Wing tip aileron actuation system

• US 10,308,347 B2
• Filed: 10/26/2016
• Issued: 06/04/2019
• Est. Priority Date: 10/26/2016
• Status: Active Grant

• Current Assignee: Simmonds Precision Products, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Simmonds Precision Products, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Buttolph, Martin Edwy, Moran, David F.
• Primary Examiner(s): Benedik, Justin M
• Application Number:
  US15/334,801
• Publication Number:
  US 20180111675A1
• Time in Patent Office: 951 Days
• CPC Class Codes: B64C 2009/005 Ailerons
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 9/00 Adjustable control surfaces or members, e.g. rudders trimming stabilising surfaces B64C5/10
• CPC Class Codes: F42B 10/14 using fins spread or deployed after launch, e.g. after leaving the barrel
• CPC Class Codes: F42B 10/64 of fins

Abstract

A control system for a flight vehicle includes first and second pivot pins each having a hollow cylindrical shape with an opening therein, first and second deployable wings configured to pivot about the first and second pivot pins between a stowed position and a deployed position with the first and second deployable wings each having first and second wing tip shafts extending between the first and second pivot pins and first and second ailerons at a tip of the deployable wings, first and second lever pins within the opening in the pivot pins with the first and second lever pins each having a first end that extends out from a top of the pivot pin and a second end connected to the wing tip shaft and with the first and second lever pins configured to rotate the wing tip shafts to control the ailerons.

Claims

1. A flight vehicle comprising:

first and second wings configured to be contained within a housing when in a stowed position and extend outward from the housing when in a deployed position;

an actuator;

a bell crank having a first end connected to the actuator, a pivot point at a second end, and first and second arms extending outward from the second end with the first arm having a first fork and the second arm having a second fork;

a first pivot pin rotatable with the first wing between the stowed position and the deployed position, the first pivot pin having an opening that is aligned with and adjacent to the first fork;

a first lever pin within the opening in the first pivot pin and extending out from the opening in the first pivot pin to be located within the first fork on the first arm, the first lever pin rotatable with the first wing and the first pivot pin so that the first lever pin is disengaged from the first fork when in the stowed position and is engaged with the first fork when in the deployed position;

a first wing tip shaft within the first wing and connected to the first lever pin at a first end and to a first aileron at a second end, the first wing tip shaft configured to rotate to control the first aileron when the first fork of the bell crank moves the first lever pin within the first pivot pin;

a second pivot pin rotatable with the second wing between the stowed position and the deployed position, the second pivot pin having an opening that is aligned with and adjacent to the second fork;

a second lever pin within the opening in the second pivot pin and extending out from the opening in the second pivot pin to be located within the second fork on the second arm, the second lever pin rotatable with the second wing and second pivot pin so that the second lever pin is disengaged from the second fork when in the stowed position and is engaged with the second fork when in the deployed position; and

a second wing tip shaft within the second wing and connected to the second lever pin at a first end and to a second aileron at a second end, the second wing tip shaft configured to rotate to control the second aileron when the second fork of the bell crank moves the second lever pin within the second pivot pin.

2. The flight vehicle of claim 1, further comprising:

a first slot in the housing into which an end of the first lever pin extends; and

a second slot in the housing into which an end of the second lever pin extends.

3. The flight vehicle of claim 2, wherein the first slot and the second slot each have an elongated cross section oriented parallel to the first wing tip shaft and the second wing tip shaft, respectively, when in the stowed position configured to prevent nonrotational movement of a top end the first lever pin and a top end the second lever pin when in the stowed position and configured to allow nonrotational movement of the top end of the first lever pin and the top end of the second lever pin along the first slot and second slot, respectively, when the first wing tip shaft and the second wing tip shaft are in the deployed position.

4. The flight vehicle of claim 2, wherein the first slot and the second slot are configured to ensure the top end of the first lever pin remains within the first fork and the top end of the second lever pin remains within the second fork when the first wing and the second wing move from the stowed position to the deployed position.

5. The flight vehicle of claim 1, wherein the first lever pin and the second lever pin each have a cross section that is elongated so that the first lever pin is in contact with the first fork and the second pin is in contact with the second fork when in the deployed position and the first lever pin is not in contact with the first fork and the second pin is not in contact with the second fork when in the stowed position.

6. The flight vehicle of claim 1, wherein the first lever pin pivots about the first end of the first wing tip shaft within the opening in the first pivot pin to rotate the first wing tip shaft and the second lever pin pivots about the first end of the second wing tip shaft within the opening in the second pivot pin to rotate the second wing tip shaft.

