US3583660A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Lift and control augmenter for airfoils
Assignee: Lockheed Martin Corp
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Filing: 1969-08-18
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Granted: 1971-06-08
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Expires: 1989-08-18
Abstract
Abstract Means is herein provided for augmenting the lift and controllability of an aircraft by blowing compressed air through spanwise slots in a multiple trailing edge flap system on the aircraft''s airfoils. The mechanism consists of a main flap, with rotary and translation motion relative to the associated airfoil; a lower surface flap which is hinged to both the airfoil and the main flap; and an airflow directional control device rotatably mounted to the aft end of the main flap. Downward deflection of the flap mechanism creates a spanwise duct between the main and lower surface flaps, through which compressed air, extracted from a suitable source, is allowed to flow. The air is ejected at high velocity from multiple spanwise slots provided in the flap mechanism. The resultant jet sheets impart a downward momentum to the air passing over the associated airfoil increasing the circulating flow around its chordwise sections and imparting an upward reaction. The airflow directional control device may be utilized both to vary lift symmetrically on the aircraft and to provide roll control by differential action.
Inventors
- 👤 Charles H Hurkamp
- 👤 Willi F Jacobs
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 16:51
CPC Classifications
B; B64; B64C; B64C9/00; B64C9/14; B64C9/146; B64C21/00; B64C21/02; B64C21/04; B64C9/38; B64C2230/00; B64C2230/04; B64C2230/06; B64C2230/16; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
248 words
A lift and control augmenter for an airfoil of an aircraft comprising: a fluid-conveying duct mounted internally of said airfoil; an articulated flap mechanism pivotally connected to the aft end of said airfoil and formed by hinged flap elements defining an internal fluid chamber communicating with said airfoil duct, said flap mechanism including a main flap, a pivotal and translational connection between said main flap and said airfoil, an upper and lower flap element hinged at one end at and along the aft end of said airfoil and adapted to overlie and define at least a portion of the exterior upper and lower surfaces respectively of said main flap, and an actuator between said airfoil and each said upper and lower flap element operative to deflect the latter relative to the former and concurrently move said main flap rearwardly along a path determined and described by said pivotal and translational connection; a first fluid outlet from said chamber at and along the upper surface of said flap mechanism medially of the aft end thereof and the aft end of said airfoil; a second fluid outlet adjacent the aft end of said flap mechanism, said first and second outlets being in a relatively closed position when said flap mechanism is disposeD in its undeflected position relative to said airfoil; and means to locate said outlets in a relatively open position and to regulate the effective transverse dimension of said second outlet concurrently with the deflection of said flap mechanism.
Claim 2
Dependent Claim
248 words
A lift and control augmenter for an airfoil of an aircraft comprising: a fluid-conveying duct mounted internally of said airfoil; an articulated flap mechanism pivotally connected to the aft end of said airfoil and formed by hinged flap elements defining an internal fluid chamber communicating with said airfoil duct, said flap mechanism including a main flap, a pivotal and translational connection between said main flap and said airfoil, an upper and lower flap element hinged at one end at and along the aft end of said airfoil and adapted to overlie and define at least a portion of the exterior upper and lower surfaces respectively of said main flap, and an actuator between said airfoil and each said upper and lower flap element operative to deflect the latter relative to the former and concurrently move said main flap rearwardly along a path determined and described by said pivotal and translational connection; a first fluid outlet from said chamber at and along the upper surface of said flap mechanism medially of the aft end thereof and the aft end of said airfoil; a second fluid outlet adjacent the aft end of said flap mechanism, said first and second outlets being in a relatively closed position when said flap mechanism is disposeD in its undeflected position relative to said airfoil; and means to locate said outlets in a relatively open position and to regulate the effective transverse dimension of said second outlet concurrently with the deflection of said flap mechanism.
Claim 3
Dependent Claim
24 words
The augmenter of claim 1 including a control associated with said second outlet to vary the direction thereof angularly relative to said flap mechanism.
Claim 4
Dependent Claim
35 words
The augmenter of claim 1 wherein said pivotal and translational connection includes an arcuate slot in said main flap, and a roller connected to and carried by said airfoil in constant engagement with said slot.
Claim 5
Dependent Claim
55 words
The augmenter of claim 1 wherein said pivotal and translational connection includes a lever pivotally connected at one end to the forward end of said main flap and at the other end to a fixed point relative to said airfoil aft of said forward main flap end when said flap mechanism is undeflected as aforesaid.
Claim 6
Dependent Claim
43 words
The augmenter of claim 4 wherein said lever is one arm of a bellcrank, the other arm of which is pivotally connected to a link pivotally connected in turn at its other end to said lower flap element aft of said fixed point.
Claim 7
Dependent Claim
27 words
The augmenter of claim 1 including an auxiliary flap at the aft end of said main flap mounted for rotation thereon to and from various deflected positions.
Claim 8
Dependent Claim
77 words
The augmenter of claim 6 wherein said auxiliary flap is rotatably mounted at the aft end of said main flap with its opposite surfaces disposed in the plane of the corresponding surfaces of the upper and lower flaps when in the neutral position, and said second outlet is disposed in a predetermined position about said auxiliary flap so as to discharge fluid when operative in preselected quantities adjacent the upper and lower surfaces of said auxiliary flap.
Claim 9
Dependent Claim
32 words
The augmenter of claim 6 wherein said auxiliary flap is rotatably mounted at the aft end of said main flap and is pierced by a passage in communication with said fluid chamber.
Claim 10
Dependent Claim
33 words
The augmenter of claim 7 wherein said quantity of fluid discharged adjacent the upper surface of said auxiliary flap is appreciably less than that discharged adjacent the lower surface of said auxiliary flap.
Claim 11
Dependent Claim
34 words
The invention of claim 1 wherein said airfoil is a fixed wing on each side of the fuselage of the aircraft and one said lift and control augmenter is associated with each said wing.
References Cited (Backward Citations)
US3188021A
Cited
US3361386A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-06-07 | 1974-12-07 | 1975-06-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-06-07 | 1978-12-07 | 1979-06-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-06-07 | 1982-12-07 | 1983-06-08 | $7700.00 | Window Closed / Lapsed |