GB1347297A - Multiplex actuator - Google Patents
Multiplex actuatorInfo
- Publication number
- GB1347297A GB1347297A GB2088171A GB2088171A GB1347297A GB 1347297 A GB1347297 A GB 1347297A GB 2088171 A GB2088171 A GB 2088171A GB 2088171 A GB2088171 A GB 2088171A GB 1347297 A GB1347297 A GB 1347297A
- Authority
- GB
- United Kingdom
- Prior art keywords
- differential
- servomotors
- rod
- actuator
- coupled
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Control Of Position Or Direction (AREA)
Abstract
1347297 Controlling aircraft E-SYSTEMS Inc 19 April 1971 [2 Feb 1970] 20881/71 Heading B7G [Also in Divisions G1 and H2] A redundant channel, velocity summing, multiplex actuator for adjusting the position of a control surface 56 of an aircraft comprises four servomotors, Fig. 2 (not shown), each having a respective control amplifier receiving the same control signal 11 ... 14, which may be derived from the pilot's control stick or the autopilot, stability or navigation controls, two sets of differential gearing coupling respective pairs of motor shafts to a third differential gear set whose rotary motion is converted to linear movement of a rod 16, a dual tandem servovalve 18 responsive to movement of the rod 16 to vary the fluid pressure flow signals to a dual tandem power ram 20 connected by members 52, 54 to the surface 56, and a linear voltage differential transformer 57 responsive to movement of the piston-rod 52 to generate separate but equal position feedback signals 59 ... 62 which are applied to the control amplifiers to balance the signals 11 ... 14. Fig. 4 shows a pair of the servomotors which are combined with respective tachometer and brake members to form units 150, 160 mounted on a housing 152. The motor shafts are coupled to a differential 158 by gears 154, 156, 164, 166, the differential 158 being coupled to a differential 176 by gears 172, 174. Another gear 178 of the differential 176 is coupled to a third differential (not shown) receiving the drives from units (not shown) similar to the units 150, 160. The shaft 182 of the differential 176 rotates with a speed equal to the velocity sum of the four units and engages the lead-screw 186 of a ball-screw assembly, whose ball nut 192 is restrained from rotation by retaining pins 194, 196 and is fixed to an extension shaft 198 terminating in a rod end 200 coupled to the rod 16 in Fig. 1. The rod end 200 is moved to a neutral position, in the event of failure of the actuator, by means of a centring assembly including a carriage 202 fastened to extension 198 by a nut 204, the carriage 202 moving with the nut 192 during normal operation. Upon actuator failure a spring 206, maintained in a housing 208 by spring guides 210, 212, forces the nut 192 to a centre position. To allow spring 206 to act on the actuator output, at least one brake must be released to allow back-driving the mechanism. Connectors 214, 216 transmit the control, feedback and velocity signals in the respective motor, amplifier and tachometer circuits. Operation of an arrangement, Fig. 3 (not shown), similar to Fig. 4, is discussed for failure of one, two or three of the servomotors, the or each failed motor preferably being stopped by its brake to prevent it being dragged by the remaining operative motor of the affected pair. Another similar arrangement, Fig. 5 (not shown) is discussed with respect to gear ratios, velocities and variation of the number of servomotors and gears. Gearing other than differential may be used to couple the servomotors which may be odd instead of even in number.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US767670A | 1970-02-02 | 1970-02-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1347297A true GB1347297A (en) | 1974-02-27 |
Family
ID=21727531
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB2088171A Expired GB1347297A (en) | 1970-02-02 | 1971-04-19 | Multiplex actuator |
Country Status (4)
Country | Link |
---|---|
US (1) | US3679956A (en) |
CA (1) | CA971246A (en) |
FR (1) | FR2079184B1 (en) |
GB (1) | GB1347297A (en) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA1026850A (en) * | 1973-09-24 | 1978-02-21 | Smiths Industries Limited | Dual, simultaneously operating control system with fault detection |
US4035705A (en) * | 1975-03-17 | 1977-07-12 | Sperry Rand Corporation | Fail-safe dual channel automatic pilot with maneuver limiting |
US4521707A (en) * | 1983-12-12 | 1985-06-04 | The Boeing Company | Triple redundant electromechanical linear actuator and method |
US5589749A (en) * | 1994-08-31 | 1996-12-31 | Honeywell Inc. | Closed loop control system and method using back EMF estimator |
US5670856A (en) * | 1994-11-07 | 1997-09-23 | Alliedsignal Inc. | Fault tolerant controller arrangement for electric motor driven apparatus |
US5929549A (en) * | 1998-04-02 | 1999-07-27 | Pacific Scientific Company | Fault tolerant electric machine |
FR2832685A1 (en) * | 2001-11-23 | 2003-05-30 | Conception & Dev Michelin Sa | ELECTRIC STEERING FOR VEHICLE, TRIPLE REDUNDANCY |
US9150308B2 (en) | 2012-02-10 | 2015-10-06 | Merlin Technology, Inc. | Rotorcraft autopilot system, components and methods |
CN104603706B (en) | 2012-02-10 | 2019-09-27 | 默林科技股份有限公司 | The control device and method of automatic pilot |
EP2913265B1 (en) * | 2014-02-27 | 2019-07-17 | Goodrich Actuation Systems SAS | Stability and control augmentation system |
US11014658B1 (en) | 2015-01-02 | 2021-05-25 | Delbert Tesar | Driveline architecture for rotorcraft featuring active response actuators |
DE102015203411A1 (en) * | 2015-02-26 | 2016-09-01 | Zf Friedrichshafen Ag | Actuator for aerospace applications |
US10318904B2 (en) | 2016-05-06 | 2019-06-11 | General Electric Company | Computing system to control the use of physical state attainment of assets to meet temporal performance criteria |
US11383824B2 (en) * | 2019-05-22 | 2022-07-12 | Honeywell International Inc. | Actuator systems and methods for flight control surface |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR958153A (en) * | 1950-03-04 | |||
US2589788A (en) * | 1947-10-13 | 1952-03-18 | Fell Developments Ltd | Internal-combustion engine power plant |
US3054039A (en) * | 1957-09-05 | 1962-09-11 | Meredith Dennis Lello | Plural channel servo systems |
US3136698A (en) * | 1962-08-24 | 1964-06-09 | Estle R Mann | Servo-controlled regulator for neutronic reactors |
US3146386A (en) * | 1963-07-10 | 1964-08-25 | Gerber Scientific Instr Co | Stepping motor drive |
US3422325A (en) * | 1964-03-10 | 1969-01-14 | Gerber Scientific Instr Co | Device for driving a movable part with precise control over its displacement during movement |
US3462662A (en) * | 1967-04-12 | 1969-08-19 | Lear Siegler Inc | Monitoring and fault correction system for a multiple channel servo actuator |
US3530355A (en) * | 1968-10-14 | 1970-09-22 | John Alfred Hodgkins | Automatic control systems |
-
1970
- 1970-02-02 US US7676A patent/US3679956A/en not_active Expired - Lifetime
-
1971
- 1971-02-02 FR FR7103383A patent/FR2079184B1/fr not_active Expired
- 1971-02-02 CA CA104,246A patent/CA971246A/en not_active Expired
- 1971-04-19 GB GB2088171A patent/GB1347297A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
FR2079184B1 (en) | 1976-04-16 |
CA971246A (en) | 1975-07-15 |
FR2079184A1 (en) | 1971-11-12 |
US3679956A (en) | 1972-07-25 |
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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 |