7. The flight vehicle of claim 1, wherein the first wing tip shaft extends within the first wing nonparallel to the first wing.

8. The flight vehicle of claim 1, wherein the second wing tip shaft extends within the second wing nonparallel to the second wing.

9. The flight vehicle of claim 1, wherein the actuator is configured to pivot the bell crank about the pivot point to move the first lever pin adjacent to the first fork on the first arm and the second lever pin adjacent to the second fork on the second arm.

10. The flight vehicle of claim 9, wherein the bell crank is configured to pivot to move the first lever pin in an opposite direction from the second lever pin to control the roll of the flight vehicle.

11. The flight vehicle of claim 1, wherein the first aileron is located at a tip of the first wing and the second aileron is located at a tip of the second wing.

12. The flight vehicle of claim 1, wherein the actuator includes a motor and pinion with teeth that mate with teeth on the first end of the bell crank.

13. The flight vehicle of claim 1, further comprising:

a first pivot shaft within the first wing and attached at a first end of the first pivot shaft to the second end of the first wing tip shaft and at a second end of the first pivot shaft to the first aileron; and

a second pivot shaft within the second wing and attached at a first end of the second pivot shaft to the second end of the second wing tip shaft and at a second end of the second pivot shaft to the second aileron.

14. The flight vehicle of claim 1, wherein the first pivot pin is cylindrical in shape and the second pivot pin is cylindrical in shape.

15. The flight vehicle of claim 14, wherein the opening in the first pivot pin has a substantially hourglass cross-sectional shape to allow the first lever pin to pivot within the first pivot pin about the first end of the first wing tip shaft, and wherein the opening in the second pivot pin has a substantially hourglass cross-sectional shape to allow the second lever pin to pivot within the second pivot pin about the first end of the second wing tip shaft.

16. A control system for a flight vehicle comprising:

a first pivot pin having a hollow cylindrical shape with an opening therein;

a second pivot pin having a hollow cylindrical shape with an opening therein;

a first deployable wing configured to pivot about the first pivot pin between a stowed position and a deployed position, the first deployable wing having a first wing tip shaft extending between the first pivot pin and a first aileron at a tip of the first deployable wing;

a second deployable wing configured to pivot about the second pivot pin between the stowed position and the deployed position, the second deployable wing having a second wing tip shaft extending between the second pivot pin and a second aileron at a tip of the second deployable wing;

a first lever pin within the opening in the first pivot pin with the first lever pin having a first end that extends out from a top of the first pivot pin and a second end connected to the first wing tip shaft, the first lever pin configured to rotate the first wing tip shaft to control the first aileron; and

a second lever pin within the opening in the second pivot pin with the second lever pin having a first end that extends out from a top of the second pivot pin and a second end connected to the second wing tip shaft, the second lever pin configured to rotate the second wing tip shaft to control the second aileron.

17. The control system of claim 16, further comprising:

a bell crank with a first arm adjacent to the first end of the first lever pin and a second arm adjacent to the first end of the second lever pin, the bell crank configured to move the first end of the first lever pin to rotate the first wing tip shaft and to move the first end of the second lever pin to rotate the second wing tip shaft when the first deployable wing and the second deployable wing are in the deployed position.

18. The control system of claim 16, further comprising:

an actuator connected to the bell crank and configured to pivot the bell crank about a pivot point to move the first arm and the second arm of the bell crank.

19. The control system of claim 16, wherein the first deployable wing, the first pivot pin, and the first lever pin are configured to rotate from the stowed position to the deployed position so that the first lever pin is in contact with the first arm of the bell crank when in the deployed position and is not in contact with the first arm of the bell crank when in the stowed position, and wherein the second deployable wing, the second pivot pin, and the second lever pin are configured to rotate from the stowed position to the deployed position so that the second lever pin is in contact with the second arm of the bell crank when in the deployed position and is not in contact with the second arm of the bell crank when in the stowed position.

20. The control system of claim 16, wherein the first lever pin has an elongated cross-sectional shape configured to be in contact with a first fork on the first arm of the bell crank when in the deployed position and provide clearance between the first lever pin and the first fork when in the stowed position and the second lever pin has an elongated cross-sectional shape configured to be in contact with a second fork on the second arm of the bell crank when in the deployed position and provide clearance between the second lever pin and the second fork when in the stowed position.