Vertical take-off and landing (VTOL) aircraft with exhaust deflector

Patent metadata

Field	Value
Publication number	US-10077108-B2
Application number	US-201614987295-A
Country	US
Kind code	B2
Filing date	Jan 4, 2016
Priority date	Mar 2, 2015
Publication date	Sep 18, 2018
Grant date	Sep 18, 2018

Abstract

A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions.

First claim

What is claimed is:

1. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage with first and second wings extending outwardly from opposite sides of the fuselage;
a first nacelle having a first proprotor disposed on the first wing and a second nacelle having a second proprotor disposed on the second wing, the first nacelle having a first trailing end and the second nacelle having a second trailing end, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight;
a first alighting element extending from rearwardly from a distal end of the first wing and a second alighting element extending rearwardly from a distal end of the second wing, the first and second alighting elements being disposed to support the aircraft in a ground operational condition; and
a first plurality of exhaust deflectors pivotally mounted to the first trailing end and a second plurality of exhaust deflectors mounted to the second trailing end, each of the first plurality of exhaust deflectors and the second plurality of exhaust deflectors being disposed to assume at least a first configuration, a second configuration, and a third configuration associated with corresponding ones of a first flight condition, a second flight condition, and a third flight condition.

2. The VTOL aircraft according to claim 1 , further comprising: a third alighting element extending rearwardly from the first nacelle and a fourth aligning element extending rearwardly from the second nacelle, the third and fourth alighting elements being disposed to support the aircraft in a ground operational condition.

3. The VTOL aircraft according to claim 1 , wherein the first and second wings respectively comprise:
first and second wing portions extending outwardly from the opposite sides of the fuselage; and
first and second swept winglets extending outwardly from and forming obtuse angles with the first and second wing portions.

4. The VTOL aircraft according to claim 1 , wherein each of the first and second nacelles comprise primary exhaust ducts at corresponding ones of the first and second trailing ends and each of the first plurality of exhaust deflectors and the second plurality of exhaust deflectors comprise:
hinges disposed at trailing edges of each of the primary exhaust ducts; and
first and second deflector flaps coupled to each of the primary exhaust ducts via the hinges such that the first and second deflector flaps are pivotable about the trailing edges of the primary exhaust ducts.

5. The VTOL aircraft according to claim 4 , wherein the first and second deflector flaps are disposed in parallel.

6. The VTOL aircraft according to claim 4 , wherein the first and second deflector flaps are independently pivotable.

7. The VTOL aircraft according to claim 4 , wherein the first and second deflector flaps each comprise a Coanda deflector.

8. The VTOL aircraft according to claim 1 , wherein:
the first flight condition comprises ground operations, the second flight condition comprises vertical take-off, hover and landing operations and the third flight condition comprises high speed flight, and
the first configuration comprises a deflecting configuration, the second configuration comprises a divergent-to-neutral configuration and the third configuration comprises a neutral-to-convergent configuration.

9. A vertical take-off and landing (VTOL) aircraft, comprising:
a fuselage with first and second wings extending outwardly from opposite sides of the fuselage;
a first nacelle having a first proprotor disposed on the first wing and a second nacelle having a second proprotor disposed on the second wing, the first nacelle having a first trailing end and the second nacelle having a second trailing end, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight;
a first alighting element extending from rearwardly from a distal end of the first wing and a second alighting element extending rearwardly from a distal end of the second wing, the first and second alighting elements being disposed to support the aircraft in a ground operational condition;
a first plurality of exhaust deflectors pivotally mounted to the trailing end of the first nacelle and a second plurality of exhaust deflectors pivotally mounted to the trailing end of the second nacelle; and
a control system coupled to the exhaust deflectors and configured to control the first plurality of exhaust deflectors and the second plurality of exhaust deflectors to assume at least a first configuration, a second configuration, and a third configuration associated with corresponding ones of a first flight condition, a second flight condition, and a third flight condition.

10. The VTOL aircraft according to claim 9 , further comprising: a third alighting element extending rearwardly from the first nacelle and a fourth aligning element extending rearwardly from the second nacelle, the third and fourth alighting elements being disposed to support the aircraft in a ground operational condition.

11. The VTOL aircraft according to claim 9 , wherein the first and second wings respectively comprise:
first and second wing portions extending outwardly from the opposite sides of the fuselage; and
first and second swept winglets extending outwardly from and forming obtuse angles with respective distal tips of the first and second wing portions.

12. The VTOL aircraft according to claim 9 , wherein each of the first and second nacelles comprise primary exhaust ducts at corresponding ones of the first and second trailing ends and each of the first plurality of exhaust deflectors and the second plurality of exhaust deflectors comprise:
hinges disposed at trailing edges of each of the primary exhaust ducts; and
first and second deflector flaps coupled to each of the primary exhaust ducts via the hinges such that the first and second deflector flaps are independently pivotable about the trailing edges of the primary exhaust ducts.

13. The VTOL aircraft according to claim 12 , wherein the first and second deflector flaps are disposed in parallel.

14. The VTOL aircraft according to claim 12 , wherein the first and second deflector flaps each comprise a Coanda deflector.

15. The VTOL aircraft according to claim 9 , wherein:
the first flight condition comprises ground operations, the second flight condition comprises vertical take-off, hover and landing operations and the third flight condition comprises high speed flight, and
the first configuration comprises a deflecting configuration, the second configuration comprises a divergent-to-neutral configuration and the third configuration comprises a neutral-to-convergent configuration.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Lauder Timothy Fred

Classifications

• B64C29/02 Primary

  having its flight directional axis vertical when grounded · CPC title

• B64D29/02

  associated with wings · CPC title

• Y02T50/164

  Cross-Sectional Technologies · mapped topic

• B64C23/069

  using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title

• B64C9/38

  Jet flaps · CPC title