ES2101872T3 - Sistema de maniobra para una aeronave de ala rotativa. - Google Patents

Sistema de maniobra para una aeronave de ala rotativa.

Info

Publication number
ES2101872T3
ES2101872T3 ES92920122T ES92920122T ES2101872T3 ES 2101872 T3 ES2101872 T3 ES 2101872T3 ES 92920122 T ES92920122 T ES 92920122T ES 92920122 T ES92920122 T ES 92920122T ES 2101872 T3 ES2101872 T3 ES 2101872T3
Authority
ES
Spain
Prior art keywords
signal
heading
aircraft
control point
attitude
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
ES92920122T
Other languages
English (en)
Inventor
Phillip J Gold
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.)
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 ES2101872T3 publication Critical patent/ES2101872T3/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
    • G05D1/0055—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)

Abstract

UN SISTEMA DE CONTROL DEL VUELO DE UNA AERONAVE DE ALAS ROTATIVAS (21) QUE RECIBE SEÑALES INDICATIVAS DEL GRADO DE CABECEO DE LA AERONAVE (88), LA ACTITUD EN CABECEO (86), EL ANGULO DE INCLINACION TRANSVERSAL (87) Y LA VELOCIDAD RESPECTO AL AIRE (66) Y QUE RESPONDE A UN COMANDO DE CABECEO PROCEDENTE DE UN CONTROLADOR DE CRUCETA DESEQUILIBRADA (29) PARA CONTROLAR EL CABECEO DE LA AERONAVE Y QUE CONSTA DE ELEMENTOS PARA PROGRAMAR Y PROPORCIONAR UNA SEÑAL DE FIJACION DEL PUNTO DE CONTROL INDICATIVA DE LA RAPIDEZ DE CAMBIO DESEADA DEL CABECEO DE LA AERONAVE, ELEMENTOS PARA CALCULAR LA DIFERENCIA ENTRE EL PUNTO ANTEDICHO Y LA SEÑAL INDICATIVA DEL GRADO DE CABECEO Y PARA PROPORCIONAR UNA SEÑAL DE ERROR DEL GRADO DE CABECEO INDICATIVA DEL MISMO, UN ELEMENTO DE MODELISMO INVERSO (56) QUE RESPONDE A DICHA SEÑAL DE FIJACION DEL PUNTO DE CONTROL PARA PROGRAMAR UNA SEÑAL DE COMANDO AVANCE PARA IMPULSAR LA AERONAVE DE MODO QUE RESPONDA DE UNA MANERA ESENCIALMENTE IGUAL A DICHA SEÑAL DE FIJACION DEL PUNTO DE CONTROL, UN ELEMENTO PARA PROPORCIONAR UNA VERIFICACION LA MANIOBRA AL CONTROLADOR DE CRUCETA DESEQUILIBRADA (29) CUANDO EL ANGULO DE INCLINACION TRANSVERSAL (29) DE LA AERONAVE SOBREPASA UN VALOR PREDETERMINADO A BASE DE ACONDICIONAR DICHA SEÑAL DE FIJACION DEL PUNTO DE CONTROL, UN ELEMENTO PARA INTEGRAR PASADO EL MOMENTO DICHA SEÑAL DE FIJACION DEL PUNTO DE CONTROL ACONDICIONADA PARA OBTENER UN PUNTO DE CONTROL DE LA ACTITUD EN CABECEO DESEADO, PARA COMPARAR DICHO PUNTO DE CONTROL DE LA ACTITUD EN CABECEO CON LA SEÑAL INDICATIVA DE LA ACTITUD EN CABECEO (86) Y OBTENER UNA SEÑAL DE ERROR RELATIVA A LA ACTITUD EN CABECEO INDICATIVA DE LA DIFERENCIA Y UN ELEMENTO QUE RESPONDE A DICHA SEÑAL DE ERROR RELATIVA AL GRADO DE CABECEO, A DICHA SEÑAL DE COMANDO DE AVANCE Y A DICHA SEÑAL DE ERROR RELATIVA A LA ACTITUD EN CABECEO, PARA PROPORCIONAR UNA SEÑAL DE COMANDO DEL CABECEO AL ROTOR PRINCIPAL DE LA AERONAVE.
ES92920122T 1991-08-28 1992-08-21 Sistema de maniobra para una aeronave de ala rotativa. Expired - Lifetime ES2101872T3 (es)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
ES2101872T3 true ES2101872T3 (es) 1997-07-16

