Vertical takeoff and landing aircraft using a redundant array of independent rotors

• US 20060266881A1
• Filed: 01/04/2006
• Published: 11/30/2006
• Est. Priority Date: 01/14/2005
• Status: Active Grant

• Current Assignee: Hughey Electricopter Corporation
• Original Assignee: Hughey Electricopter Corporation
• Inventors: Hughey, Bradley Ward
• Granted Patent: US 7,699,260 B2
• Time in Patent Office: Days
• US Class Current: 244/17.230
• CPC Class Codes: B64C 27/08 with two or more rotors
• CPC Class Codes: B64C 31/028 Hang-glider-type aircraft; Microlight-type aircraft

Abstract

A vertical takeoff and landing aircraft, using for vertical lift and lateral thrust a redundant plurality of essentially similar electrically-powered and electronically-controlled thrust units mounted in a mechanically static or fixed fashion relative to one another in a substantially horizontal plane. The thrust units are situated in this planar array in aerodynamically approximate pairs, such that a complete failure of a single thrust unit would not substantially compromise the ability of the aircraft to maintain flight.

Claims

1. A vertical take off and landing aircraft using a vertical lifting and directional control means comprising:

six or more substantially similar independent electrically powered thrusting means;

means for mechanically joining said independent electric powered thrusting means in fixed positions relative to one another and spaced apart in an approximate geometric plane with a common thrust vector direction substantially perpendicular to said approximate geometric plane;

thrust magnitude control means whereby the individual or collective magnitude of thrust from said independent electrically powered thrusting means can be altered during operation of said vertical take off and landing aircraft;

means of attaching a payload carrying means whereby the center of mass of said payload-carrying means is substantially near the center of said approximate geometric plane.

2. The vertical take off and landing aircraft of claim 1 wherein said thrust magnitude control means incorporates a variable voltage control means.

3. The vertical take off and landing aircraft of claim 1 wherein electrical power for said independent electrically powered thrusting means is provided by an internal combustion engine to electrical power conversion means.

4. The vertical take off and landing aircraft of claim 1 wherein electrical power for said independent electrically powered thrusting means is provided by electrical energy storage means.

5. The vertical take off and landing aircraft of claim 1 wherein said thrust magnitude control means incorporates an analog or digital computer means.

6. The vertical take off and landing aircraft of claim 1 wherein the thrust vector direction of one or more of said independent electrically powered thrusting means is oriented within said approximate geometric plane at a different angle with respect to one or more of the other said independent electrically powered thrusting means to provide a yaw control means.

7. A vertical take off and landing aircraft using a redundant array of independent rotors comprising:

six or more substantially similar independent electrically powered thrusting means wherein said independent thrusting means incorporate rotational air movement means;

means for mechanically joining said independent electric powered thrusting means in fixed positions relative to one another and spaced apart in an approximate geometric plane with a common thrust vector direction substantially perpendicular to said approximate geometric plane;

thrust magnitude control means whereby the individual or collective magnitude of thrust from said independent electrically powered thrusting means can be altered during operation of said vertical take off and landing aircraft and wherein said thrust magnitude control means incorporates an analog or digital computer means;

means of attaching a payload carrying means whereby the center of mass of said payload-carrying means is substantially near the center of said approximate geometric plane.

8. The vertical take off and landing aircraft of claim 7 wherein said rotational air movement means (rotor) disk areas overlap.

9. The vertical take off and landing aircraft of claim 7 wherein one or more of said rotational air movement means incorporate an aerodynamic shrouding or ducting means.

10. The vertical take off and landing aircraft of claim 7 wherein said thrust magnitude control means incorporates a variable pitch control means within said rotational air movement means.

11. The vertical take off and landing aircraft of claim 7 wherein the thrust vector direction of one or more of said independent electrically powered thrusting means is oriented within said approximate geometric plane at a different angle with respect to one or more of the other said independent electrically powered thrusting means to provide a yaw control means.

12. The vertical take off and landing aircraft of claim 7 wherein said thrust modules incorporate more than one said rotational air movement means, such as in but not limited to a coaxial mounting configuration.