US20050021193A1 - Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system - Google Patents

Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system Download PDF

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Publication number
US20050021193A1
US20050021193A1 US10/703,564 US70356403A US2005021193A1 US 20050021193 A1 US20050021193 A1 US 20050021193A1 US 70356403 A US70356403 A US 70356403A US 2005021193 A1 US2005021193 A1 US 2005021193A1
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United States
Prior art keywords
control
oscillations
damping means
controllable damping
fly
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Abandoned
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US10/703,564
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English (en)
Inventor
Nathalie Raimbault
Jean-Pierre Gautier
Alain Sagansan
Pierre Fabre
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Airbus Operations SAS
Bright Technologies LLC
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Individual
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Assigned to AIRBUS FRANCE reassignment AIRBUS FRANCE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FABRE, PIERRE, GAUTIER, JEAN-PIERRE, RAIMBAULT, NATHALIE, SAGANSAN, ALAIN
Publication of US20050021193A1 publication Critical patent/US20050021193A1/en
Assigned to BRIGHT TECHNOLOGIES, LLC reassignment BRIGHT TECHNOLOGIES, LLC CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: KWOLEK, LLC
Priority to US12/765,713 priority Critical patent/US8473121B2/en
Assigned to AIRBUS OPERATIONS SAS reassignment AIRBUS OPERATIONS SAS MERGER (SEE DOCUMENT FOR DETAILS). Assignors: AIRBUS FRANCE
Abandoned legal-status Critical Current

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    • 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