Family

ID=25022046

Family Applications (1)

Application Number Title Priority Date Filing Date
ES92920122T Expired - Lifetime ES2101872T3 (es) 1991-08-28 1992-08-21 Sistema de maniobra para una aeronave de ala rotativa.

Country Status (6)

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

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
CA2824932C (en) 2011-01-14 2016-03-22 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 (en) * 2011-07-06 2018-09-05 Airbus Helicopters Primary flight controls
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
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
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
US20160033300A1 (en) * 2014-08-01 2016-02-04 Safe Flight Instrument Corporation Arinc 429 data substitution
US10676185B2 (en) * 2014-08-28 2020-06-09 Sikorsky Aircraft Corporation Rotary wing aircraft pitch control system
WO2016043942A2 (en) 2014-08-28 2016-03-24 Sikorsky Aircraft Corporation Pitch control system
EP3186149B1 (en) * 2014-08-29 2019-04-10 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 (en) * 2018-12-20 2020-06-24 Bombardier Inc. Method and system for longitudinal control of aircraft
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
EP0249848B1 (de) * 1986-06-14 1990-02-28 Deutsches Zentrum für Luft- und Raumfahrt e.V. System zur Bestimmung der Fluggeschwindigkeit von Hubschraubern
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
DE69218439T2 (de) 1997-06-26
EP0601122A1 (en) 1994-06-15
DE69218439D1 (de) 1997-04-24
EP0601122B1 (en) 1997-03-19
WO1993005464A1 (en) 1993-03-18
CA2114326C (en) 2000-09-26
US5213282A (en) 1993-05-25

Similar Documents

Publication Publication Date Title
ES2101872T3 (es) Sistema de maniobra para una aeronave de ala rotativa.
US2650046A (en) Automatic control for helicopters
US4129275A (en) Automatic flight control apparatus for aircraft
CA1091213A (en) Variable incidence helicopter stabilator and fail safe actuator
GB1487137A (en) Flight path control apparatus
ES2048985T3 (es) Dispositivo de mando de palanca basculante y sistema de mando de vuelo para aeronave que integra como minimo un tal dispositivo de mando.
IL102482A (en) Seyal introduction limit to control system
CA2965494A1 (en) Autopilot system, and related components and methods
US4005835A (en) Automatic flight control means for rotary wing aircraft having attitude-air speed control
JPH09510933A (ja) 対気速度を制御するヘリコプターの自動操縦装置
US4303212A (en) Vertical seeking aircrew escape system
CA1085368A (en) Helicopter pitch rate feedback bias for pitch axis maneuvering stability and load feel
EP3326911B1 (en) Rotor speed control using a feed-forward rotor speed command
US3658280A (en) Altitude and glide slope track controller
US3819135A (en) System for augmenting aircraft attitude stability using vertical vane type sensors
US2561873A (en) Flight control system
US2919081A (en) Stabilizing system for helicopter aircraft
JPH0338499A (ja) 可変主翼をもつ航空機
US2959230A (en) Mechanical directional and trim control for helicopters
US2520665A (en) Gyroscope control device for bombs
US3061240A (en) Control system for helicopter
US2513120A (en) Airplane automatic pilot
WO2004041381A3 (en) Control systems for use with flying craft and other remote elements
US3098627A (en) Automatic stabilizing apparatus for aircraft
JP2000005451A (ja) ラジコン飛行機の緊急姿勢制御装置

Legal Events

Date Code Title Description
FG2A Definitive protection

Ref document number: 601122

Country of ref document: ES