Articulated support for unmanned aircraft system

• US 10,399,703 B2
• Filed: 10/05/2017
• Issued: 09/03/2019
• Est. Priority Date: 10/05/2016
• Status: Active Grant

• Current Assignee: Textron Systems Corporation (Textron Inc)
• Original Assignee: AAI Corporation (Textron Inc)
• Inventors: Schill, Graham, Baity, Sean Marshall, McCool, Kyle W., Katilas, Leonard T.
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US15/725,382
• Publication Number:
  US 20180099764A1
• Time in Patent Office: 698 Days
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64F 1/10 using self-propelled vehicles
• CPC Class Codes: B64F 1/22 for handling aircraft
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 30/10 Wings
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/23 with each propulsion means having an individual motor
• CPC Class Codes: B64U 70/00 Launching, take-off or landing arrangements
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20
• CPC Class Codes: B64U 70/93 for use on a land or nautical vehicle
• CPC Class Codes: B64U 80/86 Land vehicles

Abstract

An articulated support includes a base and pitch-roll-yaw assembly having a pitch/roll subassembly and a yaw subassembly. The pitch/roll subassembly includes a central member configured for spring-loaded rotation about a pitch/roll axis, and the yaw subassembly has a U-shaped member configured (a) at end portions to engage under-wing connection lugs of an unmanned aircraft system (UAS) and (b) at a central portion to mate to the central member of the pitch/roll subassembly in a rotatable manner providing for rotation of the yaw subassembly about a yaw axis. The pitch/roll subassembly and yaw subassembly are further co-configured to define first and second fixed yaw positions in which a fuselage of the UAS is, respectively, parallel to and perpendicular to the pitch/roll axis, permitting roll motion and pitch motion of the UAS when mounted on the articulated support.

Claims

1. An articulated support for an unmanned aircraft system, comprising:

a base; and

a pitch-roll-yaw assembly attached to the base, the pitch-roll-yaw assembly including a pitch/roll subassembly and a yaw subassembly, the pitch/roll subassembly including a central member configured for spring-loaded rotation about a pitch/roll axis, the yaw subassembly having a U-shaped member configured (a) at end portions to engage under-wing connection lugs of the unmanned aircraft system and (b) at a central portion to mate to the central member of the pitch/roll subassembly in a rotatable manner providing for rotation of the yaw subassembly about a yaw axis perpendicular to the pitch/roll axis, the pitch/roll subassembly and yaw subassembly being further co-configured to define first and second fixed yaw positions in which a fuselage of the unmanned aircraft system is, respectively, parallel to and perpendicular to the pitch/roll axis, permitting roll motion and pitch motion of the unmanned aircraft system when mounted on the articulated support,

wherein the pitch/roll subassembly includes;

a pair of mounting shafts extending from the central member along the pitch/roll axis through corresponding mounting blocks; and

a pair of coil springs each mounted on a respective one of the mounting shafts and configured to provide the spring-loaded rotation of the central member about the pitch/roll axis.

2. The articulated support of claim 1, wherein the mounting blocks are secured to a flange plate of the pitch/roll subassembly, the flange plate being secured to a corresponding flange plate of the base.

3. The articulated support of claim 1, wherein the ends of the mounting shafts are covered by respective caps having respective flanges with openings that align with respective openings of a lock member used to lock the rotational position of the central member.

4. The articulated support of claim 3, wherein the flange of each cap has two holes corresponding to upright and rotated pitch/roll positions respectively of the central member, one hole being aligned with a hole of the lock member in the upright position and the other hole being aligned with the hole of the lock member in the rotated position, a locking pin being placed through the aligned holes to lock the central member in either position.

5. The articulated support of claim 1, wherein the pitch/roll subassembly includes a post extending upwardly along the yaw axis from the central member, the post being received in an opening of the yaw subassembly.

6. The articulated support of claim 5, wherein the post has a groove for receiving an O-ring retainer to secure the yaw subassembly to the pitch/roll subassembly.

7. The articulated support of claim 1, wherein the yaw subassembly further includes a horizontally extending pan configured to receive the fuselage of the unmanned aircraft system, enabling the articulated support to temporarily support and elevate the unmanned aircraft system without the unmanned aircraft system being mounted to the end portions of the U-shaped member.

8. The articulated support of claim 7, wherein the pan is attached to and supported by the central member of the yaw subassembly.

9. The articulated support of claim 8, wherein the pan is positioned to support the unmanned aircraft system with its wings clearing the end portions of the U-shaped member, providing for vertical take-off of the unmanned aircraft system from the articulated support.

10. The articulated support of claim 1, wherein each end portion includes retention flanges defining retention slots for receiving the under-wing connection lugs of the unmanned aircraft system, the retention flanges having holes that align with corresponding holes of the connection lugs to receive a removable retention pin used to secure the unmanned aircraft system to the articulated support.

11. The articulated support of claim 1, wherein the base has a pyramidal shape narrowing to a top to which the pitch-roll-yaw assembly is mounted.

12. The articulated support of claim 11, wherein the top includes a horizontal flange plate to which a corresponding horizontal flange plate of the pitch-roll-yaw assembly is attached to mount the pitch-roll-yaw subassembly to the base.

13. The articulated support of claim 11, wherein the base includes a set of I-beam legs extending downwardly and outwardly to a frame surrounding the legs at a bottom of the base.

14. The articulated support of claim 13, wherein the frame includes blocks configured to attach the articulated support to an underlying platform or other structure.

15. The articulated support of claim 14, wherein the blocks include wedge blocks that interface to corresponding anchor blocks, and one or more paired wedge block and anchor block include a wedge-type draw latch mechanism configured to tightly draw the wedge block and anchor block together and retain them in locked relationship.