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ES2035600T3 - Procedimiento de basculamiento del momento de inercia de un cuerpo rotatorio libre en el espacio hasta una direccion dada. - Google Patents

Procedimiento de basculamiento del momento de inercia de un cuerpo rotatorio libre en el espacio hasta una direccion dada.

Info

Publication number
ES2035600T3
ES2035600T3 ES198989401176T ES89401176T ES2035600T3 ES 2035600 T3 ES2035600 T3 ES 2035600T3 ES 198989401176 T ES198989401176 T ES 198989401176T ES 89401176 T ES89401176 T ES 89401176T ES 2035600 T3 ES2035600 T3 ES 2035600T3
Authority
ES
Spain
Prior art keywords
inertia
moment
rotating body
space
given direction
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
ES198989401176T
Other languages
English (en)
Inventor
Bernard Blancke
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Application granted granted Critical
Publication of ES2035600T3 publication Critical patent/ES2035600T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • 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
    • B64G1/244—Spacecraft control systems
    • 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
    • B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Navigation (AREA)
  • Control Of Position Or Direction (AREA)

Abstract

PARA LLEVAR AL MOMENTO DE INERCIA HI DE UN CUERPO EN ROTACION INICIALMENTE EN ROTACION APROXIMATIVAMENTE ALREDEDOR DE SU EJE PRINCIPAL DE INERCIA Z HASTA UNA ORIENTACION DADA HF, SE APLICAN TRANSVERSALMENTE AL EJE Z TRES IMPULSOS DE PAR DE FUERZAS EN UN PLANO QUE CONTIENE HI Y HF. EL PRIMER IMPULSO DURANTE UN TIEMPO T1 TAL QUE, AL FINAL DE UN GIRO DEL SATELITE SOBRE SI MISMO, EL EJE Z LLEGA A Z1 EN EL PLANO BIS-SECTOR DE HI Y HF MIENTRAS QUE EL MOMENTO CINETICO LLEGA A H1, EL SEGUNDO IMPULSO EN EL INSTANTE EN QUE EL EJE PRINCIPAL DE INERCIA ESTA EN Z1 DURANTE UN TIEMPO T2 PROPIO PARA LLEVAR AAL MOMENTO CINETICA A UNA POSICION H2 SIMETRICA DE H1 RESPECTO A ESTE PLANO BIS-SECTOR, Y EL TERCER IMPULSO EN EL INSTANTE EN QUE EL EJE PRINCIPAL DE INERCIA ES PARALELO A HF DURANTE UN TIEMPO IGUAL A T1.
ES198989401176T 1988-04-26 1989-04-25 Procedimiento de basculamiento del momento de inercia de un cuerpo rotatorio libre en el espacio hasta una direccion dada. Expired - Lifetime ES2035600T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR8805517A FR2630398B1 (fr) 1988-04-26 1988-04-26 Procede de basculement du moment d'inertie d'un corps rotatif libre dans l'espace jusqu'en une direction donnee

Publications (1)

Publication Number Publication Date
ES2035600T3 true ES2035600T3 (es) 1993-04-16

Family

ID=9365681

Family Applications (1)

Application Number Title Priority Date Filing Date
ES198989401176T Expired - Lifetime ES2035600T3 (es) 1988-04-26 1989-04-25 Procedimiento de basculamiento del momento de inercia de un cuerpo rotatorio libre en el espacio hasta una direccion dada.

Country Status (7)

Country Link
US (1) US4927101A (es)
EP (1) EP0341130B1 (es)
JP (1) JPH01312000A (es)
CA (1) CA1327193C (es)
DE (1) DE68903244T2 (es)
ES (1) ES2035600T3 (es)
FR (1) FR2630398B1 (es)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5067673A (en) * 1990-02-07 1991-11-26 Hughes Aircraft Company Essentially passive method for inverting the orientation of a dual spin spacecraft
US5080307A (en) * 1990-05-14 1992-01-14 Hughes Aircraft Company Spacecraft earth-pointing attitude acquisition method
US5222023A (en) * 1991-04-02 1993-06-22 Space Systems/Loral, Inc. Compensated transition for spacecraft attitude control
US5308025A (en) * 1992-07-30 1994-05-03 Hughes Aircraft Company Spacecraft spin axis capture system and method
DE19510371C1 (de) * 1995-03-22 1996-10-31 Daimler Benz Aerospace Ag Verfahren zur Sonnensuche für einen dreiachsenstabilisierten Satelliten und dreiachsenstabilisierter Satellit
FR2742122B1 (fr) * 1995-12-06 1998-02-06 Matra Marconi Space France Procede et dispositif de commande d'attitude de satellite a generateurs solaires
US5984237A (en) * 1997-02-13 1999-11-16 Lockheed Martin Corp. Delta-V targeting system for three-axis controlled spacecraft
FR2815730B1 (fr) * 2000-10-19 2003-10-24 Astrium Sas Procede de commande d'attitude et de stabilisation d'un satellite en orbite basse, par couplage avec le champ magnetique terrestre
GB0125728D0 (en) * 2001-10-26 2001-12-19 Astrium Ltd Autonomous active manoeuvring method and system for spinning spacecraft
DE60117744T2 (de) * 2001-11-20 2006-11-16 Eads Astrium S.A.S. Steuerungsverfahren zur Lageregelung und Stabilisierung eines Satelliten in niedriger Umlaufbahn, durch Kopplung mit dem Erdmagnetfeld
US6745984B2 (en) 2002-04-23 2004-06-08 Astrium Sas Method of controlling the attitude and stabilization of a satellite in low orbit

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1372563A (fr) * 1963-07-31 1964-09-18 Nord Aviation Procédé pour stabiliser un solide en rotation, et dispositif correspondant
FR1468913A (fr) * 1965-11-13 1967-02-10 Nord Aviation Procédé et dispositif pour stabiliser, selon une direction fixe, un véhicule en rotation lente
US3558078A (en) * 1967-08-21 1971-01-26 Whittaker Corp Space vehicle attitude control
US3944172A (en) * 1972-04-14 1976-03-16 Erno Raumfahrttechnik Gmbh Attitude control for space vehicle
GB1514745A (en) * 1975-09-11 1978-06-21 Rca Corp Elimination of residual spacecraft nutation due to propulsive torques
US4193570A (en) * 1978-04-19 1980-03-18 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active nutation controller
FR2447320A1 (fr) * 1979-01-23 1980-08-22 Matra Perfectionnements aux procedes et dispositifs d'amortissement actif de nutation pour vehicule spatial
US4504032A (en) * 1982-03-10 1985-03-12 Rca Corporation Control of nutation in a spacecraft
US4758957A (en) * 1985-05-17 1988-07-19 General Electric Company Spacecraft stabilization system and method
US4848706A (en) * 1988-02-29 1989-07-18 Ford Aerospace Corporation Spacecraft attitude control using coupled thrusters

Also Published As

Publication number Publication date
US4927101A (en) 1990-05-22
FR2630398A1 (fr) 1989-10-27
EP0341130B1 (fr) 1992-10-21
DE68903244T2 (de) 1993-05-27
JPH01312000A (ja) 1989-12-15
CA1327193C (en) 1994-02-22
DE68903244D1 (de) 1992-11-26
EP0341130A1 (fr) 1989-11-08
FR2630398B1 (fr) 1990-08-24

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