GB931251A - Improvements in or relating to jet-propelled aircraft - Google Patents
Improvements in or relating to jet-propelled aircraftInfo
- Publication number
- GB931251A GB931251A GB12744/60A GB1274460A GB931251A GB 931251 A GB931251 A GB 931251A GB 12744/60 A GB12744/60 A GB 12744/60A GB 1274460 A GB1274460 A GB 1274460A GB 931251 A GB931251 A GB 931251A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft
- landing
- thrust
- take
- during
- 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
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
- Retarders (AREA)
- Control Of Turbines (AREA)
Abstract
931,251. Aircraft. JUNKERS FLUGZEUG-UND MOTORENWERKE A.G. April 11, 1960 [May 2, 1959], No. 12744/60. Class 4. A jet propelled aircraft for short take-off and landing has delta wings 2 shaped so that maximum aerodynamic lift occurs at a maximum angle of incidence, a wing loading which does not exceed 350 kg/m<SP>2</SP>, engines 3, 4 which have thrust nozzles inclined so that the thrust passes through the centre of gravity of the aircraft and is at least equal to the weight of the fully laden aircraft, the vertical component of thrust during take-off and landing being capable of supporting at least half the weight of the aircraft, an undercarriage 5, 6, 7 which enables the aircraft to assume positions on the ground in which the longitudinal axis of the aircraft is substantially horizontal during initial stage of take-off and final stage of landing or is steeply inclined as during the final take off period or initially during landing, a control arrangement comprising adjustable jet nozzles 8, 9 which may be coupled to aerodynamic control surfaces, whereby the aircraft may be tilted from one attitude to the other and a braking device e.g. a parachute 15 capable of absorbing the thrust of the engines during landing. The nozzles 8, 9 which may be operated differentially for control purposes may also act as supplementary propulsion devices.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEJ0016369 | 1959-05-02 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB931251A true GB931251A (en) | 1963-07-17 |
Family
ID=7199484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB12744/60A Expired GB931251A (en) | 1959-05-02 | 1960-04-11 | Improvements in or relating to jet-propelled aircraft |
Country Status (2)
| Country | Link |
|---|---|
| BE (1) | BE584539A (en) |
| GB (1) | GB931251A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2164612A (en) * | 1979-09-10 | 1986-03-26 | British Aerospace | Vehicles fitted with thrust vector control systems |
-
1959
- 1959-11-12 BE BE584539A patent/BE584539A/en unknown
-
1960
- 1960-04-11 GB GB12744/60A patent/GB931251A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2164612A (en) * | 1979-09-10 | 1986-03-26 | British Aerospace | Vehicles fitted with thrust vector control systems |
Also Published As
| Publication number | Publication date |
|---|---|
| BE584539A (en) | 1960-03-01 |
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