GB787102A - Compensating parachute - Google Patents
Compensating parachuteInfo
- Publication number
- GB787102A GB787102A GB31749/55A GB3174955A GB787102A GB 787102 A GB787102 A GB 787102A GB 31749/55 A GB31749/55 A GB 31749/55A GB 3174955 A GB3174955 A GB 3174955A GB 787102 A GB787102 A GB 787102A
- Authority
- GB
- United Kingdom
- Prior art keywords
- parachute
- pilot
- canopy
- aircraft
- fin
- 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
- B64C19/00—Aircraft control not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Types And Forms Of Lifts (AREA)
Abstract
787,102. Aircraft fitted with high lift devices. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU NORD. Nov. 7, 1955 [Feb. 26, 1955], No. 31749/55. Class 4. An aircraft equipped with a high-lift device has also a device for compensating for any diving moment produced by the high lift device, comprising a parachute attached to the aircraft at a point above its centre of gravity, and means for deploying the parachute at the same time as the high lift device becomes operative. In Fig. 2, the elevators 2 are depressed for high lift by a jack 13 controlled by a pilot's control 11. When the jack nears the completion of its stroke, contacts 15 bridge contacts 14 and the cover 8 of the tail fin mounted parachute housing 4 is electrically released, whereupon the spring 10 ejects a pilot parachute 9 withdrawing the main canopy 3. In Fig. 6 an auxiliary line 26 extends from a pilot-controlled winch 19 to the apex of the canopy 3, whereby the pilot may controllably invert the canopy, varying the drag and hence the pitching moment produced. In Fig. 4 (not shown) the anchorage point of the canopy is movable vertically along the trailing edge of the fin by a pilot controlled winch, again to control the pitching moment. Yawing control in this case is by the use of spoilers. In Fig. 5, the parachute'is normally housed in a tube 4 in the fin, and when deployed is attached to the aircraft fin by two lines, one 20 of fixed length and the other 23 of a length adjusted by the pilotcontrolled winch 19, so that the line of action of the drag may be varied as shown in dashed lines.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR787102X | 1955-02-26 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB787102A true GB787102A (en) | 1957-12-04 |
Family
ID=9218738
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB31749/55A Expired GB787102A (en) | 1955-02-26 | 1955-11-07 | Compensating parachute |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB787102A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3058702A (en) * | 1959-02-05 | 1962-10-16 | English Electric Co Ltd | Brake parachute attachments to aircraft |
US3089667A (en) * | 1959-05-02 | 1963-05-14 | Junkers Flugzeng Und Motorenwe | Jet aircraft for short take-off and landing distances |
EP0061353A1 (en) * | 1981-03-25 | 1982-09-29 | Peter Best | Parachute unit |
US4538778A (en) * | 1983-09-15 | 1985-09-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Dual towline spin-recovery device |
US4784353A (en) * | 1983-03-02 | 1988-11-15 | The Boeing Company | Aircrafts tail section drag compensating for nose-down pitching moment |
-
1955
- 1955-11-07 GB GB31749/55A patent/GB787102A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3058702A (en) * | 1959-02-05 | 1962-10-16 | English Electric Co Ltd | Brake parachute attachments to aircraft |
US3089667A (en) * | 1959-05-02 | 1963-05-14 | Junkers Flugzeng Und Motorenwe | Jet aircraft for short take-off and landing distances |
EP0061353A1 (en) * | 1981-03-25 | 1982-09-29 | Peter Best | Parachute unit |
US4784353A (en) * | 1983-03-02 | 1988-11-15 | The Boeing Company | Aircrafts tail section drag compensating for nose-down pitching moment |
US4538778A (en) * | 1983-09-15 | 1985-09-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Dual towline spin-recovery device |
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