Vertical/short take-off and landing (V/STOL) air vehicle capable of providing high speed horizontal flight

• US 5,758,844 A
• Filed: 05/28/1996
• Issued: 06/02/1998
• Est. Priority Date: 05/28/1996
• Status: Expired due to Term

• Current Assignee: Boeing North American Incorporated (The Boeing Co.)
• Original Assignee: Boeing North American Incorporated (The Boeing Co.)
• Inventors: Cummings, Darold B.
• Primary Examiner(s): GRANT, WILLIAM ALEXANDER
• Application Number:
  US08/654,133
• Time in Patent Office: 735 Days
• Field of Search: 244/7 C, 244/12.1, 244/12.4, 244/48, 244/52, 244/56, 244/66
• US Class Current: 244/7.00C
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage

Abstract

The vehicle includes a fuselage; a plurality of lifting surfaces attached to the fuselage having control devices attached thereto; and, an articulated propulsion system attached to the fuselage. The propulsion system includes a duct assembly pivotally connected to the fuselage. The duct assembly includes a duct and a propeller assembly mounted within the duct. A motor assembly is connected to the propeller assembly. The duct assembly may be positioned in a substantially vertical position to provide sufficient direct vertical thrust for vertical take-off and landing and may be directed in other positions to provide a varying spectrum of take-off and landing configurations, as well as a substantially horizontal position for high speed horizontal flight. Use of the control surface in the ducted propulsion assembly provides VTOL capability in a very small environment. The environment is not required to be prepared in any special manner. During horizontal flight, the wings provide the lift, which is more efficient than a propeller providing lift. The present invention takes advantage of a center line propulsion, so that there are no asymmetric propulsion loads.

Claims

1. A vertical/short take-off and landing air vehicle capable of producing high speed horizontal flight, comprising:

a) a fuselage;

b) a plurality of lifting surfaces, including at least one wing and at least one all moving horizontal tail, attached to said fuselage, each said at least one wing having a respective control device attached thereto;

c) an articulated propulsion system attached to said fuselage, comprising;

I) a duct assembly pivotally connected to said fuselage, said duct assembly comprising;

a duct; and

a propeller assembly mounted within said duct; and

ii) a motor assembly connected to said propeller assembly,

wherein said propulsion system is positionable in a substantially vertical position to provide sufficient direct vertical thrust for vertical take-off and landing and is directable to other positions to provide a varying spectrum of take-off and landing configurations as well as a substantially horizontal position for high speed horizontal flight and wherein each of said plurality of lifting surfaces pivots with respect to the fuselage to remain generally aligned with a longitudinal central axis of the duct assembly as the propulsion system is positioned in and between the substantially vertical position and the substantially horizontal position.

2. The air vehicle of claim 1, wherein said air vehicle defines a longitudinal center line and said fuselage has a longitudinal central axis,

wherein during substantially horizontal flight, said longitudinal central axes of said fuselage and said duct assembly are collinear with said longitudinal center line of said air vehicle;

and

wherein during substantially vertical flight, said duct assembly is rotatable to a position such that said longitudinal central axis of the duct assembly is substantially perpendicular to said longitudinal central axis of said fuselage and said longitudinal center line of said air vehicle.

3. The air vehicle of claim 1, wherein said duct, comprises:

a hollow cylindrical housing;

a plurality of fixed vanes, each vane being attached on an outer end to said housing and at an inner end to said motor assembly; and

a plurality of guide vanes attached to downstream portions of said fixed vanes for controlling said vehicle in a substantially vertical flight mode.

4. The air vehicle of claim 1, further comprising:

a pair of symmetrically positioned longitudinal booms, each boom being positioned on a respective side of said fuselage, said plurality of lifting surfaces being attached to said booms;

a plurality of directional control surfaces connected to said booms; and

landing gear extending from said booms.

5. The air vehicle of claim 1, further comprising:

a hydraulic actuator extending between said fuselage and said duct assembly, for positioning said propulsion system in and between the substantially vertical position and the substantially horizontal position.

6. The air vehicle of claim 1, further comprising:

a pair of longitudinal booms, said booms being positioned laterally outward from and on opposite sides of said fuselage;

each of said plurality of lifting surfaces being attached to at least one of said booms by a respective rotating shaft;

a pair of directional control surfaces each being connected to a respective one of said booms, and each directional control surface including a rudder and a vertical stabilizer.

7. The air vehicle of claim 6, further comprising:

a pair of retractable nose gear each extending from a respective one of said booms.