павлович Гажур Gyroscopic reference system
CN105511481B (en) * 2014-11-26 2017-04-26 航天恒星科技有限公司 Satellite borne orbit determination optimization method
IT201900023280A1 (en) * 2019-12-06 2021-06-06 Eni Spa ENERGY GENERATOR

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2530440A2 (en) 1982-07-22 1984-01-27 Duret Fils Ets M Upholstery element resisting laceration for seats or the like and its manufacturing method.
FR2786283B1 (en) 1998-11-19 2001-01-26 Matra Marconi Space France METHOD AND DEVICE FOR CONTROLLING THE ATTITUDE OF A SATELLITE
FR2826470B1 (en) 2001-06-26 2003-09-19 Astrium Sas METHOD AND DEVICE FOR STEERING THE ATTITUDE AND GUIDANCE OF A SATELLITE BY A GYRODYNES CLUSTER

Also Published As

Publication number Publication date
WO2004071869A1 (en) 2004-08-26
EP1590243A1 (en) 2005-11-02
FR2850948A1 (en) 2004-08-13
FR2850948B1 (en) 2006-01-06

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