TILT-BALL TURRET WITH GIMBAL LOCK AVOIDANCE

• US 20160194092A1
• Filed: 10/09/2015
• Published: 07/07/2016
• Est. Priority Date: 08/29/2011
• Status: Active Grant

• Current Assignee: Aerovironment
• Original Assignee: Aerovironment
• Inventors: SZAREK, Thomas, OMER, Thomas, DIMOTAKIS, Manolis Pavlos, McBRIDE, Jefferson C.
• Granted Patent: US 10,081,441 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• 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 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• 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 2101/32 for cartography or topography
• CPC Class Codes: F16M 11/123 the axis of rotation intersecting in a single point, e.g. by using gimbals
• CPC Class Codes: F16M 11/126 for tilting and panning F16M11/14 takes precedence
• CPC Class Codes: F16M 11/18 with mechanism for moving the apparatus relatively to the stand
• CPC Class Codes: H04N 7/183 for receiving images from a single remote source

Abstract

A turret assembly for attachment on the undersurface of an aircraft that reduces performance limitations due to gimbal lock and reduces the cross section profile of the assembly. The assembly includes a roll actuator including a drive shaft. A yoke having a cross member is coupled to the drive shaft and a pair of prongs. The yoke is rotated via the roll actuator and drive shaft along a roll axis oriented substantially parallel to the body of the aircraft. A turret is mounted on the prongs of the yoke. A tilt actuator is contained within the turret. The tilt actuator tilts the turret on a tilt axis relative to the yoke. The tilt axis is perpendicular to the roll axis.

Claims

1. (canceled)

2. An aircraft configured to fly at a positive angle of attack relative to a direction of travel, the aircraft comprising:

a fuselage; and

a turret assembly coupled to the fuselage, the turret assembly including;

a roll actuator including a drive shaft;

a yoke having a pair of prongs coupled to the drive shaft, the yoke being rotatable via the roll actuator and drive shaft along a roll axis oriented substantially parallel to a center axis of the aircraft;

a turret mounted on the prongs of the yoke for rotation along a tilt axis perpendicular to the roll axis;

a tilt actuator operable to tilt the turret about the tilt axis; and

a first sensor housed in the turret for tilting therewith about the tilt axis and rolling therewith about the roll axis,

wherein the orientation of the roll axis substantially parallel to the center axis of the aircraft achieves a first sensor field of view that is directed above the direction of travel of the aircraft at gimbal lock.

3. The aircraft of claim 2, wherein the turret has a generally spherical shape.

4. The aircraft of claim 2, wherein the first sensor is a camera.

5. The aircraft of claim 2, wherein the turret has an aperture and includes a second sensor positioned in the aperture.

6. The aircraft of claim 5, wherein the second sensor includes at least one of a color camera or an infrared camera.

7. The aircraft of claim 6, further comprising a video controller located within the turret, the video controller coupled to the first sensor and providing a video output from the first sensor.

8. The aircraft of claim 2, wherein the tilt actuator includes a processor and a tilt motor and the roll actuator includes a processor and a roll motor, the processors accepting positioning inputs and controlling the respective tilt and roll motors to position the ball turret.

9. The aircraft of claim 2, further comprising a wiring harness for delivery of electrical signals to and from the turret, the wiring harness including one or more wires having a first portion that extends through the drive shaft and a second portion that is mounted exteriorly of a first prong of the yoke, between the first prong and the turret.

10. The aircraft of claim 2, wherein the tilt actuator includes a processor and a tilt motor and the roll actuator includes a cortex controller and a roll motor, the processor accepting positioning inputs and controlling the respective tilt and roll motors to position the ball turret.

11. The aircraft of claim 2, wherein the direction of travel is substantially along the horizon.

12. An aircraft configured to fly at a positive angle of attack relative to a direction of travel, the aircraft comprising:

a fuselage; and

a turret assembly coupled to the fuselage, the turret assembly including;

a turret;

a first sensor housed in the turret;

a roll actuator for imparting to the first sensor roll motion about a roll axis that is substantially parallel to a center axis of the aircraft; and

a tilt actuator for imparting to the first sensor a tilt motion transverse to the roll axis, wherein the orientation of the roll axis substantially parallel to the center axis of the aircraft achieves a first sensor field of view that is directed above the direction of travel of the aircraft at gimbal lock.

13. The aircraft of claim 12, wherein the turret has a generally spherical shape.

14. The aircraft of claim 12, wherein the first sensor is a camera.

15. The aircraft of claim 12, wherein the turret has an aperture and includes a second sensor positioned in the aperture.

16. The aircraft of claim 15, wherein the second sensor includes at least one of a color camera or an infrared camera.

17. The aircraft of claim 16, further comprising a video controller located within the turret, the video controller coupled to the first sensor and providing a video output from the first sensor.

18. The aircraft of claim 12, wherein the tilt actuator includes a processor and a tilt motor and the roll actuator includes a processor and a roll motor, the processors accepting positioning inputs and controlling the respective tilt and roll motors to position the ball turret.

19. The aircraft of claim 12, further comprising:

a wiring harness including one or more wires for delivery of electrical signals to and from the turret;

a yoke having first and second prongs coupled to a drive shaft through which the roll motion is imparted to the turret,

wherein the one or more wires of the wiring harness extend through the drive shaft and pass exteriorly of the prong of the yoke, between the first prong and the turret.

20. The aircraft of claim 12, wherein the tilt actuator includes a processor and a tilt motor and the roll actuator includes a cortex controller and a roll motor, the processor accepting positioning inputs and controlling the respective tilt and roll motors to position the ball turret.

21. The aircraft of claim 12, wherein the direction of travel is substantially along the horizon.