GB811212A - Improvements in or relating to cyclic pitch controls for helicopters - Google Patents
Improvements in or relating to cyclic pitch controls for helicoptersInfo
- Publication number
- GB811212A GB811212A GB733/56A GB73356A GB811212A GB 811212 A GB811212 A GB 811212A GB 733/56 A GB733/56 A GB 733/56A GB 73356 A GB73356 A GB 73356A GB 811212 A GB811212 A GB 811212A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- cyclic pitch
- helicopter
- helicopters
- input
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
811,212. Helicopters. McCUTCHEN, C. W. Jan. 9, 1956, No. 733/56. Class 4. A helicopter comprises means for measuring the acceleration of the helicopter in a direction substantially perpendicular to the tip path plane, and further means under control of the measuring means for adjusting the cyclic pitch to correct instability of flight. Fig. 1 shows a rotor mast 1 supporting blades 2 on arms 3 through flapping hinges 4. An arm 6 extends from a pivot 5 on each blade to a common head 7 connected to a push-pull rod 8. The movements of this rod reflect the coning angle, taken as a measure of the acceleration perpendicular to the tip path plane. This forms one input to a mechanical multiplier 10, the other input being the pilots' fore-and-aft cyclic pitch signal on shaft 11. The product, on shaft 12, is fed to a mixer 13 which adds a trim signal on shaft 14, the output on shaft 15 operating the cyclic pitch mechanism. The trim is such that the helicopter may hover with the control stick in neutral position. A suitable mechanical multiplier is described. Specification 811,211 is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB733/56A GB811212A (en) | 1956-01-09 | 1956-01-09 | Improvements in or relating to cyclic pitch controls for helicopters |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB733/56A GB811212A (en) | 1956-01-09 | 1956-01-09 | Improvements in or relating to cyclic pitch controls for helicopters |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB811212A true GB811212A (en) | 1959-04-02 |
Family
ID=9709584
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB733/56A Expired GB811212A (en) | 1956-01-09 | 1956-01-09 | Improvements in or relating to cyclic pitch controls for helicopters |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB811212A (en) |
-
1956
- 1956-01-09 GB GB733/56A patent/GB811212A/en not_active Expired
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