GB860497A - Improvements relating to turbo-jet propulsion units in aircraft - Google Patents
Improvements relating to turbo-jet propulsion units in aircraftInfo
- Publication number
- GB860497A GB860497A GB14953/59A GB1495359A GB860497A GB 860497 A GB860497 A GB 860497A GB 14953/59 A GB14953/59 A GB 14953/59A GB 1495359 A GB1495359 A GB 1495359A GB 860497 A GB860497 A GB 860497A
- Authority
- GB
- United Kingdom
- Prior art keywords
- unit
- wing
- parts
- aircraft
- tiltable
- 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
- B64C29/0041—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 jet motors
- B64C29/0066—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 jet motors with horizontal jet and jet deflector
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
860,497. Aircraft. DAIMLER-BENZ A.G. May 1, 1959 [May 2, 1958], No. 14953/59. Class 4. [Also in Group XXVI] A turbo-jet propulsion unit is mounted in an aircraft so as to be tiltable to produce vertical thrust, part only of the intake diffuser, designed for subsonic conditions, being tiltable with the unit, and the forward part of the diffuser, designed for supersonic conditions, being fixedly mounted to the airframe. Fig. 1 shows a unit buried in a wing having fixed frame parts 17, 171, and 21. Frame parts 16 16<SP>1</SP>, are tiltable with the unit about an axis 25. A flap 23 is pivoted at the wing trailing edge. The axes 27, 28, and 29 of the turbine assembly, afterburner, and nozzle respectively, incline progressively downwardly in rearward succession, so that in the normal position (full lines) some vertical thrust is produced (more than half the lift with a high angle of incidence), and the angle through which the unit must be swung to produce a large vertical force is reduced. In the tilted position (chain lines), the part 15 of the diffuser fixed to the unit is suitable for low speed operation, e.g. during landing or take off. A gap 24 is formed by flap 23, through which air is sucked by the ejector effect of the nozzle exhaust, to remove the boundary layer from the wing and provide a cooling air flow between the flap and the exhaust gases. In the normal position, gaps 22 are formed between parts 16 and 21, through which an airflow is similarly induced for removal of the boundary layer and cooling of parts 21. Fig. 2 shows the installation of two pairs of units in wing parts extending between a central and two side fuselages. The components 17, 18, 19 of the supersonic intake extend laterally to serve a pair of units and are swept back.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE860497X | 1958-05-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB860497A true GB860497A (en) | 1961-02-08 |
Family
ID=6792030
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB14953/59A Expired GB860497A (en) | 1958-05-02 | 1959-05-01 | Improvements relating to turbo-jet propulsion units in aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB860497A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3169728A (en) * | 1959-10-20 | 1965-02-16 | Messerschmitt Ag | Intake for jet propulsion units, more particularly for aircraft |
GB2209314A (en) * | 1987-09-02 | 1989-05-10 | Manuel Munoz Saiz | Lifting arrangement by direct thrust of the engine flow to vertical take-off aircraft |
US5004187A (en) * | 1988-08-04 | 1991-04-02 | Office National D'etudes Et De Recherches Aerospatiales | Symmetrical, two dimensional, supersonic and hypersonic air intake for the combustion air of an aircraft engine |
GB2250060A (en) * | 1990-11-16 | 1992-05-27 | Rolls Royce Plc | Gas turbine engine nacelle |
FR3073493A1 (en) * | 2017-11-12 | 2019-05-17 | Michel Aguilar | MULTIPLIER DEVICE FOR PUSHING |
-
1959
- 1959-05-01 GB GB14953/59A patent/GB860497A/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3169728A (en) * | 1959-10-20 | 1965-02-16 | Messerschmitt Ag | Intake for jet propulsion units, more particularly for aircraft |
GB2209314A (en) * | 1987-09-02 | 1989-05-10 | Manuel Munoz Saiz | Lifting arrangement by direct thrust of the engine flow to vertical take-off aircraft |
US5004187A (en) * | 1988-08-04 | 1991-04-02 | Office National D'etudes Et De Recherches Aerospatiales | Symmetrical, two dimensional, supersonic and hypersonic air intake for the combustion air of an aircraft engine |
GB2250060A (en) * | 1990-11-16 | 1992-05-27 | Rolls Royce Plc | Gas turbine engine nacelle |
GB2250060B (en) * | 1990-11-16 | 1995-03-01 | Rolls Royce Plc | Engine nacelle |
FR3073493A1 (en) * | 2017-11-12 | 2019-05-17 | Michel Aguilar | MULTIPLIER DEVICE FOR PUSHING |
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