IN-FLIGHT RECONFIGURABLE AIRCRAFT TAIL

• US 20170190412A1
• Filed: 05/20/2015
• Published: 07/06/2017
• Est. Priority Date: 05/20/2014
• Status: Active Application

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Bunting, Colin Kemater, Strauss, Michael Peter
• Granted Patent: US 10,279,903 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 1/30 Parts of fuselage relatively movable to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64D 45/04 Landing aids; Safety measures to prevent collision with earth's surface

Abstract

A system and method for a reconfigurable aircraft having a fuselage with one or more propellers, at least one tail assembly, a processor, and a memory having instructions stored thereon that, when executed by the processor, cause the system to: determine a safety clearance for the at least one tail assembly; and selectively move the at least one tail assembly upon a determination that the safety clearance is achieved.

Claims

1. A system for a reconfigurable aircraft, comprising

a fuselage having one or more propellers;

at least one tail assembly;

a processor; and

memory having instructions stored thereon that, when executed by the processor, cause the system to;

determine a safety clearance for the at least one tail assembly; and

selectively move the at least one tail assembly upon a determination that the safety clearance is achieved.

2. The system of claim 1, wherein the at least one tail assembly includes a first portion that is coupled to a second portion.

3. The system of claim 2, wherein the processor is configured to selectively move the second portion from a retracted position to an extended position.

4. The system of claim 2, wherein the second portion is attached to the first portion in the extended position.

5. The system of claim 2 wherein the second portion is substantially orthogonal to the first portion in a retracted position.

6. The system of any preceding claim, further comprising respective strut and linkages coupled to the at least one tail assembly.

7. The system of any preceding claim, wherein the at least one tail assembly is coupled to a wing portion of the aircraft.

11. The method of any of the preceding claims, further comprising providing the at least one tail assembly with a first portion that is coupled to a second portion.

12. The method of claim 11, further comprising selectively moving the second portion from a retracted position to an extended position.

13. The method of claim 11, further comprising attaching the second portion to the first portion in the extended position.

14. The method of claim 11 or 12, further comprising retracting the second portion from the first portion to be substantially orthogonal with the first portion.

15. The method of any preceding claim, further comprising coupling the at least one tail assemble to a wing portion of the aircraft.

8. A method for controlling a reconfigurable aircraft, comprising:

receiving, with a processor, one or more signals indicative of position of the aircraft with the ground;

determining, with the processor, information indicative of a safety clearance for at least one tail assembly; and

selectively moving the at least one tail assembly upon a determination that the safety clearance is achieved.

9. The method of claim 8, further comprising receiving sensor information indicative of weight of the vehicle on a plurality of landing gears.

10. The method of claim 9, further comprising receiving sensor information for a strut and linkages coupled to the at least one tail assembly.