DE69218439D1 - Lenkfühlsystem für ein drehflügelflugzeug - Google Patents

Lenkfühlsystem für ein drehflügelflugzeug

Info

Publication number
DE69218439D1
DE69218439D1 DE69218439T DE69218439T DE69218439D1 DE 69218439 D1 DE69218439 D1 DE 69218439D1 DE 69218439 T DE69218439 T DE 69218439T DE 69218439 T DE69218439 T DE 69218439T DE 69218439 D1 DE69218439 D1 DE 69218439D1
Authority
DE
Germany
Prior art keywords
sensing system
turning plane
steering sensing
steering
turning
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 - Fee Related
Application number
DE69218439T
Other languages
English (en)
Other versions
DE69218439T2 (de
Inventor
Phillip Gold
Stuart 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.)
Raytheon Technologies 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 DE69218439D1 publication Critical patent/DE69218439D1/de
Publication of DE69218439T2 publication Critical patent/DE69218439T2/de
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
    • G05D1/0061—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements for transition from automatic pilot to manual pilot and vice versa

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)
  • Feedback Control In General (AREA)
DE69218439T 1991-08-28 1992-08-21 Lenkfühlsystem für ein drehflügelflugzeug Expired - Fee Related DE69218439T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US07/751,456 US5213282A (en) 1991-08-28 1991-08-28 Maneuver feel system for a rotary wing aircraft
PCT/US1992/007126 WO1993005464A1 (en) 1991-08-28 1992-08-21 Maneuver feel system for a rotary wing aircraft

Publications (2)

Publication Number Publication Date
DE69218439D1 true DE69218439D1 (de) 1997-04-24
DE69218439T2 DE69218439T2 (de) 1997-06-26

Family

ID=25022046

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69218439T Expired - Fee Related DE69218439T2 (de) 1991-08-28 1992-08-21 Lenkfühlsystem für ein drehflügelflugzeug

Country Status (6)

Country Link
US (1) US5213282A (de)
EP (1) EP0601122B1 (de)
CA (1) CA2114326C (de)
DE (1) DE69218439T2 (de)
ES (1) ES2101872T3 (de)
WO (1) WO1993005464A1 (de)

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6092919A (en) * 1995-08-01 2000-07-25 Guided Systems Technologies, Inc. System and method for adaptive control of uncertain nonlinear processes
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
FR2814433B1 (fr) * 2000-09-28 2002-12-13 Eurocopter France Dispositif de commande de vol d'un aeronef, en particulier d'un helicoptere
US6648269B2 (en) 2001-12-10 2003-11-18 Sikorsky Aircraft Corporation Trim augmentation system for a rotary wing aircraft
US20070235594A1 (en) * 2006-04-06 2007-10-11 Honeywell International, Inc. Pilot flight control stick feedback system
FR2903379B1 (fr) * 2006-07-07 2008-08-29 Thales Sa Convertisseur de commande de facteur de charge en consigne d'ecart d'assiette longitudinale
US7658349B2 (en) * 2006-10-26 2010-02-09 Honeywell International Inc. Pilot flight control stick haptic feedback system and method
US20080156939A1 (en) * 2007-01-03 2008-07-03 Honeywell International, Inc. Active pilot flight control stick system with passive electromagnetic feedback
US7930074B2 (en) * 2007-03-19 2011-04-19 Sikorsky Aircraft Corporation Vertical speed and flight path command module for displacement collective utilizing tactile cueing and tactile feedback
FR2948629B1 (fr) * 2009-07-28 2011-08-19 Eurocopter France Amortissement variable de restitution haptique pour chaine cinematique de changement d'attitude de vol d'un aeronef
WO2012096668A1 (en) 2011-01-14 2012-07-19 Bell Helicopter Textron Inc. Flight control laws for vertical flight path control
CN102736630A (zh) * 2011-04-02 2012-10-17 南京航空航天大学 基于三余度的光传飞控系统的实现方法
EP2543589B1 (de) * 2011-07-06 2018-09-05 Airbus Helicopters Primäre Flugsteuerungen
US8718841B2 (en) 2012-02-14 2014-05-06 Sikorsky Aircraft Corporation Method and system for providing sideslip envelope protection
FR3023016B1 (fr) 2014-06-30 2016-07-01 Airbus Helicopters Systeme et procede de commande de vol en tenue de trajectoire pour un aeronef a voilure tournante
FR3023018B1 (fr) 2014-06-30 2016-06-10 Airbus Helicopters Procede et systeme de mise en vol stationnaire d'un aeronef a voilure tournante en tenue de trajectoire ou tenue de cap selon sa vitesse d'avancement
FR3023017B1 (fr) 2014-06-30 2016-06-10 Airbus Helicopters Systeme et procede de commande de vol d'un aeronef a voilure tournante en tenue de trajectoire ou tenue de cap selon sa vitesse d'avancement
US20160033300A1 (en) * 2014-08-01 2016-02-04 Safe Flight Instrument Corporation Arinc 429 data substitution
EP3186146B1 (de) * 2014-08-28 2019-10-09 Sikorsky Aircraft Corporation Anstellwinkelsteuerungssystem
WO2016043942A2 (en) 2014-08-28 2016-03-24 Sikorsky Aircraft Corporation Pitch control system
US10353402B2 (en) 2014-08-29 2019-07-16 Sikorsky Aircraft Corporation Vector limiting of a rotor control volume
CN104678764B (zh) * 2015-01-28 2017-03-01 北京航空航天大学 基于解析重构信号的飞控系统传感器混合余度方法
CN105116717B (zh) * 2015-08-11 2018-06-29 中国航空工业集团公司西安飞机设计研究所 四余度信号监控方法和装置
US10642283B2 (en) * 2016-10-07 2020-05-05 Sikorsky Aircraft Corporation Simultaneous flight path control and attitude control with control axis splitting
EP3670335A1 (de) * 2018-12-20 2020-06-24 Bombardier Inc. Verfahren und system zur längssteuerung eines flugzeugs
CN112114574B (zh) * 2019-06-21 2023-12-05 北京自动化控制设备研究所 一种双余度伺服系统故障检测与隔离方法及系统

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4129275A (en) * 1974-11-22 1978-12-12 The Boeing Company Automatic flight control apparatus for aircraft
US4206891A (en) * 1978-10-26 1980-06-10 United Technologies Corporation Helicopter pedal feel force proportional to side slip
US4313165A (en) * 1979-10-23 1982-01-26 United Technologies Corporation Force feel actuator with limited proportional/integral error feedback
US4420808A (en) * 1980-04-01 1983-12-13 United Technologies Corporation Multi-axis force stick, self-trimmed aircraft flight control system
US4385356A (en) * 1981-03-30 1983-05-24 United Technologies Corporation Non-saturating airspeed/attitude controls
US4563743A (en) * 1983-02-22 1986-01-07 United Technologies Corporation Maneuver-force gradient system
US4849900A (en) * 1986-05-02 1989-07-18 The Boeing Company Flight control system and method
ES2013274B3 (es) * 1986-06-14 1990-05-01 Deutsche Forschungsanstalt Fur Luft- Und Raumfahrt E V Sistema para determinacion de la velocidad de vuelo de helicopteros
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
US5213282A (en) 1993-05-25
DE69218439T2 (de) 1997-06-26
EP0601122B1 (de) 1997-03-19
ES2101872T3 (es) 1997-07-16
WO1993005464A1 (en) 1993-03-18
CA2114326C (en) 2000-09-26
EP0601122A1 (de) 1994-06-15

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8339 Ceased/non-payment of the annual fee