ES2089550T3 - Control automatico de coordinacion de viraje para avion de ala rotativa. - Google Patents

Control automatico de coordinacion de viraje para avion de ala rotativa.

Info

Publication number
ES2089550T3
ES2089550T3 ES92917949T ES92917949T ES2089550T3 ES 2089550 T3 ES2089550 T3 ES 2089550T3 ES 92917949 T ES92917949 T ES 92917949T ES 92917949 T ES92917949 T ES 92917949T ES 2089550 T3 ES2089550 T3 ES 2089550T3
Authority
ES
Spain
Prior art keywords
coordination
automatic control
rotary wing
turn
turn coordination
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
ES92917949T
Other languages
English (en)
Inventor
Phillip J Gold
Nicholas D Lappos
Don L Adams
Stuart C Wright
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
Application granted granted Critical
Publication of ES2089550T3 publication Critical patent/ES2089550T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • G05D1/085—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft to ensure stability to ensure coordination between different movements

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)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Toys (AREA)
  • Feedback Control In General (AREA)

Abstract

UN SISTEMA DE CONTROL DEL VUELO DE UN HELICOPTERO QUE INCLUYE UN SISTEMA AUTOMATICO DE COORDINACION DEL VIRAJE QUE PROPORCIONA UNA SEÑAL DE COMANDO DE GUIÑADA DE COORDINACION AL ROTOR DE COLA DEL HELICOPTERO. AL RECIBIR EL COMANDO, EL SISTEMA ALMACENA LAS POSICIONES EN VUELO DE COMPENSACION (EJ. SEÑALES INDICATIVAS DEL ANGULO DE INCLINACION, LA VELOCIDAD LATERAL RESPECTO AL SUELO Y ACELERACION LATERAL) CON LA QUE SE OBTIENE UNA COORDINACION AUTOMATICA DEL VIRAJE, LO QUE HACE QUE EL PILOTO CUENTE CON UNA COORDINACION DE VIRAJE AUTOMATICA SOBRE LAS POSICIONES EN VUELO DISTINTAS DEL NIVEL DE LAS ALAS.
ES92917949T 1991-08-28 1992-07-31 Control automatico de coordinacion de viraje para avion de ala rotativa. Expired - Lifetime ES2089550T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/751,433 US5222691A (en) 1991-08-28 1991-08-28 Automatic turn coordination trim control for rotary wing aircraft

Publications (1)

Publication Number Publication Date
ES2089550T3 true ES2089550T3 (es) 1996-10-01

Family

ID=25021961

Family Applications (1)

Application Number Title Priority Date Filing Date
ES92917949T Expired - Lifetime ES2089550T3 (es) 1991-08-28 1992-07-31 Control automatico de coordinacion de viraje para avion de ala rotativa.

Country Status (6)

Country Link
US (1) US5222691A (es)
EP (1) EP0600991B1 (es)
CA (1) CA2113731C (es)
DE (1) DE69205174T2 (es)
ES (1) ES2089550T3 (es)
WO (1) WO1993005459A1 (es)

Families Citing this family (21)

