Air vehicle with control system mechanical coupler

Patent metadata

Field	Value
Publication number	US-9546853-B2
Application number	US-201414451696-A
Country	US
Kind code	B2
Filing date	Aug 5, 2014
Priority date	Aug 5, 2014
Publication date	Jan 17, 2017
Grant date	Jan 17, 2017

Abstract

An air vehicle, such as a munition like a guided bomb or missile, has a control system that allows control surfaces to be mechanically uncoupled from one or more actuators to allow the control surfaces to freely move (rotate) relative to a fuselage of the vehicle, for example allowing the control surfaces to “weather vane” by assuming an orientation corresponding to the direction of airflow past the air vehicle (direction of airflow relative to the air vehicle). When active positioning of the control surfaces is desired, the control surfaces may be mechanically coupled to one or more actuators that are used to position the control surfaces. The selective coupling of the actuator(s) and the control surfaces may be accomplished by selectively coupling together a sleeve that is mechanically coupled to the control surfaces, and a nut that moves along a shaft of an actuator, for example using a resilient device.

First claim

What is claimed is:

1. An air vehicle comprising:
a fuselage;
a pair of control surfaces movable relative to the fuselage;
an actuator having a movable actuator shaft; and
a coupler that selectively mechanically couples the actuator shaft to the control surfaces, wherein the coupler is in a disengaged condition when the actuator shaft and the control surfaces are not coupled by the coupler, and wherein the coupler is in an engaged condition when the actuator shaft and the control surfaces are coupled by the coupler;
wherein the coupler is able to shift between the disengaged condition in which the control surfaces move independently of the actuator shaft such that movement of the actuator shaft does not cause movement of the control surfaces, and between the engaged condition in which the actuator shaft and the control surfaces are mechanically coupled such that movement of the actuator shaft causes movement of the control surfaces.

2. The air vehicle of claim 1 , wherein the coupler selectively couples together the actuator shaft, and a sleeve that surrounds the actuator shaft and is mechanically coupled to the control surfaces.

3. The air vehicle of claim 2 , wherein, when the coupler is in the disengaged condition, the sleeve moves freely longitudinally along the shaft, independent of the actuator.

4. The air vehicle of claim 2 ,
wherein the actuator shaft is an externally-threaded shaft; and
wherein a nut threadedly engages the actuator shaft to move longitudinally along the actuator shaft as the actuator shaft is turned by the actuator.

5. The air vehicle of claim 4 , wherein the coupler includes a resilient device that engages both the nut and the sleeve, when the coupler is in the engaged condition.

6. The air vehicle of claim 5 , wherein the coupler includes:
a pair of engagement members that protrude inward into a volume enclosed by the sleeve, wherein the engagement members engage detents on the nut when the coupler is in the engaged condition; and
springs operatively coupled to the engagement members to provide a force to engage the engagement members in the detents.

7. The air vehicle of claim 6 , wherein the engagement members are diametrically opposed, on opposite sides of the sleeve.

8. The air vehicle of claim 6 , wherein the engagement members are pins.

9. The air vehicle of claim 6 , wherein the engagement members are plates.

10. The air vehicle of claim 4 , wherein the coupler moves with the sleeve when the coupler is both in the engaged condition and in the disengaged condition.

11. The air vehicle of claim 4 , wherein movement of the nut presses the sleeve against a stop, to have the coupler mechanically couple the nut and the sleeve, shifting the coupler from the disengaged condition to the engaged condition.

12. The air vehicle of claim 4 , wherein the nut is secured to the actuator prior to operation of the actuator to shift the coupler from the disengaged condition to the engaged condition.

13. The air vehicle of claim 12 ,
wherein the nut is initially secured to an actuator housing of the actuator using a bracket that is fixedly coupled to the actuator housing;
wherein the bracket engages the nut to secure the nut to the actuator housing.

14. The air vehicle of claim 1 , wherein the coupler is mechanically resettable from the engaged condition to the disengaged condition.

15. The air vehicle of claim 1 , wherein the actuator is an electromechanical actuator.

16. The air vehicle of claim 1 , wherein the air vehicle is a guided bomb or missile.

17. The air vehicle of claim 1 , wherein the actuator is an electromagnetic actuator operatively coupled to the actuator shaft, the actuator shaft being rotatable; and
wherein the coupler selectively couples together the actuator shaft, and a sleeve that surrounds the actuator shaft and is mechanically coupled to the control surfaces.

18. A method of operating the air vehicle of claim 1 , wherein the actuator is an electromagnetic actuator, the method comprising:
allowing the control surfaces of the air vehicle to weather vane by being passively positioned by air flow, with the control surfaces mechanically decoupled from the actuator shaft of the air vehicle;
after the allowing the control surfaces to weather vane, mechanically coupling the actuator shaft to the control surfaces; and
after the mechanically coupling, actively positioning the control surfaces using the electromagnetic actuator.

19. The method of claim 18 , wherein the coupler is a resilient coupler, and the actuator shaft is a rotatable actuator shaft;
wherein the mechanically coupling includes using the resilient coupler to mechanically couple the rotatable actuator shaft that is mechanically coupled to the electromagnetic actuator, with a sleeve that surrounds the rotatable actuator shaft and that is mechanically coupled to the control surfaces.

20. The method of claim 18 ,
wherein the air vehicle is a guided munition; and
wherein the actively positioning of the control surfaces is used to guide the munition to a target.

Assignees

• Raytheon Co

Inventors

• Morgan Bruce E
• Alejandro Stevie
• Robichaux Jerry D
• Ramos Alfredo
• Klemm Heinz D
• Nickel Bryan W
• Douglas Andrew P

Classifications

• F42B15/01

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title

• F42B10/02

  Stabilising arrangements · CPC title

• F42B10/64 Primary

  of fins · CPC title

• F42B15/10

  Missiles having a trajectory only in the air · CPC title