Adjustable servomechanism assemblies and associated systems and methods

• US 8,382,027 B2
• Filed: 07/24/2012
• Issued: 02/26/2013
• Est. Priority Date: 03/18/2009
• Status: Active Grant

• Current Assignee: Insitu Incorporated (The Boeing Co.)
• Original Assignee: Insitu Incorporated (The Boeing Co.)
• Inventors: Jackson, Clifford
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Dixon, Keith L
• Application Number:
  US13/556,931
• Publication Number:
  US 20120325959A1
• Time in Patent Office: 217 Days
• Field of Search: 244/1.R, 244/99.2, 244/99.3, 244/90.R, 244/87
• US Class Current: 244/1.R
• CPC Class Codes: A63H 27/02 Model aircraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/25 Fixed-wing aircraft VTOL aircraft B64U10/20
• CPC Class Codes: B64U 40/10 for adjusting control surfaces or rotors
• CPC Class Codes: Y10T 403/7033 including a lock or retainer
• CPC Class Codes: Y10T 74/18568 Reciprocating or oscillating to or from alternating rotary

Abstract

Adjustable servomechanism assemblies and associated systems and methods. An unmanned aircraft system in accordance with one embodiment of the disclosure includes a movable mechanism and a servomechanism assembly operably coupled to the movable mechanism. The system also includes an interface assembly operably coupled to an output shaft of the servo and the movable mechanism. The interface assembly includes an adapter portion carried by the output shaft and an output arm releasably engaged with the adapter portion. The adapter portion includes a first aperture having a non-round surface mated with a non-round surface of the output shaft, and a non-splined, engagement surface. The output arm includes a second aperture sized to receive at least a portion of the outer surface of the adapter portion. The second aperture includes a generally smooth inner surface in contact with and rotatable through 360 degrees relative to the engagement surface of the adapter portion.

Claims

1. A method for operating an unmanned aircraft, the method comprising:

coupling a movable mechanism of the aircraft to a servomechanism carried by the aircraft with an interface assembly operably coupled to a linkage between the movable mechanism and the servomechanism, wherein the interface assembly includes—

an adapter portion mated with a non-round surface of an output shaft of the servomechanism, wherein the adapter portion includes a generally smooth, non-splined, engagement surface; and

an output arm having an aperture sized to receive at least a portion of the engagement surface of the adapter portion;

inserting at least a portion of the adapter through the aperture in the output arm, wherein the output arm is rotatably movable through 360 degrees relative to the engagement surface of the adapter portion; and

rotating at least one of the output arm and the adapter portion relative to each other until the output arm is at a desired orientation relative to the output shaft.

2. The method of claim 1 wherein rotating at least one of the output arm and the adapter portion relative to each other comprises adjusting the orientation of the output arm without changing a geometry of the linkage.

3. The method of claim 1 wherein rotating at least one of the output arm and the adapter portion relative to each other comprises adjusting the orientation of the output arm with the servo commanded to center.

4. The method of claim 1 wherein the aperture in the output arm has (a) a first diameter sized such that the output arm can freely move through 360 degrees relative to the outer surface of the adapter, and (b) a second diameter less than the first diameter, and wherein the method further comprises:

changing the diameter of the aperture from the first diameter to the second diameter such that the output arm is releasably secured to the adapter portion and generally non-rotatable when the output arm is at the desired position.

5. The method of claim 4 wherein the output arm further comprises an adjustable collar portion positioned to receive a fastener, and wherein changing the diameter of the output arm from the first diameter to the second diameter comprises rotating the fastener relative to the collar portion to change the aperture between the first and second diameters.

6. The method of claim 1, further comprising releasably securing the output arm relative to the adapter portion and the output shaft with a fastener.

7. The method of claim 1 wherein coupling the movable mechanism to a servomechanism comprises coupling a first servomechanism having a first interface assembly to the movable mechanism, and wherein the method further comprises coupling a second servomechanism having a second interface assembly at least approximately identical to the first interface assembly to the movable mechanism.

8. The method of claim 1 wherein coupling a movable mechanism of the aircraft to a servomechanism comprises coupling an aerodynamic control surface of the aircraft to the servomechanism.

9. The method of claim 1 wherein coupling a movable mechanism of the aircraft to a servomechanism comprises coupling at least one of a throttle control, cylinder head temperature control, and carburetor heat control to the servomechanism.