ES8104102A1 - Perfeccionamientos en sistemas electricos de control de un elevador para helicopteros - Google Patents

Perfeccionamientos en sistemas electricos de control de un elevador para helicopteros

Info

Publication number
ES8104102A1
ES8104102A1 ES491516A ES491516A ES8104102A1 ES 8104102 A1 ES8104102 A1 ES 8104102A1 ES 491516 A ES491516 A ES 491516A ES 491516 A ES491516 A ES 491516A ES 8104102 A1 ES8104102 A1 ES 8104102A1
Authority
ES
Spain
Prior art keywords
air speed
actuator
elevator
transducer
longitudinal cyclic
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
Application number
ES491516A
Other languages
English (en)
Other versions
ES491516A0 (es
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.)
Textron Inc
Original Assignee
Textron Inc
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 Textron Inc filed Critical Textron Inc
Publication of ES491516A0 publication Critical patent/ES491516A0/es
Publication of ES8104102A1 publication Critical patent/ES8104102A1/es
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/50—Transmitting means with power amplification using electrical energy
    • B64C13/503—Fly-by-Wire
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/16—Initiating means actuated automatically, e.g. responsive to gust detectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/50—Transmitting means with power amplification using electrical energy
    • B64C13/505—Transmitting means with power amplification using electrical energy having duplication or stand-by provisions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24—Transmitting means
    • B64C13/38—Transmitting means with power amplification
    • B64C13/50—Transmitting means with power amplification using electrical energy
    • B64C13/506—Transmitting means with power amplification using electrical energy overriding of personal controls; with automatic return to inoperative position
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes

Landscapes

  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Vehicle Body Suspensions (AREA)
  • Control Of Multiple Motors (AREA)
  • Cage And Drive Apparatuses For Elevators (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Control Of Electric Motors In General (AREA)
  • Elevator Control (AREA)
  • Control Of Ac Motors In General (AREA)

Abstract

SISTEMA ELECTRICO DE CONTROL DE UN ELEVADOR PARA HELICOPTEROS. EL ACCIONADOR (20) CON SUS MOTORES (36A, 36B) CONTROLA POR UN CIRCUITO CON SENSORES DE ORDEN CICLICA (40), DE CABECEO COLECTIVO (41) Y DE VELOCIDAD DEL VIENTO (42), SIENDO COMBINADAS ESTAS SEÑALES PARA OBTENER UNA SEÑAL DE SALIDA, A LA QUE SE REALIMENTA, EN UN SUMADOR (47), SEÑALES CORRESPONDIENTES A LA VELOCIDAD DE GIRO (61) Y ANGULO DE INCIDENCIA (39A) DEL ACCIONADOR (20). EL SISTEMA DISPONE DE CIRCUITOS REDUNDANTES PARA EVITAR AVERIAS, Y DE DISPOSITIVOS DE ACTUACION DE SEÑALES PARA VALORES MINIMOS. S
ES491516A 1979-05-17 1980-05-14 Perfeccionamientos en sistemas electricos de control de un elevador para helicopteros Expired ES8104102A1 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/039,943 US4304375A (en) 1979-05-17 1979-05-17 Electrically controlled elevator

Publications (2)

Publication Number Publication Date
ES491516A0 ES491516A0 (es) 1981-03-16
ES8104102A1 true ES8104102A1 (es) 1981-03-16

Family

ID=21908206

Family Applications (1)

Application Number Title Priority Date Filing Date
ES491516A Expired ES8104102A1 (es) 1979-05-17 1980-05-14 Perfeccionamientos en sistemas electricos de control de un elevador para helicopteros

Country Status (12)

Country Link
US (1) US4304375A (es)
JP (1) JPS568799A (es)
AU (1) AU536643B2 (es)
BR (1) BR8003067A (es)
CA (1) CA1132683A (es)
DE (1) DE3018200A1 (es)
ES (1) ES8104102A1 (es)
FR (1) FR2456663A1 (es)
GB (1) GB2050980B (es)
IL (1) IL60081A (es)
IT (1) IT1147048B (es)
MX (1) MX6588E (es)

