GB625636A - Improvements relating to the control of aircraft - Google Patents
Improvements relating to the control of aircraftInfo
- Publication number
- GB625636A GB625636A GB22511/47A GB2251147A GB625636A GB 625636 A GB625636 A GB 625636A GB 22511/47 A GB22511/47 A GB 22511/47A GB 2251147 A GB2251147 A GB 2251147A GB 625636 A GB625636 A GB 625636A
- Authority
- GB
- United Kingdom
- Prior art keywords
- servomotor
- piston
- cylinder
- cell
- twisting
- 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
- B64C17/00—Aircraft stabilisation not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
Abstract
625,636. Controlling aircraft. WILLIAMS, D. Aug. 13, 1947, No. 22511. [Class 4] An aircraft is provided with means for detecting relative twisting of parts of an aerofoil and for initiating in accordance with such twisting an operation for varying the lift or lift moment on the aerofoil to reduce the resultant air-loads thereon. In the arrangement shown, an open-sided torsion cell is provided near a wing tip, the relative movement of the opposite sides, due to twisting of the cell as the result of gusts, being utilized to move a load-relieving flap 8.- The cell is formed between spanwise and chordwise extending spars 2 and 5, 6 respectively by slitting the aerofoil skin at 3, 4 in a chordwise direction between the spar 2 and the trailing edge, and by slitting the latter between the slits 3, 4. A pseudo web 7, also slit in the spanwise direction, is provided near the trailing edge of the torsion cell, the relative movement of the two portions of the web being utilized to operate the flap 8, either directly or through a servomotor 9. A unit 10 is provided between the web 7 and servomotor 9 for differentiating between gradual changes of air load due to normal movements of the pilot's controls and sudden changes due to gusts, the latter only causing operation of the servomotor. As shown in Fig. 3, the unit 10 comprises a movable self-centring cylinder 11 containing a dashpot piston 12 and piston-rod 13. The latter is connected to the air load or gust responsive device and the cylinder is connected to the servo unit by a rod 14. The piston 12 moves freely in the cylinder 11 with slow changes of air load, but a sudden change results in movement of both the piston and cylinder to cause operation of the servomotor.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB22511/47A GB625636A (en) | 1947-08-13 | 1947-08-13 | Improvements relating to the control of aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB22511/47A GB625636A (en) | 1947-08-13 | 1947-08-13 | Improvements relating to the control of aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB625636A true GB625636A (en) | 1949-06-30 |
Family
ID=10180557
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB22511/47A Expired GB625636A (en) | 1947-08-13 | 1947-08-13 | Improvements relating to the control of aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB625636A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4457479A (en) * | 1982-02-15 | 1984-07-03 | Martine Daude | Winglets for aircraft wing tips |
GB2136746A (en) * | 1983-03-23 | 1984-09-26 | Messerschmitt Boelkow Blohm | Mechanism for increasing the flutter speeds of transonic aircraft wings |
US4725020A (en) * | 1980-12-09 | 1988-02-16 | The Boeing Company | Control system incorporating structural feedback |
-
1947
- 1947-08-13 GB GB22511/47A patent/GB625636A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4725020A (en) * | 1980-12-09 | 1988-02-16 | The Boeing Company | Control system incorporating structural feedback |
US4457479A (en) * | 1982-02-15 | 1984-07-03 | Martine Daude | Winglets for aircraft wing tips |
GB2136746A (en) * | 1983-03-23 | 1984-09-26 | Messerschmitt Boelkow Blohm | Mechanism for increasing the flutter speeds of transonic aircraft wings |
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