GB1076188A - Improved stall-correcting apparatus for aircraft - Google Patents
Improved stall-correcting apparatus for aircraftInfo
- Publication number
- GB1076188A GB1076188A GB47701/63A GB4770163A GB1076188A GB 1076188 A GB1076188 A GB 1076188A GB 47701/63 A GB47701/63 A GB 47701/63A GB 4770163 A GB4770163 A GB 4770163A GB 1076188 A GB1076188 A GB 1076188A
- Authority
- GB
- United Kingdom
- Prior art keywords
- incidence
- sensors
- aircraft
- elevators
- piston
- 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
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract 2
- 239000012530 fluid Substances 0.000 abstract 1
- 239000007789 gas Substances 0.000 abstract 1
- 229910052757 nitrogen Inorganic materials 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
- B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
Abstract
1,076,188. Stall correcting apparatus. BRITISH AIRCRAFT CORPORATION (OPERATING) Ltd. March 2, 1965 [Dec. 3, 1963], No. 47701/63. Headings: B7G and B7W. [Also in Division F1] An aircraft has incidence sensing means arranged, when the incidence exceeds a given value, to actuate a stall warning device such as a stick shaker, and afterwards to actuate elevators to pitch the aircraft nose-down. The elevators may be actuated a predetermined time after the warning, to allow the pilot to correct, or at an incidence higher than the warning incidence. The signal to the elevators may be modified by a generator (20) in accordance with variations, e.g. in flap angle. The pilot's elevator control may comprise mechanical links (15) to spring links (18) and power actuated units (16) coupled to the elevators (Figs. 1 and 2, not shown), and the pitch signal from the incidence sensing means (10) may be applied either through an autopilot (19, Fig. 1) or directly (Fig. 2) to lock the spring links (18) and to operate the units (16). In another embodiment (Fig. 3, not shown), two sensors (30, 31) give warning of the approach of a stall and two further sensors (34, 35), are operative at a higher incidence. The sensors (30, 31) actuate relays (44, 45, 49, 50) so that signals from the sensors (34, 35) cause klaxons (46, 47) to be sounded and valves (55, 56) to be opened, permitting compressed gas to flow to a ram (36) to push the control column. Where the aircraft has turbo-jet engines which are liable to flame out at high incidence, the sensors (30, 31) may also operate igniters in the engines. The signals from the sensors are modified by phase advance networks and altitude switches to compensate for rate of change of incidence and for altitude. The ram (Fig. 4, not shown), has two pistons in series the piston (63) having a hollow rod (66) which abuts, and allows compressed nitrogen to pass to, a second piston (69) carrying the actuating rod (70). Thus initially, fluid pressure is applied to both pistons. The travel of the piston (63) is limited by an abutment (68), and then only the piston (69) produces a load on the rod (70), and this is further reduced by a precompressed spring (74). The force applied to the control column is therefore reduced from its initial value to avoid an excessive negative " g " on the aircraft.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB47701/63A GB1076188A (en) | 1963-12-03 | 1963-12-03 | Improved stall-correcting apparatus for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB47701/63A GB1076188A (en) | 1963-12-03 | 1963-12-03 | Improved stall-correcting apparatus for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1076188A true GB1076188A (en) | 1967-07-19 |
Family
ID=10445960
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB47701/63A Expired GB1076188A (en) | 1963-12-03 | 1963-12-03 | Improved stall-correcting apparatus for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1076188A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2311331A (en) * | 1996-03-22 | 1997-09-24 | Boughton T T Sons Ltd | Hydraulic ram booster |
EP1936386A3 (en) * | 2006-12-19 | 2010-10-20 | Rosemount Aerospace Inc. | Air data stall protection system |
-
1963
- 1963-12-03 GB GB47701/63A patent/GB1076188A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2311331A (en) * | 1996-03-22 | 1997-09-24 | Boughton T T Sons Ltd | Hydraulic ram booster |
EP1936386A3 (en) * | 2006-12-19 | 2010-10-20 | Rosemount Aerospace Inc. | Air data stall protection system |
US8620495B2 (en) | 2006-12-19 | 2013-12-31 | Rosemount Aerospace Inc. | Air data stall protection system |
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