ES2057459T3 - Sistema de estabilizacion mecanica en contra-rotacion de rotores separados. - Google Patents

Sistema de estabilizacion mecanica en contra-rotacion de rotores separados.

Info

Publication number
ES2057459T3
ES2057459T3 ES90400248T ES90400248T ES2057459T3 ES 2057459 T3 ES2057459 T3 ES 2057459T3 ES 90400248 T ES90400248 T ES 90400248T ES 90400248 T ES90400248 T ES 90400248T ES 2057459 T3 ES2057459 T3 ES 2057459T3
Authority
ES
Spain
Prior art keywords
rotor
useful
support
antagonist
stabilization system
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
ES90400248T
Other languages
English (en)
Inventor
Gerard Atlas
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.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP SA
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 Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Application granted granted Critical
Publication of ES2057459T3 publication Critical patent/ES2057459T3/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
    • B64G1/283—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using reaction wheels
    • 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
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect

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)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Lubricants (AREA)

Abstract

EL SISTEMA DE ESTABILIZACION DE UN SOPORTE (6) A ESTABILIZAR CONSTA DE UN ROTOR UTIL (10) MONTADO EN SOPORTE (6) MEDIANTE UNOS COJINETES (12,13) Y SOLIDARIO DE UN ORGANO UTIL (1), AL MENOS UNO DE CUYOS PARAMETROS ASOCIADO A LA ROTACION DEL ROTOR UTIL (10) ES VARIABLE EN FUNCION DEL TIEMPO, UN PRIMER MOTOR ELECTRICO RETROALIMENTADO (3) INTERPUESTO ENTRE EL SOPORTE (6) Y EL ROTOR UTIL PARA PROPORCIONAR EL ARRASTRE EN ROTACION DEL ROTOR UTIL (10) EN UN PRIMER SENTIDO, UN ROTOR ANTAGONISTA (21) QUE ESTA MONTADO SOBRE EL SOPORTE MEDIANTE UNOS COJINETES (22,23) INDEPENDIENTEMENTE DEL ROTOR UTIL (10) AUNQUE COAXIAL AL MISMO, Y QUE SOPORTA UN ORGANO DE INERCIA ANTAGONISTA (20), Y UN SEGUNDO MOTOR ELECTRICO RETROALIMENTADO (4) INTERPUESTO ENTRE EL ROTOR ANTAGONISTA (21) Y EL SOPORTE (6) PARA ARRASTRAR AL ROTOR ANTAGONISTA (21) EN SENTIDO INVERSO AL ROTOR UTIL (10) Y A UNA VELOCIDAD SUPERIOR DE FORMA QUE SE ANULEN LAS PERTURBACIONES APORTADAS POR EL ROTOR UTIL (10) AL SOPORTE (6), SIENDO LA MASADEL CONJUNTO QUE GIRA ASOCIADA AL ROTOR ANTAGONISTA (21) INFERIOR A LA MASA DE CONJUNTO QUE GIRA ASOCIADO AL ROTOR UTIL (10).
ES90400248T 1989-01-31 1990-01-30 Sistema de estabilizacion mecanica en contra-rotacion de rotores separados. Expired - Lifetime ES2057459T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR8901217A FR2642552B1 (es) 1989-01-31 1989-01-31

Publications (1)

Publication Number Publication Date
ES2057459T3 true ES2057459T3 (es) 1994-10-16

Family

ID=9378316

Family Applications (1)

Application Number Title Priority Date Filing Date
ES90400248T Expired - Lifetime ES2057459T3 (es) 1989-01-31 1990-01-30 Sistema de estabilizacion mecanica en contra-rotacion de rotores separados.

Country Status (6)

Country Link
US (1) US5042753A (es)
EP (1) EP0381573B1 (es)
CA (1) CA2008305A1 (es)
DE (1) DE69009209T2 (es)
ES (1) ES2057459T3 (es)
FR (1) FR2642552B1 (es)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5692707A (en) * 1995-05-15 1997-12-02 Hughes Aircraft Company Universal spacecraft attitude steering control system
US5751078A (en) * 1996-10-03 1998-05-12 Lockheed Martin Corp. Missiles & Space Reactionless, momentum compensated payload positioner
US6107770A (en) * 1998-01-27 2000-08-22 Lockheed Martin Corporation Control system for counter-oscillating masses
GB0130021D0 (en) * 2001-12-15 2002-02-06 Renishaw Plc Reaction balanced rotary drive mechanism
US9090361B2 (en) 2011-11-05 2015-07-28 Spacedesign Corporation Space vehicle comprising a multiple passenger bay module
US10155598B2 (en) 2011-11-05 2018-12-18 Spacedesign Corporation Commercially feasible method of flying repeated orbital missions using a space vehicle

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3341151A (en) * 1965-07-23 1967-09-12 Kampinsky Abe Apparatus providing a directive field pattern and attitude sensing of a spin stabilized satellite
US4219107A (en) * 1977-12-13 1980-08-26 Nasa Speed control device for a heavy duty shaft
DE2829432A1 (de) * 1978-07-05 1980-01-24 Peter Dr Kuemmel Kreiseldrallantrieb
US4230294A (en) * 1979-07-23 1980-10-28 Rca Corporation Closed loop roll control for momentum biased satellites
WO1986000863A1 (en) * 1984-07-20 1986-02-13 Hughes Aircraft Company Spin-stabilized satellite with nutation control subsystem
US4723735A (en) * 1984-12-28 1988-02-09 The Charles Stark Draper Laboratory, Inc. Energy storage attitude control and reference system
US4752884A (en) * 1985-07-18 1988-06-21 Hughes Aircraft Company Precision platform pointing controller for a dual-spin spacecraft
US4824052A (en) * 1987-06-18 1989-04-25 Hughes Aircraft Company Nutation sensor and nutation control system for a dual-spin stabilized satellite

Also Published As

Publication number Publication date
EP0381573A1 (fr) 1990-08-08
FR2642552A1 (es) 1990-08-03
EP0381573B1 (fr) 1994-06-01
DE69009209D1 (de) 1994-07-07
CA2008305A1 (en) 1990-07-31
FR2642552B1 (es) 1991-05-24
DE69009209T2 (de) 1994-09-29
US5042753A (en) 1991-08-27

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