GB1328592A - System for positioning a control element - Google Patents

System for positioning a control element

Info

Publication number
GB1328592A
GB1328592A GB3189471A GB3189471A GB1328592A GB 1328592 A GB1328592 A GB 1328592A GB 3189471 A GB3189471 A GB 3189471A GB 3189471 A GB3189471 A GB 3189471A GB 1328592 A GB1328592 A GB 1328592A
Authority
GB
United Kingdom
Prior art keywords
summed
transducers
actuator
gates
output
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
Application number
GB3189471A
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 Co
Original Assignee
E Systems Inc
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 E Systems Inc filed Critical E Systems Inc
Publication of GB1328592A publication Critical patent/GB1328592A/en
Priority to HK47678A priority Critical patent/HK47678A/en
Expired 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 or altitude of land, water, air, or space vehicles, e.g. automatic pilot
    • G05D1/0055—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements
    • G05D1/0077—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements using redundant signals or controls

Abstract

1328592 Fluid-pressure servo-motor systems E-SYSTEMS Inc 7 July 1971 [20 July 1970] 31894/71 Heading G3P [Also in Divisions G4 H2] In a system for positioning an element 82, such as the control surface of an aircraft, at least three transducers 10, 12, 14 each produce an output related to an electrical signal and the outputs are summed into a single mechanical motion applied to an actuator 44. The actuator adjusts servo valves or variable displacement pumps 50, 52 controlling servo-motors 66, 74 providing feedback to the actuator through links 84 and 45. A nut 58 allows the pumps or valves to be synchronized. Each transducer consists of an AC, DC or brushless DC motor 126 connected by a nut 131 and lead screw 132 to an output shaft and by a brush ring 125 to an amplifier, such as 16. A linear differential transformer 136 supplies a feedback signal to the amplifier and a further signal to a comparator 86 arranged to disable a failed channel to operate an indicator 94. The signals from the transducers are compared by differential amplifiers 96, 98 etc, Fig.4, having their output voltages applied to NAND gates 108....113 and NOR gates 114, 116, 118 so that with all channels operating correctly the output of each NOR gate will be at logic zero level. Should one channel differ from the others by an amount greater than a differential amplifier setting, one of the NOR gates will switch to a logic one level. The mechanical outputs of the transducers 10 and 12 are summed by a link 40 which has its movement summed with that of the transducer 14 by a link 42.
GB3189471A 1970-07-20 1971-07-08 System for positioning a control element Expired GB1328592A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
HK47678A HK47678A (en) 1971-07-08 1978-08-17 A process for the manufacture of benzodiazepine derivatives

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US5655170A 1970-07-20 1970-07-20

Publications (1)

Publication Number Publication Date
GB1328592A true GB1328592A (en) 1973-08-30

Family

ID=22005144

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3189471A Expired GB1328592A (en) 1970-07-20 1971-07-08 System for positioning a control element

Country Status (4)

