Modular flight vehicle with wings

• US 8,646,720 B2
• Filed: 05/10/2011
• Issued: 02/11/2014
• Est. Priority Date: 05/10/2010
• Status: Expired due to Fees

• Current Assignee: Donald Orval Shaw
• Original Assignee: Donald Orval Shaw
• Inventors: Shaw, Donald Orval
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Hawk, Steven
• Application Number:
  US13/104,969
• Publication Number:
  US 20120119016A1
• Time in Patent Office: 1,008 Days
• Field of Search: 244/7.R, 244/7.C, 244/17.23, 244/17.27
• US Class Current: 244/17.23
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 60/40 foldable or retractable
• CPC Class Codes: B64U 70/50 Launching from storage containers, e.g. from submarine missile tubes
• CPC Class Codes: B64U 70/90 Launching from or landing on platforms

Abstract

The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. The propellers are mounted on supports which have an airfoil shape to generate additional lift. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe.

Claims

1. A flight vehicle, comprising:

a main airframe, the airframe defining an airframe horizontal plane and having an airframe front, airframe back, airframe left side, and airframe right side;

at least four propeller supports extending from the main airframe, wherein each propeller support comprises a proximal end, a distal end, and an elongated main support body between the proximal end and the distal end, wherein the elongated main support body comprises a longitudinal axis, wherein the proximal end is secured to the main airframe and the elongated main support extends sideways from the main airframe, wherein at least two propeller supports are positioned with the distal ends thereof to the left of the airframe left side, and at least two propeller supports are positioned with the distal ends thereof to the right of the airframe right side;

at least four propellers, wherein at least one of the four propellers is positioned at the distal end of each propeller support;

at least four movable airfoils, each airfoil comprising a leading edge, a trailing edge, a span, and a chord line, wherein at least one of the four movable airfoils is positioned on a corresponding propeller support of the at least four propeller supports, wherein the span of each movable airfoil is positioned substantially parallel to the longitudinal axis of the elongated main support body of the corresponding propeller support, and wherein the movable airfoil is configured to be rotated about an airfoil rotational axis, wherein the airfoil rotational axis is substantially parallel to the longitudinal axis of the elongated main support body, wherein each movable airfoil is configured to rotate from a first position wherein the chord line is substantially perpendicular to the airframe horizontal plane and the trailing edge is positioned below the leading edge, to a second position wherein the chord line is substantially parallel to the airframe horizontal plane and the trailing edge is positioned behind the leading edge, wherein each airfoil is a free wing that is freely rotatable about the airfoil rotational axis and has an angle of attack determined solely by aerodynamic forces acting on the airfoil.

2. The flight vehicle of claim 1, wherein each airfoil is freely rotatable responsive to aerodynamic forces through at least 30 degrees about the airfoil rotational axis.

3. The flight vehicle of claim 2, wherein each airfoil is freely rotatable responsive to aerodynamic forces through at least 90 degrees about the airfoil rotational axis.

4. The flight vehicle of claim 3, wherein each airfoil is freely rotatable responsive to aerodynamic forces through multiple rotations about the airfoil rotational axis.

5. The flight vehicle of claim 1, wherein each airfoil is a generally symmetrical airfoil.

6. The flight vehicle of claim 1, wherein each airfoil defines a thickness and a chord length, wherein the airfoil maximum thickness is at least 25 percent of the airfoil chord length.

7. A method of operating an air vehicle, comprising:

providing an air vehicle comprising;

a main airframe, the airframe defining an airframe horizontal plane and having an airframe front, airframe back, airframe left side, and airframe right side;

at least four propeller supports extending from the main airframe, wherein each propeller support comprises a proximal end, a distal end, and an elongated main support body between the proximal end and the distal end, wherein the elongated main support body comprises a longitudinal axis, wherein the proximal end is secured to the main airframe and the elongated main support extends sideways from the main airframe, wherein at least two propeller supports are positioned with the distal ends thereof to the left of the airframe left side, and at least two propeller supports are positioned with the distal ends thereof to the right of the airframe right side;

at least four propellers, wherein at least one of the four propellers is positioned at the distal end of each propeller support;

at least four movable airfoils, each airfoil comprising a leading edge, a trailing edge, a span, and a chord line, wherein at least one of the four movable airfoils is positioned on a corresponding propeller support of the at least four propeller supports, wherein the span of each movable airfoil is positioned substantially parallel to the longitudinal axis of the elongated main support body of the corresponding propeller support, and wherein the movable airfoil is configured to be rotated about an airfoil rotational axis, wherein the airfoil rotational axis is substantially parallel to the longitudinal axis of the elongated main support body, wherein each movable airfoil is configured to rotate from a vertical flight position wherein the chord line is substantially perpendicular to the airframe horizontal plane and the trailing edge is positioned below the leading edge, to a forward flight position wherein the chord line is substantially parallel to the airframe horizontal plane and the trailing edge is positioned behind the leading edge, wherein each airfoil is a free wing that is freely rotatable about the airfoil rotational axis and has an angle of attack determined solely by aerodynamic forces acting on the airfoil;

positioning the air vehicle on a takeoff surface;

positioning each movable airfoil in the vertical flight position; and

rotating the propellers to generate sufficient propeller thrust to lift the vehicle substantially vertically off the takeoff surface, whereby the vehicle lifts from the takeoff surface.