Definitions

  • the present invention relates to a fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations, and to a control for such a control system.
  • the pilot may attempt to further increase the amplitude by which he tilts said control member.
  • the amplitude of turning of the aerodynamic surfaces may then exceed that corresponding to the initial command, which means that the pilot then reduces the tilt of said control member, thus leading, with a delay, to a return of the aerodynamic surfaces, etc.
  • Oscillations caused by coupling and generally referred to in aeronautical parlance as “pilot induced oscillations” (PIO) therefore occur in the aircraft and may degrade the precision of the flying.
  • PIO pilot induced oscillations
  • the object of the present invention is to overcome these drawbacks.
  • the invention relates to a fly-by-wire control system and to a control alerting the pilot to the occurence of pilot induced oscillation and acting to avoid its effects.
  • the fly-by-wire control system involving electric flight commands for an aircraft comprising:
  • the action of said controllable damping means on said control may be of an amplitude that is constant irrespective of the amplitude of said oscillations.
  • said detection means deliver a detection signal the amplitude of which increases with the amplitude of said oscillations
  • the action of said controllable damping means on said control may advantageously increase in magnitude with the amplitude of said oscillations.
  • the present invention additionally relates to a mobile control able to generate at least one electric command for controlling an aircraft about at least one of its axes of maneuver, said control being intended for a fly-by-wire control system comprising means for detecting, in said command, any oscillations corresponding to pilot induced oscillations.
  • this control for example of the stick or rudder type, is notable in that it comprises controllable damping means for said control and in that said controllable damping means are controlled by said detection means in such a way that said controllable damping means exert on said control an action that opposes the rate of travel of the latter when said detection means detect such oscillations.
  • said structural damping means and said controllable damping means are formed of a single controllable damper controlled by said detection means such that:
  • Said controllable damping means may be of mechanical or hydraulic known type.
  • said controllable damping means are formed by a magnetic machine, for example a synchronous machine with a permanent-magnet rotor, operated in a known way to deliver a resistive torque that varies with the rotational speed.
  • said control may be able to generate two electric commands for controlling said aircraft about two of its axes of maneuver and be intended for a fly-by-wire control system comprising means for detecting, in each of said commands, any oscillations corresponding to pilot induced oscillations.
  • said control comprises controllable damping means controlled by said oscillation detection means and able to act on said control in its movements corresponding to each of said commands.
  • FIGS. 1 and 2 schematically illustrate two embodiments of the present invention.
  • the fly-by-wire control system for an aircraft illustrated schematically in FIG. 1 , comprises a control stick system 1 , able to generate a roll command and a pitch command.
  • the control stick system 1 comprises a mobile grip 2 which, via a known mechanism, can pivot about a roll-control axis R-R and a pitch-control axis T-T.
  • the pivoting of the grip 2 about the roll-control axis R-R (double-headed arrow 3 ) is detected by a sensor 4 .
  • the pivoting of the grip 2 about the pitch-control axis T-T (double-headed arrow 5 ) is detected by a sensor 6 .
  • the sensors 4 and 6 generate electric commands for roll and pitch, which correspond to the pivotings of the grip 2 and which are sent to the fly-by-wire computers 7 of said system, via lines 8 and 9 respectively.
  • the computers 7 calculate corresponding turn commands for controlled aerodynamic surfaces (flaps, ailerons, rudders, etc.) 10 of said aircraft (not depicted), and via lines 11 , send appropriate electric orders to the actuators 12 of these controlled aerodynamic surfaces 10 .
  • artificial sensation devices 13 and 14 providing the pilot with feedback are mounted on the roll-control and pitch-control axes.
  • the device 13 consists for example of a strong scissors mechanism and the device 14 of a strong link rod.
  • the control stick system 1 comprises two dampers 15 and 16 , the damping characteristics of which can be modified by an electric order. They are, for example, of mechanical or hydraulic known type.
  • the controllable damper 15 is connected to the roll axis R-R and the controllable damper 16 is connected to the pitch axis T-T to damp the rotation of the grip 2 about these two axes.
  • fly-by-wire computers 7 incorporate means for detecting any oscillations, corresponding to pilot induced oscillations, in the commands originating from the sensors 4 and 6 , these detection means being able to deliver, on respective lines 17 and 18 bound for said dampers 15 and 16 , orders to modify the damping characteristics of these dampers according to the amplitude of said induced oscillations.
  • the control stick system 20 comprises electric dampers 21 and 22 in place of the mechanical or hydraulic dampers 15 and 16 .
  • the dampers 21 and 22 are, for example, synchronous machines the rotor of which carries permanent magnets and is wedged on the axis R-R or the axis T-T, respectively.
  • the resistive torque exerted by these synchronous machines on said axes can be controlled by electric commands generated by the means for detecting said oscillations belonging to the computers 7 and sent to said dampers 21 and 22 via lines 23 or 24 respectively.

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  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Vibration Prevention Devices (AREA)
  • Vehicle Body Suspensions (AREA)
  • Steering Control In Accordance With Driving Conditions (AREA)
  • Toys (AREA)
  • Details Of Aerials (AREA)
  • Mechanical Control Devices (AREA)
  • Position Input By Displaying (AREA)
US10/703,564 2002-11-18 2003-11-10 Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system Abandoned US20050021193A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US12/765,713 US8473121B2 (en) 2002-11-18 2010-04-22 Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0214388 2002-11-18
FR0214388A FR2847352B1 (fr) 2002-11-18 2002-11-18 Systeme de commandes de vol electriques pour aeronef comportant une detection de couplages oscillatoires de pilotage et organe de pilotage pour un tel systeme

Related Child Applications (1)

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US12/765,713 Continuation US8473121B2 (en) 2002-11-18 2010-04-22 Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system

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US20050021193A1 true US20050021193A1 (en) 2005-01-27

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US10/703,564 Abandoned US20050021193A1 (en) 2002-11-18 2003-11-10 Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system
US12/765,713 Expired - Fee Related US8473121B2 (en) 2002-11-18 2010-04-22 Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system

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Application Number Title Priority Date Filing Date
US12/765,713 Expired - Fee Related US8473121B2 (en) 2002-11-18 2010-04-22 Fly-by-wire control system for an aircraft comprising detection of pilot induced oscillations and a control for such a system

Country Status (6)

