Airframe

• US 8,905,351 B2
• Filed: 11/01/2011
• Issued: 12/09/2014
• Est. Priority Date: 11/01/2011
• Status: Expired due to Fees

• Current Assignee: Vanguard Defense Industries, LLC
• Original Assignee: Vanguard Defense Industries, LLC
• Inventors: Buscher, Michael Sean, Kulesza, Henry E.
• Primary Examiner(s): Ellis, Christopher P
• Assistant Examiner(s): ANDONYAN, GEORGE A
• Application Number:
  US13/286,897
• Publication Number:
  US 20130105628A1
• Time in Patent Office: 1,134 Days
• Field of Search: 244/17.11, 244/119, 344/144, 396/12, 396/13
• US Class Current: 244/119
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/17 Helicopters flying platforms B64U10/13
• CPC Class Codes: B64U 20/65 Composite materials
• CPC Class Codes: B64U 20/87 Mounting of imaging devices, e.g. mounting of gimbals
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 60/50 with landing legs

Abstract

The disclosure describes airframe systems. In one embodiment, an airframe system includes a first side wall and a second side wall. The airframe system further includes a drive train platform configured to carry an aircraft drive train and to attach the first side wall parallel to the second side wall. The airframe system additionally includes a first structural rod configured to attach the first side wall parallel to the second side wall, and a second structural rod positioned aft of the first structural rod and configured to attach the first side wall to parallel to the second side wall. The first and second structural rods are configured to carry a camera mount.

Claims

1. An unmanned aircraft airframe system comprising:

a first planar side wall;

a second planar side wall positioned vertically parallel to the first planar side wall;

a drive train platform configured to carry an aircraft drive train and to attach the first planar side wall parallel to the second planar side wall;

a first structural rod configured to attach the first planar side wall vertically parallel to the planar second side wall; and

a second structural rod positioned aft of the first structural rod and configured to attach the first planar side wall vertically parallel to the second planar side wall, wherein the first and second structural rods are configured to carry a camera mount, wherein the first and the second structural rods are configured to provide rigidity to a forward section of the airframe system, wherein the first structural rod comprises a first piston attachment point and wherein the second structural rod comprises a second piston attachment point, wherein the camera mount is mounted onto the first structural rod via a first piston, and the camera mount is mounted onto the second structural rod via a second piston, and wherein the first and the second pistons do not extend past a cowling covering the unmanned aircraft airframe system.

2. The system of claim 1, wherein the first piston comprises a first shock absorber and the second piston comprises a second shock absorber.

3. The system of claim 1, wherein the drive train platform is configured to provide rigidity to an aft section of the airframe system.

4. The system of claim 1, comprising a support member disposed in a middle section of the airframe system between the second structural rod and the drive train platform, wherein the support member is configured to provide rigidity to a middle section of the airframe system.

5. The system of claim 1, wherein the plurality of holes openings comprise over one third a surface area of the first and the second planar side walls.

6. The system of claim 1, wherein the plurality of openings comprise openings having different diameters.

7. The system of claim 1, comprising a plurality of L-brackets, wherein the L-brackets are configured to removably couple a skid landing system, a pontoon landing system, a wheeled landing system, or a combination thereof, to the first and the second side walls.

8. The system of claim 1, wherein a liquid fuel tank is attached to the airframe system directly under the drive train platform and along a centerline between the first and the second side walls, and wherein the liquid fuel tank comprises a first tank wall positioned extending beyond the first planar side wall and a second tank wall positioned extending beyond the second planar side wall to define a tank width wider than a distance separating the first side wall from the second side wall.

9. The system of claim 4, wherein the drive train platform comprises a drive train mechanically coupled to a shaft and configured to rotate a blade via rotation of the shaft.

10. The system of claim 9, wherein the first and the second side walls comprise a length of between 24 inches and 52 inches, and wherein the airframe system weighs 7 pounds or less.

11. An unmanned aircraft system (UAS) comprising:

a liquid fuel tank comprising a first tank wall disposed opposite a second tank wall, wherein a first distance between the first and the second tank walls defines a tank width of the liquid fuel tank;

an airframe comprising;

a first planar side wall;

a second planar side wall positioned vertically parallel to the first planar side wall;

a drive train platform configured to support an aircraft drive train and to attach the first planar side wall to the second planar side wall;

a first structural rod configured to attach the first side wall vertically parallel to the second side wall; and

a second structural rod positioned aft of the first structural rod and configured to attach the first side wall vertically parallel to the second side wall,

wherein the liquid fuel tank is disposed completely underneath the drive train platform,

wherein the first tank wall is positioned extending beyond the a UAS canopy and the second tank wall is positioned extending beyond the UAS canopy,

wherein the tank width is wider than the UAS canopy, and

wherein the first and the second structural rods are configured to provide rigidity to a forward section of the airframe,

wherein the first structural rod comprises a first piston attachment point and

wherein the second structural rod comprises a second piston attachment point,

wherein a camera mount is mounted onto the first structural rod via a first piston, and the camera mount is mounted onto the second structural rod via a second piston, and

wherein the first and the second pistons do not extend past a cowling covering the airframe.

12. The system of claim 11, wherein the fuel tank comprises a third and a fourth tank walls coupled to each other at an angle of between 45 degrees and 179 degrees to form a fuel trench.

13. The system of claim 11, wherein the liquid fuel tank comprises means for protection against a projectile.

14. The system of claim 12, comprising a fuel line positioned in the fuel trench and disposed between the first and the second tank walls.

15. The system of claim 13, wherein the means for protection against the projectile comprise a plurality of baffled plates having a plurality of through-holes.

16. An unmanned aircraft system (UAS) comprising:

a landing system;

an airframe comprising;

a first planar side wall;

a second planar side wall positioned vertically parallel to the first planar side wall;

a drive train platform configured to support an aircraft drive train and to attach the first side wall vertically parallel to the second side wall;

a support member configured to provide structural support in a middle section of the airframe;

a first structural rod configured to attach the first planar side wall to the second planar side wall; and

a second structural rod configured to attach the first planar side wall to the second planar side wall, wherein the first and the second structural rods are configured to provide rigidity to a forward section of the airframe, wherein the first structural rod comprises a first piston attachment point, wherein the second structural rod comprises a second piston attachment point, wherein a camera mount is mounted onto the first structural rod via a first piston and the camera mount is mounted onto the second structural rod via a second piston, wherein the first and the second pistons do not extend past a cowling covering the airframe, and wherein the landing system is attached to the first and to the second planar side walls.

17. The system of claim 16, comprising a weapon and a liquid fuel tank, wherein the landing system comprises:

a first skid support member disposed fore of the liquid fuel tank;

a second skid support member disposed aft of the liquid fuel tank;

a first skid positioned perpendicular to the first and second skid support members and attached to the first and second skid support members, wherein the first skid is configured to contact a ground during landing; and

a second skid positioned perpendicular to the first and second skid support members and attached to the first and second skid support members, wherein the second skid is configured to contact the ground during landing, wherein the weapon is attached to the first and second skid support members.

18. The system of claim 16, wherein the landing system comprises skids, pontoons, wheels, or a combination thereof.

19. The system of claim 16, comprising a plurality of L-brackets configured to attach the landing system to the first and to the second side walls.