Airborne vehicle having deployable wing and control surface

• US 6,186,443 B1
• Filed: 06/25/1999
• Issued: 02/13/2001
• Est. Priority Date: 06/25/1998
• Status: Expired due to Fees

• Current Assignee: International Dynamics Corporation
• Original Assignee: International Dynamics Corporation
• Inventors: Shaffer, James E.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/344,032
• Time in Patent Office: 599 Days
• Field of Search: 244/3.24, 244/3.26, 244/3.3, 244/49, 244/75.R
• US Class Current: 244/49
• CPC Class Codes: B64C 5/12 for retraction against or within fuselage or nacelle
• CPC Class Codes: F42B 10/14 using fins spread or deployed after launch, e.g. after leaving the barrel
• CPC Class Codes: F42B 15/105 Air torpedoes, e.g. projectiles with or without propulsion, provided with supporting air foil surfaces

Abstract

An airborne vehicle having a deployable airfoil with an elevon wherein the deployment of the airfoil and the control of the elevon are both powered by a single servo mechanism. A shear pin prevents relative movement between the elevon and the airfoil until the airfoil is in the deployed position. A stop mechanism locks the airfoil in the deployed position, whereafter operation of the drive mechanism fractures the shear pin, thereby allowing the elevon to be controlled by the drive mechanism.

Claims

1. An airborne vehicle comprising:

a frame;

a drive mechanism connected to the frame;

a first drive link connected to the drive mechanism;

a second drive link connected to the first drive link;

a base;

a control surface connected to the second drive link and to the base;

a means for preventing relative movement between the first and the second drive links so that forward movement of the first drive link will move the base from a storage position to an extended position relative to the frame;

a stop operable when engaged to prevent movement of the base relative to the frame once the base reaches the extended position;

wherein operation of the drive mechanism with the stop engaged will release the means for preventing relative movement between the first and the second drive links so that movement of the drive mechanism will cause movement of the control surface relative to the frame.

2. The vehicle of claim 1 wherein the means for preventing relative movement between the first and the second drive links comprises a shear pin.

3. The vehicle of claim 1 wherein the means for preventing relative movement between the first and the second drive links comprises a clutch mechanism.

4. The vehicle of claim 1 wherein the means for preventing relative movement between the first and the second drive links comprises a ball detent mechanism.

5. The vehicle of claim 1 wherein the means for preventing relative movement between the first and the second drive links comprises an actuator.

6. The vehicle of claim 1 wherein the stop comprises a spring loaded pin and detent mechanism.

7. The vehicle of claim 1 wherein the stop comprises an actuator.

8. The vehicle of claim 1 wherein the drive mechanism comprises a servo motor.

9. The vehicle of claim 1 wherein the base further comprises an airfoil.

10. The vehicle of claim 1 further comprising a means for preventing relative movement between the control surface and the frame during a launching of the vehicle.

11. The vehicle of claim 10 wherein the means for preventing relative movement between the control surface and the frame comprises a shear pin, and wherein the shear pin is operable to be fractured by operation of the drive mechanism.

12. The vehicle of claim 10 wherein the means for preventing relative movement between the control surface and the frame comprises an actuator.

13. An airborne vehicle comprising:

a frame;

a servo mechanism attached to the frame;

a first drive shaft connected to the servo mechanism and rotatably supported by the frame;

a second drive shaft connected to the first drive shaft by a gear mechanism;

an elevon attached to the second drive shaft;

a wing base rotatably attached to the first drive shaft and the elevon;

a means for preventing relative movement between the first and the second drive shafts so that forward rotation of the first drive shaft will rotate the wing base from a storage position to an extended position relative to the frame;

a stop operable when engaged to prevent rotation of the wing base relative to the frame once the wing base reaches the extended position;

wherein operation of the servo mechanism with the stop engaged will release the means for preventing relative movement between the first and the second drive shafts so that rotation of the servo mechanism will cause rotation of the elevon relative to the wing base.

14. The vehicle of claim 13 wherein the wing base further comprises an airfoil.

15. The vehicle of claim 13 wherein the means for preventing relative movement between the first and the second drive shafts comprises a shear pin.

16. The vehicle of claim 13 wherein the means for preventing relative movement between the first and the second drive shafts comprises a clutch mechanism.

17. The vehicle of claim 13 wherein the means for preventing relative movement between the first and the second drive shafts comprises a ball detent mechanism.

18. The vehicle of claim 13 wherein the means for preventing relative movement between the first and the second drive shafts comprises an actuator.