Movable control surface ejection system

Patent metadata

Field	Value
Publication number	US-9828096-B2
Application number	US-201615051602-A
Country	US
Kind code	B2
Filing date	Feb 23, 2016
Priority date	Feb 23, 2016
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

Systems and methods are provided for decoupling movable control surfaces. Such systems may detect that a movable control surface is in a non-responsive state, such as a hard-over, and decouple the movable control surface from the main, fixed, control surface. The control surfaces may be coupled to an aircraft. A controller of the aircraft may detect the nonresponsive movable control surface, provide instructions to decouple the movable control surface, and compensate for the decoupling of the movable control surface in instructions provided to flight systems of the aircraft.

First claim

What is claimed is:

1. A system comprising:
an aircraft control surface comprising:
a main control surface body, and
a movable control surface body, wherein the movable control surface body is configured to output position data to a controller and is coupled to a release mechanism configured to:
couple, during normal operation, the movable control surface body to the main control surface body;
allow for movement of the movable control surface body relative to the main control surface body; and
decouple the movable control surface body from the main control surface body in response to a decouple command communicated by the controller to separate the movable control surface body from the main control surface body; and

the controller communicatively connected to the aircraft control surface and configured to:
receive the position data,
determine, from the position data, that the movable control surface body is in a non-responsive condition, and
provide the decouple command to the release mechanism to decouple the movable control surface body from the main control surface body.

2. The system of claim 1 , wherein the non-responsive condition is a hard-over condition.

3. The system of claim 1 , wherein the aircraft control surface comprises a plurality of movable control surface bodies.

4. The system of claim 3 , wherein each movable control surface body is coupled to the main control surface body via at least one release mechanism.

5. The system of claim 1 , wherein the controller is further configured to provide, responsive to input received from an input device, instructions to the movable control surface body associated with positioning of the movable control surface body.

6. The system of claim 5 , wherein the controller is further configured to detect that the movable control surface body is decoupled from the main control surface body.

7. The system of claim 6 , wherein the aircraft control surface comprises a plurality of movable control surface bodies and wherein the controller is further configured to adjust, responsive to detecting that at least one of the movable control surface bodies is decoupled, the instructions provided to one or more coupled movable control surface bodies.

8. The system of claim 6 , wherein the controller is further configured to:
provide instructions to one or more propulsors responsive to input received from the input device; and
adjust, responsive to detecting that the movable control surface body is decoupled, the instructions provided to the one or more propulsors.

9. The system of claim 1 , wherein the aircraft control surface comprises a plurality of movable control surface bodies and wherein the controller is further configured to:
adjust, responsive to determining that at least one of the movable control surface bodies is in a non-responsive condition and prior to providing the decoupling command, instructions to one or more responsive movable control surface bodies associated with positioning of the one or more responsive movable control surface bodies.

10. The system of claim 1 , wherein the controller is further configured to:
determine a global position of at least a portion of the system;
determine that the global position is within a populated area; and
prevent, responsive to the determination that the global position is within the populated area, decoupling of the movable control surface body from the main control surface body.

11. The system of claim 1 , wherein the release mechanism comprises:
a first joint portion configured to be coupled to the main control surface body;
a second joint portion configured to be coupled to the movable control surface body; and
a linkage configured to selectively move between a holding position to couple, during normal operation, the first joint to the second joint and a released position to decouple, upon detection of the non-responsive condition, the first joint and the second joint.

12. The system of claim 11 , wherein the linkage comprises at least one of a slide, a hook, a grasping mechanism, an adhesive, a hydraulic linkage, a pneumatic linkage, and/or a magnetic connection.

13. The system of claim 1 , wherein the release mechanism comprises an explosive charge.

14. The system of claim 1 , wherein the movable control surface body is a flap, an aileron, a flaperon, an elevator, a rudder, a wing tip, a spoiler, a tab, a slat, a body-flap, a VTOL (Vertical Take-off and Land) blade, a canard, an air brake, and/or a sleeve.

15. The system of claim 1 , wherein the position data is generated, at least in part, by a strain gauge coupled to the movable control surface body and the main control surface body, and wherein the release mechanism comprises a strain gauge release mechanism configured to sever at least a portion of the strain gauge from the main control surface body.

16. An aircraft comprising the system of claim 1 , wherein the aircraft comprises a fuselage and/or blended-wing-body coupled to the aircraft control surface and a propulsor.

17. A method comprising:
receiving position data from a movable control surface body, wherein the movable control surface body is coupled to a main control surface body via a release mechanism configured to:
couple, during normal operation, the movable control surface body to the main control surface body,
allow for movement of the movable control surface body relative to the main control surface body, and
decouple the movable control surface body from the main control surface body to separate the movable control surface body from the main control surface body,

determining that the movable control surface body is in a non-responsive condition; and
decoupling, via the release mechanism, the movable control surface body from the main control surface body.

18. The method of claim 17 , wherein a plurality of movable control surfaces are coupled to the main control surface body and further comprising adjusting, responsive to decoupling at least one non-responsive movable control surface body, control instructions provided to one or more movable control surface bodies coupled to the main control surface body.

19. The method of claim 17 , wherein a plurality of movable control surfaces are coupled to the main control surface body and further comprising adjusting, responsive to decoupling the at least one non-responsive movable control surface body, control instructions provided to one or more propulsors.

20. The method of claim 17 , wherein the main control surface body is a portion of an aircraft and the method further comprises:
determining a global position of an aircraft;
determining that the global position is within a populated area; and
preventing, responsive to the determination that the global position is within the populated area, decoupling of the movable control surface body from the main control surface body.

21. The method of claim 17 , wherein the non-responsive condition is a hard-over condition.

22. The method of claim 17 , wherein the position data is generated, at least in part, by a strain gauge coupled to the movable control surface body and the main control surface body, and wherein the release mechanism comprises a strain gauge release mechanism configured to sever at least a portion of the strain gauge from the main control surface body.

Assignees

• Boeing Co

Inventors

• Veto Christopher

Classifications

• B64D31/06

  actuated automatically · CPC title

• B64C2009/005

  Ailerons · CPC title

• B64C27/46

  Blades · CPC title

• B64C5/10

  adjustable · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title