GB1226991A - - Google Patents
Info
- Publication number
- GB1226991A GB1226991A GB1226991DA GB1226991A GB 1226991 A GB1226991 A GB 1226991A GB 1226991D A GB1226991D A GB 1226991DA GB 1226991 A GB1226991 A GB 1226991A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fluid
- yaw
- pitch
- sensors
- mark
- 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
- 239000012530 fluid Substances 0.000 abstract 7
- 230000001141 propulsive effect Effects 0.000 abstract 2
- 235000015842 Hesperis Nutrition 0.000 abstract 1
- 235000012633 Iberis amara Nutrition 0.000 abstract 1
- 238000005096 rolling process Methods 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
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/10—Ejector seats
Landscapes
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
1,226,991. Ejection seats. HONEYWELL Ltd. 17 April, 1969 [12 March, 1968], No. 11967/68. Heading B7G. An ejection seat comprises propulsion means 4, 7 at each side of the seat 1, each propulsion means being able to eject a high velocity stream in either of two generally downward directions, one direction having a forward component and the other a backward component, and control apparatus 12-15 responsive to the output of pitch and yaw sensing means 10 and 11 to switch the propulsive streams between their two possible directions to oppose the sensed pitch and yaw movements. Sensing means 10 and 11 are pure fluid vortex sensors, and their outputs are summed by fluid summing amplifiers 21-24; considering the left half of Fig. 2, the outputs from summing amplifiers 21 and 22 cause a pressure difference between lines 25 and 26, thereby determining the mark/space ratio of fluid bi-stable oscillator 12. The oscillator mark output appears at 12a, and the space output at 12b, and both are amplified by a fluid amplifiee cascade 14 and fed, at 14a, 14b, to opposite sides of bifurcated propulsion nozzle 4. The fluid flow along lines 14a, 14b deflects the main propulsive stream between bifurcations 5 or 6, the amount of time the stream passes through each bifurcation depending on the mark/space ratio; the sensed pitch and yaw movements may thus be opposed, using nozzle 4 in conjunction with similarly operated nozzle 7. Vortex sensors 10, 11, require an integrating component (not shown), as they are rate sensors. The fluid control system may operate from a pressurized air supply; the fluid control system may also be replaced by electromechanical sensors, electronic amplifiers and oscillators and electromechanical deflecting vanes. Nozzles 4 and 7 may be connected to a single rocket unit, or to separate rockets 2, 3. The mean thrust of nozzles 4 and 7 may be displaced slightly forwards or backwards from the yaw axis to cornpensate for any known tendency of seat 1 to pitch or yaw, but this would generate small rolling moments.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1196768 | 1968-03-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1226991A true GB1226991A (en) | 1971-03-31 |
Family
ID=9995955
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1226991D Expired GB1226991A (en) | 1968-03-12 | 1968-03-12 |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1226991A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4236687A (en) * | 1979-05-24 | 1980-12-02 | The United States Of America As Represented By The Secretary Of The Navy | Ejection seat with pitch, roll and yaw control |
GB2363448A (en) * | 2000-06-16 | 2001-12-19 | Baker Martin Aircraft Co | Ejection seat rocket motors |
-
1968
- 1968-03-12 GB GB1226991D patent/GB1226991A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4236687A (en) * | 1979-05-24 | 1980-12-02 | The United States Of America As Represented By The Secretary Of The Navy | Ejection seat with pitch, roll and yaw control |
GB2363448A (en) * | 2000-06-16 | 2001-12-19 | Baker Martin Aircraft Co | Ejection seat rocket motors |
GB2363448B (en) * | 2000-06-16 | 2004-02-25 | Baker Martin Aircraft Co | Improvements in or relating to ejection seat rocket motors |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PLNP | Patent lapsed through nonpayment of renewal fees |