GB788608A - Improvements in or relating to aircraft - Google Patents
Improvements in or relating to aircraftInfo
- Publication number
- GB788608A GB788608A GB35409/54A GB3540954A GB788608A GB 788608 A GB788608 A GB 788608A GB 35409/54 A GB35409/54 A GB 35409/54A GB 3540954 A GB3540954 A GB 3540954A GB 788608 A GB788608 A GB 788608A
- Authority
- GB
- United Kingdom
- Prior art keywords
- valve
- pressure
- control pressure
- control
- port
- 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
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/40—Transmitting means with power amplification using fluid pressure
- B64C13/46—Transmitting means with power amplification using fluid pressure with artificial feel
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
788,608. Aircraft feel simulators. HOBSON, Ltd., H. M., SMITH, C. P., HULLEY, B. J., and PUGH, A. T. Oct. 26, 1955 [Dec. 7, 1954], No. 35409/54. Class 4. An aircraft fitted with power or servo-tab operated ailerons includes a feel simulator comprising a housing and a piston therein linked to a control column so as to be moved by departure of the column from neutral position, and means for establishing in the housing a hydraulic pressure opposing movement of the piston and increasing the pressure with increase in the rate of roll. In Fig. 1, the pilot's control stick 10 operates the ailerons 12 through servo-mechanism 13, 14, and is coupled to the piston 17 of a jack 16 pivoted to the aircraft, the jack containing fluid at a control pressure which offers resistance to the movement of the pilot's control stick from its neutral position. The control pressure fluid is supplied by a conduit 21 from a hydraulic valve block 22, supplied at a port 23 with fluid under pressure by a pump 25 and a reservoir 25<SP>1</SP> connected to an exhaust port 26 on the valve. Bob weights 49, 50 mounted on levers pivoted to the fuselage and connected by links 52, 53 to a lever 47 pivoted on the aircraft at 48, exert a torque on the lever proportional to the square of the rate of roll, due to centrifugal force. The lever 47 is also connected to a damper 55, and has an integral part 46 abutting a push rod 44. The hydraulic valve block 22, Fig. 2, comprises a valve 28 having lands 29, 30 and a waisted part 31 co-operating with a pressure part 23 an exhaust port 26, and a port 41 leading to the control pressure conduit 21. The control pressure acts on one end of valve 28 through a passage 34, and a spring 35 acts on the other end through a push rod 37 and a relief valve 38. The push rod 44 abuts a member 43 which forms one abutment for the spring 35, so that if the push rod is urged upwardly by the bob weights due to an increase in the rate of roll, the force of the spring is increased, and the valve 28 moves upwardly against the control pressure, placing the pressure port 23 in communication with the control pressure port 41, raising the control pressure until this is sufficient to return the valve 28 to its neutral position. Similarly a decrease in the rate of roll decreases the control pressure. The valve is also moved to allow fluid to flow into and out of the jack 15 as the pilot moves his control stick. Should the valve stick, the pilot can still move his stick, opening the relief valve to put the jack in communication with the exhaust port 26 through passage 40. Specification 734,437 is referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB35409/54A GB788608A (en) | 1954-12-07 | 1954-12-07 | Improvements in or relating to aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB35409/54A GB788608A (en) | 1954-12-07 | 1954-12-07 | Improvements in or relating to aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB788608A true GB788608A (en) | 1958-01-02 |
Family
ID=10377401
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB35409/54A Expired GB788608A (en) | 1954-12-07 | 1954-12-07 | Improvements in or relating to aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB788608A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1254976B (en) * | 1961-11-24 | 1967-11-23 | Hobson Ltd H M | Hydraulic control force simulator for an airplane |
CN110645216A (en) * | 2018-06-27 | 2020-01-03 | 赛峰起落架***公司 | Method for controlling three-position slide valve |
-
1954
- 1954-12-07 GB GB35409/54A patent/GB788608A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1254976B (en) * | 1961-11-24 | 1967-11-23 | Hobson Ltd H M | Hydraulic control force simulator for an airplane |
CN110645216A (en) * | 2018-06-27 | 2020-01-03 | 赛峰起落架***公司 | Method for controlling three-position slide valve |
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