GB886111A - Aircraft - Google Patents
AircraftInfo
- Publication number
- GB886111A GB886111A GB1460959A GB1460959A GB886111A GB 886111 A GB886111 A GB 886111A GB 1460959 A GB1460959 A GB 1460959A GB 1460959 A GB1460959 A GB 1460959A GB 886111 A GB886111 A GB 886111A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- compresser
- auxiliary
- booms
- engine
- 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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
886,111. Direct-lift aircraft. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. April 13, 1960 [April 29, 1959], No. 14609/59. Class 4. [Also in Group XXVI] An aircraft having a fuselage, a wing, twin booms spaced from the fuselage, one on each side thereof, and a stabiliser supported by the booms, further comprises a plurality of lifting fans mounted in the booms and arranged to draw in air and to discharge it downwardly to produce lifting thrust on the aircraft. The aircraft comprises a fuselage 1, high-mounted wing 2 and a pair of booms 3 which carry a tail unit 4, 5. A cluster of three jet-propulsion engines 6 is mounted beneath the wing adjacent each boom and each boom houses a bank of eight direct-lift fans located in longitudinal positions that ensure that their resulting line of lifting thrust passes through the aircraft centre of gravity. Each engine 6 comprises an auxiliary compresser independent of the engine compresser, which may be driven by an exhaust gas driven turbine forward or rearward of the main engine or the auxiliary compresser may be driven by clutches from the turbine rotor driving the main engine compresser or by gearing. The air delivered by the auxiliary compressers is fed to a common balancing duct 47-from whence it passes through ducts 48 and 49 to the inlet volute 16 of each lifting fan 7 to drive a turbine 13 associated with fan blades 12. Stator blades 14 and 17 are provided and any set of blades may be angularly adjustable and the fan inlet nozzle may be of variable area. Adjustable shutters 19, 22 are provided at each fan inlet and outlet orifice respectively and the duct from each engine 6 incorporates a control valve and a non-return valve so that when the fans are inoperative with shutters 19, 22 closed the compressed air from the auxiliary compresser may be directed to a supplementary propulsive jet. Differential adjustment of the fan blades, intake area or closure shutters may be used to give a lateral or pitching control effect. Specification 811,840 is referred to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1460959A GB886111A (en) | 1959-04-29 | 1959-04-29 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1460959A GB886111A (en) | 1959-04-29 | 1959-04-29 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB886111A true GB886111A (en) | 1962-01-03 |
Family
ID=10044323
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1460959A Expired GB886111A (en) | 1959-04-29 | 1959-04-29 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB886111A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1254473B (en) * | 1964-09-01 | 1967-11-16 | Boelkow Gmbh | Lifting fan shaft with flap louvers arranged in the exit cross-section |
| GB2127756A (en) * | 1982-09-24 | 1984-04-18 | John Lloyd | Protection for under-carriage of air liners |
| WO2013126117A1 (en) * | 2011-12-05 | 2013-08-29 | Aurora Flight Sciences Corporation | System and method for improving transition lift-fan performance |
-
1959
- 1959-04-29 GB GB1460959A patent/GB886111A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1254473B (en) * | 1964-09-01 | 1967-11-16 | Boelkow Gmbh | Lifting fan shaft with flap louvers arranged in the exit cross-section |
| GB2127756A (en) * | 1982-09-24 | 1984-04-18 | John Lloyd | Protection for under-carriage of air liners |
| WO2013126117A1 (en) * | 2011-12-05 | 2013-08-29 | Aurora Flight Sciences Corporation | System and method for improving transition lift-fan performance |
| US10766614B2 (en) | 2011-12-05 | 2020-09-08 | Aurora Flight Sciences Corporation | Method and system for improving transition lift-fan performance |
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