8. The method of claim 7, wherein positioning each movable airfoil in the vertical flight position comprises rotating the propellers to generate sufficient airflow to cause each movable airfoil to rotate to the takeoff position.

9. The method of claim 7, further comprising:

rotating one or more of the movable airfoils to control the position of the air vehicle.

10. The method of claim 7, wherein the air vehicle comprises a horizontal thrust generator configured to provide horizontal thrust, wherein the method further comprises:

activating the horizontal thrust generator to provide horizontal thrust in a forward direction; and

positioning each movable airfoil in the forward flight position.

11. The method of claim 10, further comprising:

rotating one or more of the movable airfoils to control the direction of the air vehicle.

12. The method of claim 10, wherein at least one of the propellers is a tilting propeller configured to be tilted forward or backward with respect to the air vehicle horizontal plane, wherein the horizontal thrust generator comprises the tilting propeller, wherein activating the horizontal thrust generator comprises tilting the tilting propeller forward with respect to the air vehicle horizontal axis.

13. The method of claim 7, wherein each movable airfoil is configured to be rotated to a STOL (short takeoff and landing) position wherein the trailing edge is below and behind the leading edge and the chord line is at an angle between 15 and 75 degrees from the air vehicle horizontal plane, the method comprising:

positioning the air vehicle on the takeoff surface;

positioning each movable airfoil in the STOL position; and

rotating the propellers to generate sufficient propeller thrust to move the air vehicle forward and into the air.

14. The method of claim 13, wherein at least two of the propellers are tilting propellers configured to be positioned with a forward tilt angle of at least 15 degrees with respect to the air vehicle horizontal plane, wherein the method comprises:

positioning the tilting propellers with a forward tilt angle of at least 15 degrees with respect to the air vehicle horizontal plane.

15. A modular vehicle, comprising:

A flight vehicle module, comprising;

a main airframe, the airframe defining an airframe horizontal plane and having an airframe front, airframe back, airframe left side, and airframe right side;

a plurality of propeller supports extending from the main airframe, wherein each propeller support comprises a proximal end, a distal end, and a generally straight elongated main support body between the proximal end and the distal end, wherein the elongated main support body comprises a support body longitudinal axis, wherein the proximal end is secured to the main airframe and the elongated main support extends sideways from the main airframe, wherein at least one propeller support is positioned with the distal end thereof to the left of the airframe left side, and at least one propeller support is positioned with the distal end thereof to the right of the airframe right side, wherein each of the plurality of propeller supports is configured to rotate about a support rotational axis, wherein the support rotational axis is substantially perpendicular to the airframe horizontal plane, wherein each of the plurality of propeller supports can be rotated from a stowed position wherein the distal end thereof is substantially adjacent the airframe to a deployed position wherein the distal end thereof is substantially displaced sideways from the airframe;

a plurality of propellers, wherein at least one of the plurality of propellers is positioned at the distal end of each propeller support;

a plurality of movable airfoils, each airfoil comprising a leading edge, a trailing edge, a span, and a chord line, wherein at least one of the plurality of movable airfoils is positioned on a corresponding propeller support of the plurality of propeller supports, wherein the span of each movable airfoil is positioned substantially parallel to the longitudinal axis of the elongated main support body of the corresponding propeller support, and wherein the movable airfoil is configured to be rotated about an airfoil rotational axis, wherein the airfoil rotational axis is substantially parallel to the longitudinal axis of the elongated main support body, wherein each movable airfoil is configured to rotate from a first position wherein the chord line is substantially non-parallel to the airframe horizontal plane and the trailing edge is positioned below the leading edge, to a second position wherein the chord line is substantially parallel to the airframe horizontal plane and the trailing edge is positioned behind the leading edge, wherein each airfoil comprises a proximal end closest to the airframe and a distal end furthest from the airframe, wherein each airfoil angles upward with respect to the airframe from the proximal end to the distal end, wherein each airfoil is a free wing that is freely rotatable about the airfoil rotational axis and has an angle of attack determined solely by aerodynamic forces acting on the airfoil; and

a ground vehicle module, comprising a main ground vehicle body and a plurality of wheels, wherein the ground vehicle module is detachable from the flight module, and the ground vehicle module is configured to be driven on the ground separately from the flight vehicle module.

16. The modular vehicle of claim 15, wherein each airfoil has a center of lift, and the airfoil rotational axis is positioned substantially at the airfoil center of lift.

17. The modular vehicle of claim 15, the vehicle flight module further comprising:

at least one actuator controlling the rotational position of each airfoil.

18. The modular vehicle of claim 15, wherein each airfoil is weighted such that in the absence of airflow the airfoil will rotate responsive to gravity to the first position wherein the chord line is substantially non-parallel to the airframe horizontal plane and the trailing edge is positioned below the leading edge.

19. The modular vehicle of claim 15, wherein the air vehicle module comprises landing supports with sufficient height to permit the ground vehicle module to be driven under the main airframe of the air vehicle module when the air vehicle module is resting on the ground and supported by the landing supports.