Country Link
US (2) US20050021193A1 (de)
EP (1) EP1420320B1 (de)
AT (1) ATE313823T1 (de)
CA (1) CA2447283C (de)
DE (1) DE60302861T2 (de)
FR (1) FR2847352B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040098176A1 (en) * 2002-11-18 2004-05-20 Nathalie Raimbault Method and device for detecting pilot induced oscillations in an aircraft
US20060064207A1 (en) * 2004-09-17 2006-03-23 Hiltner Dale W Methods and systems for analyzing system operator coupling susceptibility
US7996120B2 (en) 2005-07-28 2011-08-09 Airbus France Method and device for flying an aircraft according to at least one flying line
US20130075535A1 (en) * 2011-09-26 2013-03-28 Airbus Operations (Sas) Electrical rudder control system for an aircraft
US20150248941A1 (en) * 2011-05-09 2015-09-03 U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration Radiation shielding materials containing hydrogen, boron and nitrogen
CN106741870A (zh) * 2016-11-30 2017-05-31 中国直升机设计研究所 一种座舱操纵系统及方法
US9947424B2 (en) 2013-03-19 2018-04-17 D&D Corporation Coating type radiation-shielding material and radiation-shielding elastomer material
CN114044125A (zh) * 2021-12-21 2022-02-15 中国商用飞机有限责任公司 飞行器操纵控制系统及控制方法

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202008005918U1 (de) * 2008-04-29 2009-09-03 Jungheinrich Aktiengesellschaft Betätigungsanordnung für Steuerorgane
US10482783B2 (en) 2015-11-06 2019-11-19 Frasca International, Inc. Adaptive assistance for flight simulation
FR3086273B1 (fr) * 2018-09-26 2020-10-09 Safran Electronics & Defense Dispositif de commande de vol d’un aeronef

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3236478A (en) * 1964-04-23 1966-02-22 North American Aviation Inc Flight control system
US4030011A (en) * 1975-03-24 1977-06-14 Honeywell Inc. Multimode control systems
US4298833A (en) * 1980-02-29 1981-11-03 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus for damping operator induced oscillations of a controlled system
US4477043A (en) * 1982-12-15 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Biodynamic resistant control stick
US4607202A (en) * 1984-08-28 1986-08-19 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Apparatus for automatically eliminating control force errors in aircraft, especially helicopters
US5076517A (en) * 1989-08-14 1991-12-31 United Technologies Corporation Programmable, linear collective control system for a helicopter
US5107080A (en) * 1989-12-01 1992-04-21 Massachusetts Institute Of Technology Multiple degree of freedom damped hand controls
US5125602A (en) * 1989-02-20 1992-06-30 Aerospatiale Societe Nationale Industrielle Tilting stick control device, especially for an aircraft, and system comprising two such devices
US5900710A (en) * 1996-11-22 1999-05-04 Aerospatiale Societe Nationale Industrielle System for coupling control columns
US5935177A (en) * 1997-02-06 1999-08-10 Accurate Automation Corporation Pilot-induced oscillation detection and compensation apparatus and method
US6325331B1 (en) * 1998-12-11 2001-12-04 Bell Helicopter Textron Inc. Trim actuator
US20020135327A1 (en) * 2001-03-22 2002-09-26 Zenon Szulyk Dual input servo coupled control sticks

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DE2807902C2 (de) * 1978-02-24 1980-04-30 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Steuereinrichtung mit aktiver Kraft rückführung
USH703H (en) * 1987-07-30 1989-11-07 The United States Of America As Represented By The Secretary Of The Air Force Manual control apparatus with electable mechanical impedance
US6199028B1 (en) * 1999-02-04 2001-03-06 The United States Of America As Represented By The Secretary Of The Air Force Detector for human loss of tracking control
US6311110B1 (en) * 1999-06-17 2001-10-30 Lord Corporation Adaptive off-state control method
US20030183728A1 (en) * 2002-03-29 2003-10-02 The Boeing Company Aircraft control surface controller and associated method
US20040078120A1 (en) * 2002-10-16 2004-04-22 Edgar Melkers Non-linear compensation of a control system having an actuator and a method therefore

