Apparatus for retaining and deploying a wing of an aerial vehicle

• US 10,442,521 B1
• Filed: 12/22/2016
• Issued: 10/15/2019
• Est. Priority Date: 02/03/2016
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Ellzey, Steven J., Copp, James C., Richards, Gregory M.
• Primary Examiner(s): Burgess, Marc
• Application Number:
  US15/388,560
• Time in Patent Office: 1,027 Days
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 5/12 for retraction against or within fuselage or nacelle
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 70/50 Launching from storage containers, e.g. from submarine missile tubes

Abstract

An apparatus, having: a fuselage body section (180) configured to be secured to an aircraft fuselage (16); a pivot column (310) protruding from the fuselage body section; and a center wing section (214) configured to be secured to a center wing panel of a trifold wing (200). The fuselage body section and the center wing section are configured to cooperate with each other to rotate the center wing section relative to the fuselage body section from a stowed position (250) to a deployed position (302). The pivot column comprises a column feature (240) configured to engage with tip features (236) of the trifold wing to hold the trifold wing in a folded configuration when the trifold wing is in the stowed position and to disengage from the tip features as the trifold wing rotates to the deployed position, thereby freeing the trifold wing to unfold.

Claims

1. An apparatus, comprising:

a fuselage body section configured to be secured to an aircraft fuselage;

a pivot column protruding from the fuselage body section; and

a center wing section, that rotates about the pivot column, configured to be secured to a center wing panel of a trifold wing;

wherein the fuselage body section and the center wing section are configured to cooperate with each other to rotate the center wing section relative to the fuselage body section from a stowed position to a deployed position; and

wherein the pivot column is rotationally fixed with respect to the fuselage and comprises a column feature positioned under the center wing panel that protrudes fore and aft relative to the fuselage, the column feature configured to engage with tip features of the trifold wing to hold the trifold wing in a folded configuration when the trifold wing is in the stowed position, and to disengage from the tip features as the trifold wing rotates away from the stowed position to the deployed position, thereby freeing the trifold wing to unfold.

2. The apparatus of claim 1, further comprising the trifold wing comprising:

the center wing panel comprising the center wing section;

a port wing panel pivotally secured to a port end of the center wing panel and comprising a respective tip feature configured to engage the column feature, the port wing panel configured to fold under the center wing panel into the folded configuration; and

a starboard wing panel pivotally secured to a starboard end of the center wing panel and comprising a respective tip feature configured to engage the column feature, the starboard wing panel configured to fold under the center wing panel into the folded configuration.

3. The apparatus of claim 1, wherein a longitudinal axis of the pivot column coincides with an axis of rotation of the center wing section.

4. The apparatus of claim 1, further comprising the center wing panel of the trifold wing comprising the center wing section, wherein the pivot column is configured to position the column feature below the center wing panel.

5. The apparatus of claim 4, wherein the center wing panel further comprises a pylon that moves with the center wing panel,

wherein when in the stowed position the column feature protrudes from the pylon to hold the trifold wing in the folded configuration;

and

wherein in the deployed position the pylon encompasses the column feature therein.

6. The apparatus of claim 5, further comprising a pivot column bottom fastener secured to a lower end of the pivot column and configured to frictionally engage the pylon between the pivot column bottom fastener and the pivot column to control a rate of the rotation via friction.

7. The apparatus of claim 1, further comprising a resilient member configured to bias the center wing section toward the deployed position when the center wing section is in the stowed position.

8. The apparatus of claim 1, further comprising a joint arrangement configured to enable the rotation, the joint arrangement comprising:

a fuselage cylindrical surface arranged on the fuselage body section; and

a wing cylindrical surface arranged on the center wing section,

wherein the fuselage cylindrical surface and wing cylindrical surfaces are nested.

9. The apparatus of claim 8, the joint arrangement further comprising:

a circumferential ramp; and

a tang configured to engage the circumferential ramp,

wherein a cooperation of the tang and the circumferential ramp is configured to secure the center wing section to the fuselage body section and to permit limited rotation of the center wing section.

10. The apparatus of claim 9, the joint arrangement further comprising at least one of a stop and a locking pin, each configured to stop the rotation of the center wing section when the center wing section reaches the deployed position.

11. The apparatus of claim 2, further comprising wing panel locking arrangements, each locking arrangement configured to lock a respective panel to the center wing panel in an unfolded configuration, each wing panel locking arrangement comprising a movable pin secured to one of the center wing panel and the respective panel, and a hasp secured to the other of the respective panel and the center wing panel and configured to displace and then receive the movable pin as the respective panel moves to the unfolded configuration.

12. The apparatus of claim 2, comprising an aerial vehicle that comprises the fuselage body section, the pivot column, the center wing section, and the trifold wing.

13. An apparatus, comprising:

a fuselage;

a trifold wing comprising a port wing panel, a starboard wing panel, and a center wing panel there between;

a joint arrangement configured to secure the center wing panel to the fuselage and permit the trifold wing to rotate from a stowed position to a deployed position;

a pivot column secured to the fuselage and configured to secure the port and starboard wing panels of the trifold wing in a folded configuration when the trifold wing is in the stowed position and to release from the port and starboard wing panels as the trifold wing rotates away from the stowed position by way of the center wing panel rotating about the pivot column;

wherein the pivot column is rotationally fixed with respect to the fuselage and comprises a column feature positioned under the center wing panel that protrudes fore and aft relative to the fuselage to engage respective panel features in the port and starboard wing panels when the trifold wing is in the folded configuration and the stowed position; and

wherein as the trifold wing rotates away from the stowed position the column feature disengages from the panel features.

14. The apparatus of claim 13, the center wing panel further comprising a pylon from which the column feature protrudes when the center wing panel is in the stowed position, and within which the column feature resides when the center wing panel is in the deployed position.

15. The apparatus of claim 14, further comprising a pivot column bottom fastener secured to a lower end of the pivot column and configured to frictionally engage the pylon between the pivot column bottom fastener and the pivot column to control a rate of the rotation via friction.

16. The apparatus of claim 13, the joint arrangement further comprising:

a fuselage cylindrical surface arranged on the fuselage;

a wing cylindrical surface arranged on the center wing panel and nested with the fuselage cylindrical surface;

a resilient member configured to bias the center wing panel toward the deployed position when the center wing panel is in the stowed position;

a ramp formed in the fuselage; and

a tang formed in the center wing panel,

wherein the fuselage and wing cylindrical surfaces cooperate to enable the rotation; and

wherein the ramp and the tang cooperate to secure the center wing panel to the fuselage and to limit the rotation.

17. The apparatus of claim 16, the joint arrangement further comprising a locking pin configured to engage and prevent rotation of the wing cylindrical surface relative to the fuselage cylindrical surface when the trifold wing reaches the deployed position.

18. The apparatus of claim 13, further comprising wing panel locking arrangements, each locking arrangement configured to lock a respective panel to the center wing panel in an unfolded configuration, each wing panel locking arrangement comprising a movable pin secured to one of the center wing panel and the respective panel, and a hasp secured to the other of the respective panel and the center wing panel and configured to displace and then receive the movable pin as the respective panel moves to the unfolded configuration.

19. The apparatus of claim 13, further comprising an aerial vehicle comprising the fuselage, the trifold wing, the joint arrangement, and the pivot column.