In-flight reconfigurable aircraft tail

Patent metadata

Field	Value
Publication number	US-2017190412-A1
Application number	US-201514717778-A
Country	US
Kind code	A1
Filing date	May 20, 2015
Priority date	May 20, 2014
Publication date	Jul 6, 2017
Grant date	—

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.

First claim

What is claimed is:

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.

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.

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.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Bunting Colin Kemater
• Strauss Michael Peter

Classifications

• B64D45/04

  Landing aids; Safety measures to prevent collision with earth's surface · CPC title

• B64C5/10 Primary

  adjustable · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C29/02 Primary

  having its flight directional axis vertical when grounded · CPC title

• B64C1/30

  Parts of fuselage relatively movable to reduce overall dimensions of aircraft · CPC title