Country Link
US (1) US3679156A (en)
DE (1) DE2135366C2 (en)
FR (1) FR2099479B1 (en)
GB (1) GB1328592A (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1488667A (en) * 1973-12-07 1977-10-12 Lucas Industries Ltd Actuating arrangement for aircraft control surfaces
US4270809A (en) * 1978-05-12 1981-06-02 Honda Giken Kogyo Kabushiki Kaisha Device for diagnosing trouble in a control circuit for electromagnetic actuators
GB2054173B (en) * 1978-07-21 1982-09-08 Honda Motor Co Ltd Trouble diagnosing device of a control system
NL8120344A (en) * 1980-09-02 1982-07-01 Rockwell International Corporation Te Los Angeles, Californie, Ver. St. V. Am.
US4466597A (en) * 1981-12-02 1984-08-21 Pneumo Corporation Electro-mechanical direct drive valve servo system with rotary to linear valve drive mechanism
FR2557853B1 (en) * 1984-01-09 1986-04-25 Aerospatiale FLIGHT CONTROL SYSTEM FOR AIRCRAFT
DE3462866D1 (en) * 1984-01-09 1987-05-07 Aerospatiale Aircraft flight control system
FR2557854B1 (en) * 1984-01-09 1987-01-23 Aerospatiale FLIGHT CONTROL SYSTEM FOR AIRCRAFT
US5074495A (en) * 1987-12-29 1991-12-24 The Boeing Company Load-adaptive hybrid actuator system and method for actuating control surfaces
US5033694A (en) * 1989-09-08 1991-07-23 Daiichi Electric Kabushiki Kaisha Attitude control device for air or sea transportation craft
US5082208A (en) * 1989-09-29 1992-01-21 The Boeing Company System and method for controlling an aircraft flight control member
US5182505A (en) * 1991-06-19 1993-01-26 Honeywell Inc. Aircraft control surface position transducer
FR2683502B1 (en) * 1991-11-12 1994-02-25 Aerospatiale Ste Nationale Indle SYSTEM FOR THE MOTION CONTROL OF A MOBILE MECHANICAL MEMBER, AND A FLIGHT CONTROL SYSTEM FOR AN AIRCRAFT COMPRISING THE SAME.
US5493497A (en) * 1992-06-03 1996-02-20 The Boeing Company Multiaxis redundant fly-by-wire primary flight control system
US5670856A (en) * 1994-11-07 1997-09-23 Alliedsignal Inc. Fault tolerant controller arrangement for electric motor driven apparatus
US5678786A (en) * 1995-12-06 1997-10-21 Mcdonnell Douglas Helicopter Co. Reconfigurable helicopter flight control system
DE19628395C2 (en) * 1996-07-13 1998-06-04 Daimler Benz Aerospace Airbus System for controlling the exhaust air volume flows of an aircraft
US5806805A (en) * 1996-08-07 1998-09-15 The Boeing Company Fault tolerant actuation system for flight control actuators
US6209825B1 (en) 1998-02-27 2001-04-03 Lockheed Martin Corporation Low power loss electro hydraulic actuator
US6481203B1 (en) 1999-06-10 2002-11-19 Tecumseh Products Company Electric shifting of a variable speed transmission
US6443399B1 (en) * 2000-07-14 2002-09-03 Honeywell International Inc. Flight control module merged into the integrated modular avionics
US6439512B1 (en) * 2000-08-24 2002-08-27 Hr Textron, Inc. All-hydraulic powered horizontal stabilizer trim control surface position control system
US6923405B2 (en) * 2003-11-17 2005-08-02 The Boeing Company Enhanced rudder control system
US7786684B2 (en) * 2007-10-22 2010-08-31 Honeywell International Inc. Electromechanical flight control system and method for rotorcraft
US8172174B2 (en) * 2008-11-13 2012-05-08 Honeywell International Inc. Hybrid electromechanical/hydromechanical actuator and actuation control system
GB2503397B (en) * 2011-03-29 2017-10-18 Bae Systems Plc A control system for an un-manned vehicle

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2898889A (en) * 1958-10-03 1959-08-11 John V Foster Mechanically-limited, electrically operated hydraulic valve system for aircraft controls
US3027878A (en) * 1959-06-10 1962-04-03 Honeywell Regulator Co Fluid motor control apparatus
US3198082A (en) * 1962-11-09 1965-08-03 Lockheed Aircraft Corp Electrical primary flight control system utilizing redundant channels
US3469162A (en) * 1965-04-13 1969-09-23 Hawker Siddeley Dynamics Ltd Multiplex-type control apparatus
US3401600A (en) * 1965-12-23 1968-09-17 Bell Aerospace Corp Control system having a plurality of control chains each of which may be disabled in event of failure thereof
US3426650A (en) * 1965-12-23 1969-02-11 Bell Aerospace Corp Triple channel redundant hydraeric control system
US3422767A (en) * 1966-12-05 1969-01-21 Webster Electric Co Inc Variable displacement swashplate pumps
US3554084A (en) * 1967-11-17 1971-01-12 Honeywell Inc Redundant force summing servo unit
US3505929A (en) * 1968-04-16 1970-04-14 Gen Electric Redundant flight control servoactuator

Also Published As

Publication number Publication date
FR2099479A1 (en) 1972-03-17
US3679156A (en) 1972-07-25
DE2135366A1 (en) 1972-02-03
DE2135366C2 (en) 1982-04-01
FR2099479B1 (en) 1975-02-21

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PE20 Patent expired after termination of 20 years