GB784329A - Improvements in or relating to aircraft - Google Patents
Improvements in or relating to aircraftInfo
- Publication number
- GB784329A GB784329A GB36???/54D GB3658854D GB784329A GB 784329 A GB784329 A GB 784329A GB 3658854 D GB3658854 D GB 3658854D GB 784329 A GB784329 A GB 784329A
- Authority
- GB
- United Kingdom
- Prior art keywords
- input
- potentiometers
- aircraft
- pilot
- amplifier
- 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)
- Fluid-Pressure Circuits (AREA)
Abstract
784,329. Controlling aircraft. HOBSON, Ltd., H. M., GLAZE, S. G., and SMITH, C. P. Dec. 12,1955 [Dec. 17, 1954], No. 36588/54. Class 4. A power-operated aircraft control system of the kind in which the servo motor input is positioned by the pilot's control member through an electricsignalling system, comprises a tandem hydraulic jack as the servo motor; each section of which has at least two independent control valves each actuated by the pilot's control member through an associated electro-mechanical transducer mechanism. In Fig. 1, the jack comprises two pistons 2, 2A on a rod pivoted to the aircraft, working in cylinders 3, 3A within a cylinder block 4. The inlet valves 5, 51, 5A, 5<SP>1</SP>A cooperate with inlet ports 15, 15<SP>1</SP>, 15A, 15<SP>1</SP>A and exhaust ports 11, 11<SP>1</SP>, 11A, 11<SP>1</SP>A. The cylinder block 4 is pivoted to the surface 1. The pilot's control member 7 actuates the wipers 16, 16A, 16B of potentiometers 8, 8A, 8B, to derive signals fed to amplifiers 9, 9A, 9B. The transducers 6, 61, 6A, 6<SP>1</SP>A which control the valves each have three coils, one of which is energized by each signalling system, e.g. amplifier 9 energizes coils 12, 12A, 12<SP>1</SP>A, 12<SP>1</SP>. Potentiometers 10, 10A, 10B fast with the cylinder block cooperate with fixed wipers 17, 17A, 17B to provide feed back signals to the amplifiers. The potentiometers 8 and 10 and amplifier 9 are energized from one current source, and the other two signalling systems from two further current sources. In a modification, each three coil transducer is replaced by three single coil transducers. There may be more than three signalling systems, each system energizing one input of each transducer mechanism. Each amplifier 9 saturates at an input level corresponding to a displacement error between the input and output members of the servo motor which is small compared with the total stroke of the output member, whereby if one signalling system is in a runaway condition, it may be overridden by the others. Specifications 777,273, 780,759 and 784,088 are referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3658854 | 1954-12-17 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB784329A true GB784329A (en) | 1957-10-09 |
Family
ID=34356291
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB36???/54D Expired GB784329A (en) | 1954-12-17 | 1954-12-17 | Improvements in or relating to aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB784329A (en) |
-
1954
- 1954-12-17 GB GB36???/54D patent/GB784329A/en not_active Expired
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