Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body

• US 7,185,847 B1
• Filed: 05/13/2004
• Issued: 03/06/2007
• Est. Priority Date: 05/13/2004
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Perez, Juan A., Bouchard, Mark L., Greenwood, Kevin, Gogineni, Purna, Eisentraut, Rudolph A.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US10/845,700
• Time in Patent Office: 1,027 Days
• Field of Search: 244/46, 244/218, 244 327- 329
• US Class Current: 244/46
• CPC Class Codes: F42B 10/12 using fins longitudinally-slidable with respect to the projectile or missile

Abstract

A winged vehicle includes an elongated fuselage, and a wing mechanism affixed to the fuselage. The wing mechanism has a wing-support-body track affixed to and extending lengthwise along the fuselage, a translating wing-support body engaged to and translatable along the wing-support-body track, and exactly two deployable cantilevered wings. Each deployable cantilevered wing has a wing pivot mounted to the translating wing-support body so that the deployable cantilevered wing is pivotable about the translating wing-support body. The two deployable cantilevered wings are each pivotable between a stowed position and a deployed position. An actuation mechanism is operable to controllably move the translating wing-support body along the wing-support-body track and to controllably move the two deployable cantilevered wings between the stowed position and the deployed position.

Claims

1. A winged vehicle comprising

an elongated fuselage;

a wing mechanism affixed to the fuselage and comprising

a wing-support-body track affixed to and extending lengthwise along the fuselage,

a translating wing-support body engaged to and translatable along the wing-support-body track,

exactly two deployable cantilevered wings, each deployable cantilevered wing having a wing pivot mounted to the translating wing-support body so that the deployable cantilevered wing is pivotable about the translating wing-support body, wherein the two deployable cantilevered wings are each pivotable between

a stowed position wherein the deployable cantilevered wings lie relatively close to the fuselage when the translating wing-support body is in a first position along the wing-support-body track, and

a deployed position wherein the deployable cantilevered wings extend relatively outwardly from the fuselage when the translating wing-support body is in a second position along the wing-support-body track; and

an actuation mechanism operable to controllably move the translating wing-support body along the wing-support-body track and to controllably move the two deployable cantilevered wings between the stowed position and the deployed position, wherein the actuation mechanism comprises a leadscrew and a leadscrew follower, and further comprises a gear structure that pivots the cantilevered wings.

2. The winged vehicle of claim 1, wherein the deployable cantilevered wings pivot about their respective wing pivots in linkage with a movement of the translating wing-support body.

3. The winged vehicle of claim 1, wherein the gear structure pivots the cantilevered wings responsive to the movement of the translating wing-support body.

4. The winged vehicle of claim 1, wherein the deployable cantilevered wings pivot about their respective wing pivots independently of a movement of the translating wing-support body.

5. The winged vehicle of claim 1, wherein the actuation mechanism includes a drive selected from the group consisting of an electromechanical drive motor, a pneumatic drive, a gas drive, and a spring drive.

6. The winged vehicle of claim 1, wherein the actuation mechanism comprises an electromechanical actuation mechanism.

7. The winged vehicle of claim 1, wherein the fuselage has a nose and a tail, and wherein the first position is closer to the nose than is the second position.

8. The winged vehicle of claim 1, wherein the winged vehicle further includes

an attachment structure operable to attach the winged vehicle to a launcher.

9. The winged vehicle of claim 1, wherein the winged vehicle has no propulsion system.

10. The winged vehicle of claim 1, wherein the winged vehicle is a glide bomb.

11. The winged vehicle of claim 1, wherein the winged vehicle further includes a propulsion system.

12. The winged vehicle of claim 1, wherein the winged vehicle is a guided missile.

13. The winged vehicle of claim 1, wherein the winged vehicle further includes

a movable guidance surface extending from the fuselage.

14. The winged vehicle of claim 1, further including

a controller within the fuselage.

15. A winged vehicle comprising

an elongated fuselage;

a wing mechanism affixed to the fuselage and comprising

a wing-support-body track affixed to and extending lengthwise along the fuselage,

a translating wing-support body engaged to and translatable along the wing-support-body track,

exactly two deployable cantilevered wings, each deployable cantilevered wing having a wing pivot mounted to the translating wing-support body so that the deployable cantilevered wing is pivotable about the translating wing-support body, wherein the cantilevered wings are supported only from the respective wing pivots mounted to the translating wing support body, and wherein the two deployable cantilevered wings are each pivotable between

a stowed position wherein the deployable cantilevered wings lie relatively close to the fuselage when the translating wing-support body is in a first position along the wing-support-body track, and

a deployed position wherein the deployable cantilevered wings extend relatively outwardly from the fuselage when the translating wing-support body is in a second position along the wing-support-body track; and

an actuation mechanism operable to controllably move the translating wing-support body along the wing-support-body track, the actuation mechanism comprising

a leadscrew operable between the fuselage and the translating wing-support body,

an electromechanical drive motor that turns the leadscrew, and

a pivot mechanism whose turning produces a pivoting movement of the deployable cantilevered wings about their respective wing pivots relative to the translating wing-support body, wherein the pivot mechanism is indirectly turned by the leadscrew.

16. The winged vehicle of claim 15, wherein the fuselage has a nose and a tail, and wherein the first position is closer to the nose than is the second position.

17. The winged vehicle of claim 15, wherein the winged vehicle further includes

a movable guidance surface extending from the fuselage.

18. The winged vehicle of claim 17, further including

a controller within the fuselage and operable to control the movement of the movable guidance surface.

19. The winged vehicle of claim 15, wherein the winged vehicle is a glide bomb.

20. A winged vehicle comprising

an elongated fuselage;

a wing mechanism affixed to the fuselage and comprising

a wing-support-body track affixed to and extending lengthwise along the fuselage,

a translating wing-support body engaged to and translatable along the wing-support-body track,

exactly two deployable cantilevered wings, each deployable cantilevered wing having a wing pivot mounted to the translating wing-support body so that the deployable cantilevered wing is pivotable about the translating wing-support body, wherein the two deployable cantilevered wings are each pivotable between

a stowed position wherein the deployable cantilevered wings lie relatively close to the fuselage when the translating wing-support body is in a first position along the wing-support-body track, and

a deployed position wherein the deployable cantilevered wings extend relatively outwardly from the fuselage when the translating wing-support body is in a second position along the wing-support-body track; and

an actuation mechanism operable to controllably move the translating wing-support body along the wing-support-body track and to controllably move the two deployable cantilevered wings between the stowed position and the deployed position, the actuation mechanism comprising

a first drive comprising a first actuator that moves the wing-support body along the wing-support-body track, and

a second drive comprising a second actuator that controllably moves the two deployable cantilevered wings between the stowed position and the deployed position independently of the movement of the wing-support body.