ES8502652A1 - Perfeccionamientos en los sistemas de maniobra forzada del gradiente para controles de vuelo de aviones - Google Patents

Perfeccionamientos en los sistemas de maniobra forzada del gradiente para controles de vuelo de aviones

Info

Publication number
ES8502652A1
ES8502652A1 ES529905A ES529905A ES8502652A1 ES 8502652 A1 ES8502652 A1 ES 8502652A1 ES 529905 A ES529905 A ES 529905A ES 529905 A ES529905 A ES 529905A ES 8502652 A1 ES8502652 A1 ES 8502652A1
Authority
ES
Spain
Prior art keywords
maneuver
force gradient
pitch
longitudinal
pilot
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
ES529905A
Other languages
English (en)
Other versions
ES529905A0 (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.)
RTX Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of ES529905A0 publication Critical patent/ES529905A0/es
Publication of ES8502652A1 publication Critical patent/ES8502652A1/es
Expired legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0816—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability
    • G05D1/0841—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability to prevent a coupling between different modes

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Toys (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
  • Fluid-Driven Valves (AREA)
  • Compositions Of Oxide Ceramics (AREA)

Abstract

SISTEMA DE MANIOBRA FORZADA DEL GRADIENTE PARA CONTROLES DE VUELO DE AVIONES.COMPRENDE UN ACTUADOR (27) QUE SE PUEDE ACCIONAR PARA MODIFICAR LAS POSICIONES DE LAS SUPERFICIES AERODINAMICAS, DE ACUERDO A UNA SEN/AL DE GOBIERNO; UN DETECTOR DEL ANGULO DE ESCORA (11) QUE PROPORCIONA UNA SEN/AL INDICATIVA DEL ANGULO DE ESCORA DEL AVION, UTILIZANDO COMO REFERENCIA EL NIVEL DE VUELO DE LAS ALAS; Y ELEMENTOS DE CONTROL, CONECTADOS AL DETECTOR DEL ANGULO DE ESCORA, QUE ACTUAN SEGUN LA SEN/AL RECIBIDA, Y CONECTADOS AL ACTUADOR PARA QUE ESTE FUNCIONE DE ACUERDO AL ANGULO DE ESCORA.
ES529905A 1983-02-22 1984-02-21 Perfeccionamientos en los sistemas de maniobra forzada del gradiente para controles de vuelo de aviones Expired ES8502652A1 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/468,750 US4563743A (en) 1983-02-22 1983-02-22 Maneuver-force gradient system

Publications (2)

Publication Number Publication Date
ES529905A0 ES529905A0 (es) 1985-01-16
ES8502652A1 true ES8502652A1 (es) 1985-01-16

Family

ID=23861080

Family Applications (1)

Application Number Title Priority Date Filing Date
ES529905A Expired ES8502652A1 (es) 1983-02-22 1984-02-21 Perfeccionamientos en los sistemas de maniobra forzada del gradiente para controles de vuelo de aviones

Country Status (9)

Country Link
US (1) US4563743A (es)
JP (1) JPH07112835B2 (es)
AU (1) AU556414B2 (es)
DE (1) DE3406050C2 (es)
DK (1) DK80384A (es)
ES (1) ES8502652A1 (es)
GB (1) GB2135479B (es)
NO (1) NO158128C (es)
SE (1) SE450371B (es)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5170969A (en) * 1988-11-23 1992-12-15 The Boeing Company Aircraft rudder command system
US5001646A (en) * 1988-12-19 1991-03-19 Mcdonnell Douglas Corporation Automated helicopter flight control system
US5188511A (en) * 1991-08-27 1993-02-23 United Technologies Corporation Helicopter anti-torque device direct pitch control
US5213282A (en) * 1991-08-28 1993-05-25 United Technologies Corporation Maneuver feel system for a rotary wing aircraft
US5489830A (en) * 1994-09-09 1996-02-06 Mcdonnell Douglas Corporation Control system with loadfeel and backdrive
US7248949B2 (en) * 2004-10-22 2007-07-24 The Mitre Corporation System and method for stochastic aircraft flight-path modeling
DE102005055584B4 (de) * 2005-11-18 2009-04-09 Deutsches Zentrum für Luft- und Raumfahrt e.V. Steuerungseinrichtung und Verfahren zur Generierung von Steuerungssignalen für technische Vorrichtungen
US7784340B2 (en) * 2008-08-04 2010-08-31 Bell Helicopter Textron, Inc. Force gradient using a non-contact proximity sensor
WO2010016829A1 (en) * 2008-08-04 2010-02-11 Bell Helicopter Textron, Inc. Force gradient using a non-contact proximity sensor
US10479491B2 (en) * 2017-08-17 2019-11-19 Textron Innovations Inc. System and method for rotorcraft collective power hold

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4067517A (en) * 1976-02-03 1978-01-10 United Technologies Corporation Automatic heading synchronization control system
US4261537A (en) * 1979-02-28 1981-04-14 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Velocity vector control system augmented with direct lift control
US4392203A (en) * 1981-03-30 1983-07-05 United Technologies Corporation Aircraft coordinated turn with lagged roll rate
US4387430A (en) * 1981-03-30 1983-06-07 United Technologies Corporation Pitch stick force inhibit of aircraft automatic outer loop
US4484283A (en) * 1981-03-30 1984-11-20 United Technologies Corporation Aircraft roll-yaw fault protocols
US4387432A (en) * 1981-03-30 1983-06-07 United Technologies Corporation Pulsed aircraft actuator

Also Published As

Publication number Publication date
DE3406050C2 (de) 1997-12-11
AU2451184A (en) 1984-08-30
JPH07112835B2 (ja) 1995-12-06
US4563743A (en) 1986-01-07
ES529905A0 (es) 1985-01-16
SE8400953L (sv) 1984-08-23
DE3406050A1 (de) 1984-08-23
SE8400953D0 (sv) 1984-02-21
JPS59164297A (ja) 1984-09-17
SE450371B (sv) 1987-06-22
GB2135479B (en) 1987-03-11
GB8402940D0 (en) 1984-03-07
DK80384D0 (da) 1984-02-21
NO840608L (no) 1984-08-23
GB2135479A (en) 1984-08-30
DK80384A (da) 1984-08-23
NO158128C (no) 1988-07-20
NO158128B (no) 1988-04-11
AU556414B2 (en) 1986-10-30

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Legal Events

Date Code Title Description
FD1A Patent lapsed

Effective date: 19970401