Rotor blown wing aircraft including a rotor blown wing having at least one selectively controllable control surface and a method of controlling a rotor blown wing aircraft

Patent metadata

Field	Value
Publication number	US-9908615-B2
Application number	US-201615234562-A
Country	US
Kind code	B2
Filing date	Aug 11, 2016
Priority date	Oct 26, 2015
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A rotor blown wing (RBW) aircraft including an airframe, at least one rotor blown wing (RBW) having at least control selectively controllable surface, at least one rotor configured to generate and direct an airflow over the at least one RBW, and a control system operatively connected to the at least two selectively controllable control surfaces. The control system selectively controls the at least one selectively controllable control surface to change the airflow over the at least one RBW to facilitate a vertical landing.

First claim

What is claimed is:

1. A rotor blown wing (RBW) aircraft comprising:
an airframe;
at least one rotor blown wing (RBW) including a first selectively controllable control surface arranged on one side of the at least one rotor blown wing and a second selectively controllable control surface arranged on a second, opposing side of the at least one rotor blown wing directly opposite of the first selectively controllable surface;
at least one rotor configured to generate and direct an airflow over the at least one RBW; and
a control system operatively connected to the first and second selectively controllable control surfaces, the control system selectively controlling the first and second selectively controllable control surfaces to change the airflow over the at least one RBW to facilitate a vertical landing.

2. The RBW aircraft according to claim 1 , wherein the at least one RBW includes a leading edge and a trailing edge, the first and second selectively controllable control surfaces being arranged at the trailing edge.

3. The RBW according to claim 1 , wherein the at least RBW includes a leading edge and a trailing edge, the first and second selectively controllable control surfaces being arranged at the leading edge.

4. The RBW aircraft according to claim 1 , wherein the control system selectively independently controls a position of at least one of the first and second selectively controllable control surfaces to change the airflow over the at least one RBW.

5. The RBW aircraft according to claim 3 , further comprising: a sensor operatively coupled to the control system, the control system controlling the first and second selectively controllable control surfaces based on the positional changes of the RBW aircraft sensed by the sensor.

6. The RBW aircraft according to claim 5 , wherein the sensor comprises an inertial sensor.

7. The RBW aircraft according to claim 6 , wherein the inertial sensor comprises an embedded GPS/Inertial (EGI) sensor.

8. The RBW aircraft according to claim 5 , wherein the sensor comprises a trim sensor.

9. The RBW aircraft according to claim 1 , wherein the at least one RBW includes a first RBW portion extending between the airframe and the at least one rotor and a second RBW portion extending outboard of the at least one rotor, the first and second selectively controllable control surfaces being associated with the first RBW portion and third and fourth selectively controllable control surfaces being associated with the second RBW portion.

10. A method of controlling an attitude of a rotor blown wing (RBW) aircraft including at least one rotor blown wing (RBW) having a first selectively controllable control surface arranged on one side of the at least one rotor blown wing and a second selectively controllable control surface arranged on a second, opposing side of the at least one rotor blown wing directly opposite of the first selectively controllable surface, the method comprising:
generating an airflow over the RBW;
sensing an attitude of the RBW aircraft;
changing the airflow over the RBW by selectively activating one or more of the first and second selectively controllable control surfaces; and
vertically landing the RBW aircraft.

11. The method of claim 10 , wherein sensing the attitude of the RBW aircraft includes monitoring aircraft trim changes.

12. The method of claim 11 , wherein activating the at least one first and second selectively controllable control surfaces includes changing the airflow over the RBW to compensate for the trim changes.

13. The method according to claim 10 , wherein sensing the attitude of the RBW aircraft includes sensing inertial changes in the RBW aircraft through one or more signals received from inertial sensors.

14. The method of claim 13 , wherein sensing inertial changes in the RBW aircraft includes receiving one or more signals from an embedded GPS/Inertial (EGI) sensor.

15. The method according to claim 11 , wherein selectively activating the first and second selectively controllable control surfaces includes selectively independently activating the first and second selectively controllable control surfaces arranged at a trailing edge of the RBW.

16. The method according to claim 15 , wherein selectively activating the first and second selectively controllable control surfaces includes selectively independently activating the first and second selectively controllable control surfaces arranged at a leading edge of the RBW.

17. The method according to claim 15 , wherein selectively activating the first and second selectively controllable control surfaces includes selectively independently activating the first and second selectively controllable control surfaces arranged at a leading edge of the RBW and selectively independently activating third and fourth selectively controllable control surfaces arranged at a leading edge of the RBW.

18. The method according to claim 10 , wherein selectively activating the first and second selectively controllable control surfaces includes selectively activating the first and second selectively controllable control surfaces arranged along the RBW between an airframe and a rotor and third and fourth selectively controllable control surfaces arranged along the RBW outboard of the rotor.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Alber Mark R
• Parkhurst Jeffery
• Fegely Cody
• Kubik Stephen

Classifications

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title

• B64C13/16 Primary

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

• B64C9/00

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• G01C21/165

  combined with non-inertial navigation instruments · CPC title

• B64C25/52

  Skis or runners · CPC title