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3236478A (en) * 1964-04-23 1966-02-22 North American Aviation Inc Flight control system
US4030011A (en) * 1975-03-24 1977-06-14 Honeywell Inc. Multimode control systems
US4298833A (en) * 1980-02-29 1981-11-03 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Apparatus for damping operator induced oscillations of a controlled system
US4477043A (en) * 1982-12-15 1984-10-16 The United States Of America As Represented By The Secretary Of The Air Force Biodynamic resistant control stick
US4607202A (en) * 1984-08-28 1986-08-19 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Apparatus for automatically eliminating control force errors in aircraft, especially helicopters
US5125602A (en) * 1989-02-20 1992-06-30 Aerospatiale Societe Nationale Industrielle Tilting stick control device, especially for an aircraft, and system comprising two such devices
US5076517A (en) * 1989-08-14 1991-12-31 United Technologies Corporation Programmable, linear collective control system for a helicopter
US5107080A (en) * 1989-12-01 1992-04-21 Massachusetts Institute Of Technology Multiple degree of freedom damped hand controls
US5900710A (en) * 1996-11-22 1999-05-04 Aerospatiale Societe Nationale Industrielle System for coupling control columns
US5935177A (en) * 1997-02-06 1999-08-10 Accurate Automation Corporation Pilot-induced oscillation detection and compensation apparatus and method
US6325331B1 (en) * 1998-12-11 2001-12-04 Bell Helicopter Textron Inc. Trim actuator
US20020135327A1 (en) * 2001-03-22 2002-09-26 Zenon Szulyk Dual input servo coupled control sticks

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040098176A1 (en) * 2002-11-18 2004-05-20 Nathalie Raimbault Method and device for detecting pilot induced oscillations in an aircraft
US7225061B2 (en) * 2002-11-18 2007-05-29 Airbus France Method and device for detecting pilot induced oscillations in an aircraft
US20060064207A1 (en) * 2004-09-17 2006-03-23 Hiltner Dale W Methods and systems for analyzing system operator coupling susceptibility
US7272473B2 (en) * 2004-09-17 2007-09-18 The Boeing Company Methods and systems for analyzing system operator coupling susceptibility
US7996120B2 (en) 2005-07-28 2011-08-09 Airbus France Method and device for flying an aircraft according to at least one flying line
US20150248941A1 (en) * 2011-05-09 2015-09-03 U.S.A. As Represented By The Administrator Of The National Aeronautics And Space Administration Radiation shielding materials containing hydrogen, boron and nitrogen
US20130075535A1 (en) * 2011-09-26 2013-03-28 Airbus Operations (Sas) Electrical rudder control system for an aircraft
US8979036B2 (en) * 2011-09-26 2015-03-17 Airbus Operations Sas Electrical rudder control system for an aircraft
US9947424B2 (en) 2013-03-19 2018-04-17 D&D Corporation Coating type radiation-shielding material and radiation-shielding elastomer material
CN106741870A (zh) * 2016-11-30 2017-05-31 中国直升机设计研究所 一种座舱操纵系统及方法
CN114044125A (zh) * 2021-12-21 2022-02-15 中国商用飞机有限责任公司 飞行器操纵控制系统及控制方法

Also Published As

Publication number Publication date
ATE313823T1 (de) 2006-01-15
DE60302861D1 (de) 2006-01-26
US8473121B2 (en) 2013-06-25
EP1420320A1 (de) 2004-05-19
DE60302861T2 (de) 2006-08-03
EP1420320B1 (de) 2005-12-21
US20100200701A1 (en) 2010-08-12
FR2847352A1 (fr) 2004-05-21
CA2447283C (fr) 2012-04-24
CA2447283A1 (fr) 2004-05-18
FR2847352B1 (fr) 2005-01-28

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