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US5310135A (en) * 1992-10-28 1994-05-10 United Technologies Corporation Helicopter integrated fire and flight control having coordinated area bombing control
US5553817A (en) * 1994-05-03 1996-09-10 United Technologies Corporation Turn coordination inhibit for rotary wing aircraft control system
US5617316A (en) * 1995-03-15 1997-04-01 Sikorsky Aircraft Corporation Maintaining attitude error constant in Euler singularity protection
US6145428A (en) * 1998-03-31 2000-11-14 Sikorsky Aircraft Corporation Integrated fire and flight control system for controlling the angle of attack of a rotary wing aircraft
FR2777535B1 (fr) * 1998-04-21 2000-06-16 Eurocopter France Systeme de commande de vol d'un aeronef, en particulier d'un helicoptere
US6076024A (en) * 1998-04-29 2000-06-13 Sikorsky Aircraft Corporation Earth-referenced wind adjustment for hovering aircraft
US6189836B1 (en) 1998-09-25 2001-02-20 Sikorsky Aircraft Corporation Model-following control system using acceleration feedback
US6648269B2 (en) 2001-12-10 2003-11-18 Sikorsky Aircraft Corporation Trim augmentation system for a rotary wing aircraft
US20040059474A1 (en) * 2002-09-20 2004-03-25 Boorman Daniel J. Apparatuses and methods for displaying autoflight information
US7188007B2 (en) 2003-12-24 2007-03-06 The Boeing Company Apparatuses and methods for displaying and receiving tactical and strategic flight guidance information
US7742846B2 (en) * 2006-06-02 2010-06-22 Sikorsky Aircraft Corporation Surface contact override landing scheme for a FBW rotary-wing aircraft
US8180562B2 (en) * 2008-06-04 2012-05-15 The Boeing Company System and method for taxi route entry parsing
US8386167B2 (en) 2008-11-14 2013-02-26 The Boeing Company Display of taxi route control point information
US9304516B2 (en) 2011-01-14 2016-04-05 Textron Innovations Inc. Flight control laws for vertical flight path
WO2012134447A2 (en) 2011-03-29 2012-10-04 Bell Helicopter Textron Inc. Flight control laws for full envelope banked turns
WO2016039834A2 (en) * 2014-08-29 2016-03-17 Sikorsky Aircraft Corporation Vector limiting of a rotor control volume
WO2016053408A1 (en) 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Acoustic signature variation of aircraft utilizing a clutch
WO2016054209A1 (en) 2014-10-01 2016-04-07 Sikorsky Aircraft Corporation Dual rotor, rotary wing aircraft
EP3561631B1 (en) * 2018-04-25 2022-11-23 The Boeing Company Pitch and thrust control for compound aircraft
US10935985B2 (en) 2018-04-25 2021-03-02 The Boeing Company Pitch and thrust control for tilt-rotor aircraft
CN110703754B (zh) * 2019-10-17 2021-07-09 南京航空航天大学 一种自动驾驶车辆路径与速度高度耦合的轨迹规划方法

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3057584A (en) * 1960-03-01 1962-10-09 Honeywell Regulator Co Automatic control apparatus
US3618879A (en) * 1969-08-14 1971-11-09 Bell Aerospace Corp Pitch/roll to yaw flight coordinator
US4003532A (en) * 1976-03-15 1977-01-18 United Technologies Corporation Heading hold logic
US4067517A (en) * 1976-02-03 1978-01-10 United Technologies Corporation Automatic heading synchronization control system
US4206891A (en) * 1978-10-26 1980-06-10 United Technologies Corporation Helicopter pedal feel force proportional to side slip
US4312039A (en) * 1980-01-24 1982-01-19 Sperry Corporation Transient free synchronization system
US4382283A (en) * 1980-08-08 1983-05-03 United Technologies Corporation Helicopter attitude and airspeed acquisition and retention system
US4371936A (en) * 1981-03-30 1983-02-01 United Technologies Corporation Attitude trimmed airspeed/attitude controls
US4484283A (en) * 1981-03-30 1984-11-20 United Technologies Corporation Aircraft roll-yaw fault protocols
US4371939A (en) * 1981-03-30 1983-02-01 United Technologies Corporation Roll attitude inhibit of aircraft coordinated turn disengagement
US4392203A (en) * 1981-03-30 1983-07-05 United Technologies Corporation Aircraft coordinated turn with lagged roll rate
US4477876A (en) * 1981-03-30 1984-10-16 United Technologies Corporation Dual response aircraft reference synchronization
US4500967A (en) * 1981-11-27 1985-02-19 United Technologies Corporation Aircraft short-term roll attitude retention system
US4603388A (en) * 1983-02-16 1986-07-29 Sperry Corporation VTOL altitude hold system with automatic ground effect compensation
US4626998A (en) * 1983-05-02 1986-12-02 United Technologies Corporation Heading reference trim system
US4645141A (en) * 1984-05-23 1987-02-24 Rockwell International Corporation Automatic flight control system
US5001646A (en) * 1988-12-19 1991-03-19 Mcdonnell Douglas Corporation Automated helicopter flight control system
US5117362A (en) * 1989-12-15 1992-05-26 Honeywell Path capture forcing function generator for aircraft vertical axis control
US5062583A (en) * 1990-02-16 1991-11-05 Martin Marietta Corporation High accuracy bank-to-turn autopilot

Also Published As

Publication number Publication date
US5222691A (en) 1993-06-29
DE69205174T2 (de) 1996-04-18
EP0600991B1 (en) 1995-09-27
CA2113731A1 (en) 1993-03-18
DE69205174D1 (de) 1995-11-02
CA2113731C (en) 2000-05-16
WO1993005459A1 (en) 1993-03-18
EP0600991A1 (en) 1994-06-15

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