Compound wing vertical takeoff and landing small unmanned aircraft system

Patent metadata

Field	Value
Publication number	US-9708059-B2
Application number	US-201514625806-A
Country	US
Kind code	B2
Filing date	Feb 19, 2015
Priority date	Feb 19, 2014
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

Systems, methods, and devices are provided that enable robust operations of a small unmanned aircraft system (sUAS) using a compound wing. The various embodiments may provide a sUAS with vertical takeoff and landing capability, long endurance, and the capability to operate in adverse environmental conditions. In the various embodiments a sUAS may include a fuselage and a compound wing comprising a fixed portion coupled to the fuselage, a wing lifting portion outboard of the fixed portion comprising a rigid cross member and a controllable articulating portion configured to rotate controllable through a range of motion from a horizontal position to a vertical position, and a freely rotating wing portion outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion.

First claim

What is claimed is:

1. A compound wing for a fuselage, comprising:
a fixed wing portion couplable to the fuselage;
a wing lifting portion coupled to and disposed outboard of the fixed wing portion, comprising:
a rigid cross member configured not to articulate; and
a single controllably articulating portion configured to rotate controllably through a range of motion from a horizontal position in line with the fixed wing portion to a vertical position perpendicular to the fixed wing portion; and

a freely rotating wing portion coupled to and disposed outboard of the wing lifting portion and configured to freely rotate based on wind forces incident on the freely rotating wing portion.

2. The compound wing of claim 1 , wherein the controllably articulating portion includes a lifting motor.

3. The compound wing of claim 2 , wherein the fixed wing portion is configured to be coupled to the fuselage of a small unmanned aircraft system (sUAS).

4. A small unmanned aircraft system (sUAS), comprising:
a fuselage; and
a compound wing, comprising:
a fixed wing portion coupled to the fuselage;
a wing lifting portion coupled to and disposed outboard of the fixed wing portion, comprising:
a rigid cross member configured not to articulate; and
a single controllably articulating portion configured to rotate controllably through a range of motion from a horizontal position in line with the fixed wing portion to a vertical position perpendicular to the fixed wing portion; and
a freely rotating wing portion coupled to and disposed outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion.

5. The sUAS of claim 4 , wherein the controllably articulating portion includes a lifting motor.

6. The sUAS of claim 5 , further comprising:
an aft propulsor configured to be articulated through a range of motion from a second horizontal position to a downward position.

7. The sUAS of claim 6 , wherein during a forward flight mode the controllably articulating portion is in the horizontal position, the aft propulsor is in the second horizontal position, and the freely rotating wing portion is free to rotate.

8. The sUAS of claim 7 , wherein during a vertical takeoff and landing (V/TOL) flight mode the controllably articulating portion is in the vertical position, the aft propulsor is in the downward position, and the freely rotating wing portion is free to rotate.

9. A small unmanned aircraft system (sUAS), comprising:
a fuselage;
independently controllable first and second lift engines or motors configured to provide vertical lift in a vertical takeoff and landing mode and forward propulsion in a forward flight mode;
an aft propulsor configured to be articulated through a range of motion from a second horizontal position to a downward position;
first and second compound wings positioned on opposite sides of the fuselage, each of the first and second compound wings including:
a fixed wing portion coupled to the fuselage;
a wing lifting portion coupled to and disposed outboard of the fixed wing portion and having:
a rigid cross member configured not to articulate; and
a single controllably articulating portion to which is mounted a different one of the first and second lift engines or motors, wherein the single controllably articulating portion is configured to rotate through a range of motion from a horizontal position in line with the fixed wing portion to a vertical position perpendicular to the fixed wing portion; and

a freely rotating wing portion coupled to and disposed outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion; and

a control system configured to control operations of the aft propulsor, the first and second lifting engines or motors, and the controllably articulating wing portions, including independently controlling the first and second lifting engines or motors.

Assignees

• Nasa
• The Us Adminstrator Of The Nat Aeronautics And Space Administration

Inventors

• Logan Michael J
• Motter Mark A
• Deloach Richard
• Vranas Thomas L
• Prendergast Joseph M
• Lipp Brittney N

Classifications

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64C39/005 Primary

  about a horizontal transversal axis · CPC title

• B64C2201/088

  Operations & Transport · mapped topic

• B64C2201/021

  Operations & Transport · mapped topic

• B64C2201/165

  Operations & Transport · mapped topic