US20060202083A1
Expired / Lapsed
US
⏱️ 0.0 years remaining
VTOL personal aircraft
Assignee: Individual
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Filing: 2006-01-05
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Granted: —
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Expires: 2026-01-05
Abstract
Abstract A vertical take-off and landing (VTOL) aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. According to the invention, means are provided for increasing the speed of an airstream flowing over the upper surface of each wing, and an air deflector is disposed on each side of the fuselage between the trailing edge of each wing and the aircraft tail. These deflectors each have a deflection surface to deflect downward the airstream flowing over the upper surface of the wing to act as a “brake” to the forward motion of the aircraft and to provide additional lift so that the aircraft may hover.
Inventors
- 👤 Karl Milde
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 09:33
CPC Classifications
B; B64; B64C; B64C5/00; B64C5/10; B64C5/16; B64C23/00; B64C23/02; B64C29/00; B64C29/0008; B64C29/0016; B64C29/0025; B64C29/0041; B64C29/0066; B64C3/00; B64C3/38; B64C3/385; B64C39/00; B64C39/003; B64C39/005; B64C39/06; B64C39/066; B64C9/00; B64C9/32
Claims Analysis
Total Claims: 17
Claim 1
Independent Claim
165 words
1 . A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect downward the airstream flowing over the upper surface of the wing.
Claim 2
Dependent Claim
165 words
1 . A vertical take-off and landing (VTOL) aircraft comprising, in combination: (a) a fuselage having a front end, a rear end and two lateral sides, said fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (b) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage, said rudder and elevator having movable surfaces for control of the aircraft; (c) a wing on each side of the fuselage, each wing having a front edge, a rear edge and an upper surface extending from the front edge to the rear edge thereof; (d) means for increasing the speed of an airstream flowing over the upper surface of each wing; and (e) an air deflector disposed on each side of the fuselage between the rear edge of each wing and the aircraft tail and having a deflection surface to deflect downward the airstream flowing over the upper surface of the wing.
Claim 3
Dependent Claim
38 words
2 . The aircraft defined in claim 1 , wherein said deflector is retractable into and out of the fuselage, said deflector being movable between a first position within the fuselage and a second position within the airstream.
Claim 4
Dependent Claim
51 words
3 . The aircraft defined in claim 1 , wherein said deflection surface is rotatable about an axis perpendicular to said central longitudinal axis, said deflection surface being rotatable between a first position in which said airstream is minimally deflected and a second position in which the airstream is maximally deflected.
Claim 5
Dependent Claim
27 words
4 . The aircraft defined in claim 3 , wherein said deflection surface is arranged substantially parallel to the central longitudinal axis when in the first position.
Claim 6
Dependent Claim
29 words
5 . The aircraft defined in claim 3 , wherein said deflection surface is arranged at a substantial angle to the central longitudinal axis when in the second position.
Claim 7
Dependent Claim
30 words
6 . The aircraft defined in claim 1 , wherein the deflection surface has a shape selected from the group consisting of substantially planar and curved in a horizontal arc.
Claim 8
Dependent Claim
25 words
7 . The aircraft defined in claim 1 , wherein said airstream is deflected in both a downward and rearward direction by the deflection surface.
Claim 9
Dependent Claim
25 words
8 . The aircraft defined in claim 1 , wherein said airstream is deflected in both a downward and forward direction by the deflection surface.
Claim 10
Dependent Claim
20 words
9 . The aircraft defined in claim 8 , wherein the deflector has a curved surface for deflecting the airstream.
Claim 11
Dependent Claim
116 words
10 . The aircraft recited in claim 1 , wherein each wing has a channel extending from the front edge to the rear edge thereof and defining a channel axis aligned substantially in parallel with said central longitudinal axis of the aircraft, and wherein said means for increasing the speed of the airstream flowing over said upper surface of each wing comprises a propeller arranged to rotate in a plane substantially perpendicular to said central longitudinal axis and about an axis substantially parallel to the channel axis of its associated wing, the plane of rotation of each propeller being substantially adjacent to the rear edge of the wing and the respective channel of its associated wing.
Claim 12
Dependent Claim
49 words
11 . The aircraft recited in claim 1 , wherein said means for increasing the speed of the airstream flowing over the upper surface of each wing comprises a plurality of fan blades mounted on and affixed to rotatable shaft that extends substantially perpendicular to the central longitudinal axis.
Claim 13
Dependent Claim
59 words
12 . The aircraft defined in claim 11 , wherein said means for increasing the speed of the airstream flowing over the upper surface of each wing further comprises a guide member, disposed substantially parallel to said upper surface and adjacent the fan blades, for restricting the airstream to flow in a direction substantially parallel to said upper surface.
Claim 14
Dependent Claim
19 words
13 . The aircraft defined in claim 11 , wherein each rotatable shaft is disposed within its associated wing.
Claim 15
Dependent Claim
23 words
14 . The aircraft defined in claim 11 , wherein each rotatable shaft is disposed above the upper surface of its associated wing.
Claim 16
Dependent Claim
39 words
15 . The aircraft defined in claim 14 , wherein each rotatable shaft and its associated fan blades are disposed, in part, in a shroud which covers the blades as they move in the forward direction of the aircraft.
Claim 17
Dependent Claim
29 words
16 . The aircraft defined in claim 11 , wherein each shaft and its associated fan blades are rotated by at least one prime mover arranged in the fuselage.
References Cited (Backward Citations)
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