US3829044A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Engine arrangement for high performance stol aircraft
Assignee: Lockheed Martin Corp
•
Filing: 1973-03-23
•
Granted: 1974-08-13
•
Expires: 1993-03-23
Abstract
Abstract A form of power augmented high lift for aircraft mounts engine nacelles on overwing pylons. The nozzle system is a vectoring device such that the engine exhaust flow is caused to impinge on the upper surface of the flap at any flap angle. The vector device may be any of several types, such as the swivel nozzle illustrated, and is linked to the flap system to ensure optimum impingement angle on the surface providing flow attachment and a jet sheet extension to the trailing edge. In cruise the nozzle system directs the exhaust aft so that no flow interference with the wing/flap surface occurs.
Inventors
- 👤 H Leslie
- 👤 R Samways
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 22:17
CPC Classifications
B; B64; B64C; B64C29/00; B64C29/0008; B64C29/0041
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
134 words
The combination with an aircraft having a fuselage, a fixed wing extending from each side of said fuselage and a hinged flap at and along the aft end of each said wing, of at least one engine disposed on each side of said fuselage above and in spaced relation to the associated wing, and at least one rotatable exhaust nozzle from each engine, each said nozzle having an exhaust outlet located above the wing surface adjacent the hinge line of the associated flap whereby the longitudinal centerline of each said nozzle may be disposed generally parallel to the upper surface of the associated flap at all times and the exhaust discharge restricted to impingement on and against said hinge line and said upper flap surface of each flap when the flap is fully deflected.
Claim 2
Dependent Claim
134 words
The combination with an aircraft having a fuselage, a fixed wing extending from each side of said fuselage and a hinged flap at and along the aft end of each said wing, of at least one engine disposed on each side of said fuselage above and in spaced relation to the associated wing, and at least one rotatable exhaust nozzle from each engine, each said nozzle having an exhaust outlet located above the wing surface adjacent the hinge line of the associated flap whereby the longitudinal centerline of each said nozzle may be disposed generally parallel to the upper surface of the associated flap at all times and the exhaust discharge restricted to impingement on and against said hinge line and said upper flap surface of each flap when the flap is fully deflected.
Claim 3
Dependent Claim
22 words
The combination of claim 1 including a pylon carried by and extending upwardly from each wing adapted to mount each said engine.
Claim 4
Dependent Claim
23 words
The combination of claim 2 wherein the center of gravity of each engine is located substantially at the middle of the wing chord.
Claim 5
Dependent Claim
20 words
The combination of claim 1 wherein one of said exhaust nozzles is rotatably mounted on each side of said engine.
Claim 6
Dependent Claim
26 words
The combination of claim 4 including a fairing associated with each said nozzle on the upstream side thereof in the level flight mode of the aircraft.
References Cited (Backward Citations)
DE768044C
Cited
US3018983A
Cited
US3164337A
Cited
FR1272553A
Cited
US3286930A
Cited
US3599900A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-08-12 | 1978-02-11 | 1978-08-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-08-12 | 1982-02-11 | 1982-08-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-08-12 | 1986-02-11 | 1986-08-13 | $7700.00 | Window Closed / Lapsed |