GB1328592A - System for positioning a control element - Google Patents
System for positioning a control elementInfo
- 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
Links
- 238000006073 displacement reaction Methods 0.000 abstract 1
- 230000001360 synchronised effect Effects 0.000 abstract 1
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
- G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
- G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls
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)
- Servomotors (AREA)
- Fluid-Pressure Circuits (AREA)
- Safety Devices In Control Systems (AREA)
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.
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)
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 |
EP0058713B1 (en) * | 1980-09-02 | 1990-07-18 | Rockwell International Corporation | Actuator system for a control surface of an aircraft |
US4466597A (en) * | 1981-12-02 | 1984-08-21 | Pneumo Corporation | Electro-mechanical direct drive valve servo system with rotary to linear valve drive mechanism |
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 |
FR2557853B1 (en) * | 1984-01-09 | 1986-04-25 | 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 |
WO2012131330A1 (en) * | 2011-03-29 | 2012-10-04 | Bae Systems Plc | Actuator control system |
Family Cites Families (9)
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 |
-
1970
- 1970-07-20 US US56551A patent/US3679156A/en not_active Expired - Lifetime
-
1971
- 1971-07-08 GB GB3189471A patent/GB1328592A/en not_active Expired
- 1971-07-15 DE DE2135366A patent/DE2135366C2/en not_active Expired
- 1971-07-20 FR FR7126519A patent/FR2099479B1/fr not_active Expired
Also Published As
Publication number | Publication date |
---|---|
FR2099479A1 (en) | 1972-03-17 |
FR2099479B1 (en) | 1975-02-21 |
DE2135366C2 (en) | 1982-04-01 |
US3679156A (en) | 1972-07-25 |
DE2135366A1 (en) | 1972-02-03 |
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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 |