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4371937A (en) * 1981-03-30 1983-02-01 United Technologies Corporation Retaining airspeed hold engagement in low speed maneuver
US4371938A (en) * 1981-03-30 1983-02-01 United Technologies Corporation Automatic airspeed engage/disengage
US4371936A (en) * 1981-03-30 1983-02-01 United Technologies Corporation Attitude trimmed airspeed/attitude controls
US4385356A (en) * 1981-03-30 1983-05-24 United Technologies Corporation Non-saturating airspeed/attitude controls
US4594537A (en) * 1983-12-27 1986-06-10 United Technologies Corporation Redundant control system for X-wing valve actuators
DE3416969A1 (de) * 1984-05-08 1985-11-14 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Verfahren und vorrichtung zur steuerkraftstabilisierung bei einem drehfluegelflugzeug
DE3431597A1 (de) * 1984-08-28 1986-03-13 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Vorrichtung zur verbesserung der laengssteuerstabilitaet von luftfahrzeugen
FR2604001B1 (fr) * 1986-09-15 1988-12-09 Aerospatiale Systeme de commande de vol electrique avec protection en incidence pour aeronef
US4826110A (en) * 1987-06-22 1989-05-02 The Boeing Company Oscillatory failure monitor
US4858491A (en) * 1988-01-21 1989-08-22 Plessey Incorporated Fail-free actuator assembly
JPH0226301A (ja) * 1988-07-12 1990-01-29 Teijin Seiki Co Ltd サーボ制御装置
US5058824A (en) * 1989-12-21 1991-10-22 United Technologies Corporation Servo control system for a co-axial rotary winged aircraft
FR2661149B1 (fr) * 1990-04-24 1992-08-14 Aerospatiale Systeme pour le pilotage d'un avion en tangage.
JP2902071B2 (ja) * 1990-08-02 1999-06-07 三菱重工業株式会社 ヘリコプタロータ防振装置
CA2059802C (en) * 1991-02-01 1997-12-02 Dennis W. Waggamon Wiring error detector for door operator
FR2771706B1 (fr) * 1997-12-01 2000-01-28 Eurocopter France Dispositif de commande d'une surface aerodynamique d'equilibrage en tangage d'un helicoptere
US6097165A (en) * 1998-08-03 2000-08-01 Ace-Tronics Method and apparatus for handling brake failure in variable frequency drive motors
FR2830630B1 (fr) * 2001-10-05 2004-07-30 Eurocopter France Dispositif de pilotage automatique d'un helicoptere et systeme de pilotage automatique comportant un tel dispositif
FR2832685A1 (fr) * 2001-11-23 2003-05-30 Conception & Dev Michelin Sa Direction electrique pour vehicule, a redondance triple
US6885917B2 (en) * 2002-11-07 2005-04-26 The Boeing Company Enhanced flight control systems and methods for a jet powered tri-mode aircraft
JP2005054843A (ja) * 2003-08-01 2005-03-03 Fanuc Ltd ブレーキ装置
US7021587B1 (en) 2004-01-07 2006-04-04 Trutrak Flight Systems, Inc Dual channel fail-safe system and method for adjusting aircraft trim
US7762501B2 (en) 2005-08-31 2010-07-27 Bell Helicopter Textron Inc. Method and apparatus for improving main rotor yoke fatigue life
DE102007012425A1 (de) * 2007-03-15 2008-09-18 Airbus Deutschland Gmbh Verfahren und Einrichtung zur Höhenflossentrimmung bei einem Flugzeug
FR2916420B1 (fr) * 2007-05-22 2009-08-28 Eurocopter France Helicoptere hybride rapide a grande distance franchissable avec controle de l'assiette longitudinale.
FR2959205B1 (fr) * 2010-04-27 2012-04-13 Eurocopter France Procede de commande et de regulation de l'angle de braquage d'un empennage d'helicoptere hybride
FR3005300B1 (fr) * 2013-05-03 2016-10-21 Eurocopter France Systeme et procede de commande d'un moyen de stabilisation en tangage d'un aeronef
NL2011184C2 (en) * 2013-07-17 2015-01-21 Univ Delft Tech Helicopter.
EP3201077B1 (en) 2014-10-01 2020-05-20 Sikorsky Aircraft Corporation Dual rotor, rotary wing aircraft
WO2016053408A1 (en) 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Acoustic signature variation of aircraft utilizing a clutch
EP3224135B1 (en) * 2014-11-25 2020-04-01 Sikorsky Aircraft Corporation Flight control system for a rotary wing aircraft
DE102015203411A1 (de) * 2015-02-26 2016-09-01 Zf Friedrichshafen Ag Aktuator für Luftfahrtanwendungen
FR3035979B1 (fr) 2015-05-05 2018-08-17 Airbus Helicopters Loi de commande avancee pour empennage braquable
US10691140B2 (en) 2017-03-01 2020-06-23 Textron Innovations, Inc. Rotorcraft control mode transition smoothing
US11067981B2 (en) 2017-03-01 2021-07-20 Textron Innovations, Inc. Aircraft control mode transition smoothing
JP6779183B2 (ja) * 2017-07-18 2020-11-04 川崎重工業株式会社 電気機械式アクチュエータを備える航空機操舵システム
EP3613671B1 (en) * 2018-08-22 2021-05-05 Bell Helicopter Textron Inc. Rotorcraft control mode transition smoothing

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584814A (en) * 1967-07-18 1971-06-15 Bell Aerospace Corp Stability and control augmentation system
US4032083A (en) * 1976-04-12 1977-06-28 United Technologies Corporation Automatic gain control for stability augmentation systems
US4095763A (en) * 1977-02-25 1978-06-20 Textron, Inc. Fail safe augmentation system
US4103848A (en) * 1977-03-08 1978-08-01 United Technologies Corporation Variable incidence helicopter stabilator and fail safe actuator

Also Published As

Publication number Publication date
ES491516A0 (es) 1981-03-16
GB2050980A (en) 1981-01-14
BR8003067A (pt) 1980-12-23
IT8048697A0 (it) 1980-05-15
AU536643B2 (en) 1984-05-17
US4304375A (en) 1981-12-08
AU5839880A (en) 1980-11-20
JPS568799A (en) 1981-01-29
IL60081A (en) 1983-12-30
MX6588E (es) 1985-07-26
DE3018200C2 (es) 1992-04-30
DE3018200A1 (de) 1980-11-27
IT1147048B (it) 1986-11-19
CA1132683A (en) 1982-09-28
JPH037560B2 (es) 1991-02-01
FR2456663B1 (es) 1984-02-10
GB2050980B (en) 1983-03-02
FR2456663A1 (fr) 1980-12-12

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Legal Events

Date Code Title Description
FD1A Patent lapsed

Effective date: 19990301