Miniature vertical takeoff and landing aircraft

• US 6,550,715 B1
• Filed: 12/07/2001
• Issued: 04/22/2003
• Est. Priority Date: 12/07/2001
• Status: Expired due to Fees

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Reynolds, John, Knutson, Eric, Wurts, Joseph, Young, Eric P.
• Primary Examiner(s): Poon, Peter M.
• Assistant Examiner(s): Collins, Timothy D
• Application Number:
  US10/005,746
• Time in Patent Office: 501 Days
• Field of Search: 244/17.11, 244/7.B, 244/12.2, 244/23.C, 244/34.A, 446/36, 446/37, 446/57
• US Class Current: 244/7.00B
• CPC Class Codes: A63H 27/12 Helicopters A63H27/04 takes precedence; Flying tops
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors

Abstract

A vertical takeoff and landing aircraft is disclosed that includes a support structure having a motor mounted vertically thereto, with the motor having a propeller for rotation in a horizontal plane. A power supply for the motor is mounted to the support structure below the motor and electrical coupled thereto. A plurality of fins are attached by their first end to the power and extending radially outward therefrom. Vertical posts have there first ends attached to the second end of the fins and extend upward to the plane of rotation of the propeller. A ring is mounted horizontally to the second ends of the plurality of vertical posts surrounding the propeller. The torque produced by the drag of fins as the aircraft rotates in the opposite direction reacting the torque of the propeller equal to the torque of the propeller necessary to achieve hover. The rotational inertia of aircraft is made equal to the rotational inertia of the propeller.

Claims

1. A vertical takeoff and landing aircraft comprising:

a support structure;

a motor mounted vertically to said support structure, said motor having a propeller for rotation in a horizontal plane;

a power supply for said motor mounted to said support structure below said motor;

a plurality of fins having first and second ends, said first ends attached to said power supply, said plurality of fins extending radially outward from said power supply and equally spaced from each other;

vertical posts having first and second ends, said first ends of said vertical posts directly attached to said second ends of said plurality of fins and extending upward;

a ring mounted horizontally to said second ends of said plurality of vertical posts in proximity to the rotational plane of and surrounding said propeller.

2. The aircraft as set forth in claim 1 wherein the torque produced by the drag of said fins opposes the torque of said propeller.

3. The aircraft as set forth in claim 2 comprising the rotational inertia of said propeller equal to the rotational inertia of the remainder of the aircraft.

4. The aircraft as set forth in claim 3 wherein there are three fins.

5. The aircraft as set forth in claim 4 wherein said motor is and electric motor.

6. The aircraft as set forth in claim 5 where in said power supply is a capacitor.

7. The aircraft as set forth in claim 6 further comprising:

an electrical plug mounted on said support structure; and

a switch mounted within said support structure, said switch for either electrical coupling said capacitor to said motor or coupling said capacitor to said plug;

such that said capacitor can be coupled to said plug for receiving a charging current or to said motor for powering same.

8. A vertical takeoff and landing aircraft having a support structure containing a motor mounted vertically to the support structure, the motor having a propeller for rotation in a horizontal plane about a vertical axis, and a power supply;

wherein the torque produced by the drag of the support structure opposes the torque of the propeller, and the aircraft achieves hover when, the torque of the propeller is substantially equivalent to the torque of the support structure comprising;

a plurality of fins having first and second ends, said first ends attached to the power supply, said plurality of fins extending radially outward from the power supply and equally spaced from each other;

vertical posts having first and second ends, said first ends of said vertical posts directly attached to said second ends of said plurality of fins and extending upward.

9. The aircraft as set forth in claim 8 comprising the rotational inertia of the propeller about the vertical axis equal to the rotational inertia of the remainder of the aircraft about the vertical axis.

10. The aircraft as set forth in claim 9 comprising:

the power supply mounted vertically below the motor;

a plurality of fins having first and second ends, said first ends attached to the power supply;

said plurality of fins extending radially outward from the power supply and equally spaced from each other;

vertical posts having first and second ends, said first ends of said vertical posts attached to said second ends of said plurality of fins and extending upward;

a ring mounted horizontally to said second ends of said plurality of vertical posts in proximity to the rotational plane of and surrounding said propeller.

11. The aircraft as set forth in 10 wherein there are three fins.

12. The aircraft as set forth in claim 11 wherein the motor is an electric motor.

13. The aircraft as set forth in claim 12 where in the power supply is a capacitor.

14. The aircraft as set forth in claim 13 further comprising:

an electrical plug mounted on said support structure; and

a switch mounted within said support structure, said switch for either electrical coupling the capacitor to the motor or coupling the capacitor to said plug;

such that the capacitor can be coupled to said plug for receiving a charging current or to the motor for powering same.