FR2983456B1 - AIRCRAFT CONTROL SURFACE ACTUATION SYSTEM, AND ASSOCIATED METHOD - Google Patents

AIRCRAFT CONTROL SURFACE ACTUATION SYSTEM, AND ASSOCIATED METHOD

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Publication number
FR2983456B1
FR2983456B1 FR1161096A FR1161096A FR2983456B1 FR 2983456 B1 FR2983456 B1 FR 2983456B1 FR 1161096 A FR1161096 A FR 1161096A FR 1161096 A FR1161096 A FR 1161096A FR 2983456 B1 FR2983456 B1 FR 2983456B1
Authority
FR
France
Prior art keywords
force
actuator
control surface
generate
measurement signal
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.)
Active
Application number
FR1161096A
Other languages
French (fr)
Other versions
FR2983456A1 (en
Inventor
Matthieu Pujos
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.)
Safran Electronics and Defense SAS
Original Assignee
Sagem Defense Securite SA
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 Sagem Defense Securite SA filed Critical Sagem Defense Securite SA
Priority to FR1161096A priority Critical patent/FR2983456B1/en
Publication of FR2983456A1 publication Critical patent/FR2983456A1/en
Application granted granted Critical
Publication of FR2983456B1 publication Critical patent/FR2983456B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C13/00Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/24Transmitting means
    • B64C13/38Transmitting means with power amplification
    • B64C13/50Transmitting means with power amplification using electrical energy
    • B64C13/503Fly-by-Wire
    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05BCONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00Programme-control systems
    • G05B19/02Programme-control systems electric
    • G05B19/18Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
    • G05B19/404Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for compensation, e.g. for backlash, overshoot, tool offset, tool wear, temperature, machine construction errors, load, inertia
    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05BCONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B2219/00Program-control systems
    • G05B2219/30Nc systems
    • G05B2219/41Servomotor, servo controller till figures
    • G05B2219/41188Compensate position error between two different axis as function of type of transducer

Abstract

L'invention concerne un système d'actionnement d'une surface de contrôle d'un aéronef, comprenant : - un premier actionneur (2) apte à générer une première force pour déplacer la surface de contrôle, - un premier capteur de force (14) couplé au premier actionneur (2) et apte à générer un premier signal de mesure de force proportionnel à la première force, - un deuxième actionneur (3) apte à générer une deuxième force pour déplacer la surface de contrôle, - un deuxième capteur de force (15) couplé au deuxième actionneur (3) et apte à générer un deuxième signal de mesure de force proportionnel à la deuxième force, - une unité de commande électronique (4) apte générer un signal de commande du premier actionneur (2) en fonction d'un signal de mesure de position du premier actionneur proportionnel à une position mesurée du premier actionneur et d'un signal de correction de la position mesurée qui dépend d'une différence entre le premier signal de mesure de force et le deuxième signal de mesure de force, afin d'annuler un écart permanent entre la première force et la deuxième force générées par les actionneurs.The invention relates to a system for actuating a control surface of an aircraft, comprising: - a first actuator (2) capable of generating a first force for moving the control surface, - a first force sensor (14 ) coupled to the first actuator (2) and able to generate a first force measurement signal proportional to the first force, - a second actuator (3) able to generate a second force to move the control surface, - a second pressure sensor force (15) coupled to the second actuator (3) and able to generate a second force measurement signal proportional to the second force, - an electronic control unit (4) able to generate a control signal for the first actuator (2) in function of a position measurement signal of the first actuator proportional to a measured position of the first actuator and of a correction signal for the measured position which depends on a difference between the first force measurement signal and the second force signal my ure of force, in order to cancel a permanent difference between the first force and the second force generated by the actuators.

FR1161096A 2011-12-02 2011-12-02 AIRCRAFT CONTROL SURFACE ACTUATION SYSTEM, AND ASSOCIATED METHOD Active FR2983456B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1161096A FR2983456B1 (en) 2011-12-02 2011-12-02 AIRCRAFT CONTROL SURFACE ACTUATION SYSTEM, AND ASSOCIATED METHOD

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1161096A FR2983456B1 (en) 2011-12-02 2011-12-02 AIRCRAFT CONTROL SURFACE ACTUATION SYSTEM, AND ASSOCIATED METHOD

Publications (2)

Publication Number Publication Date
FR2983456A1 FR2983456A1 (en) 2013-06-07
FR2983456B1 true FR2983456B1 (en) 2014-06-20

Family

ID=45592610

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1161096A Active FR2983456B1 (en) 2011-12-02 2011-12-02 AIRCRAFT CONTROL SURFACE ACTUATION SYSTEM, AND ASSOCIATED METHOD

Country Status (1)

Country Link
FR (1) FR2983456B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3020036B1 (en) 2014-04-16 2017-11-24 Airbus Operations Sas ACTUATOR SYSTEM FOR AN AIRCRAFT GOVERNOR.
US11745857B2 (en) 2016-03-30 2023-09-05 Goodrich Actuation Systems Sas Aircraft force-fight mechanism
EP3225540B1 (en) * 2016-03-30 2020-11-18 Goodrich Actuation Systems SAS Force fight mitigation
EP4029776A1 (en) * 2021-01-18 2022-07-20 Goodrich Actuation Systems SAS Actuator control for force fight mitigation

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8245967B2 (en) * 2008-11-25 2012-08-21 The Boeing Company Actuator force equalization controller
US8885315B2 (en) * 2009-10-15 2014-11-11 Hamilton Sundstrand Corporation Multi-actuator motion control system
US8583293B2 (en) * 2009-11-09 2013-11-12 Honeywell International Inc. Flight control surface actuation force fight mitigation system and method
US20110251739A1 (en) * 2010-04-09 2011-10-13 Honeywell International Inc. Distributed fly-by-wire system

Also Published As

Publication number Publication date
FR2983456A1 (en) 2013-06-07

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