Gimbal stabilisation system

The computer-implemented method of any preceding claim, further comprising controlling the pointing and/or alignment of the payload about at least two axes of rotation, wherein the control assembly is rotatably coupled to the gimbal assembly and the payload is rotatably coupled to the gimbal assembly.

The computer-implemented method of any preceding claim, further comprising controlling the pointing and/or alignment of the payload about at least three axes of rotation, wherein the control assembly is rotatably coupled to the gimbal assembly, the payload is rotatably coupled to the gimbal assembly, wherein the gimbal assembly includes a further axis of rotation for use in controlling the pointing and/or alignment of the payload.

The computer-implemented method as claimed in any preceding claim, wherein a base station is located at a geographic position relative to the AUT, the location of the base station defining a reference position for the aircraft during testing of the AUT, and receiving the position of the AUT further comprising:

• receiving the position of the base station;
• calculating the position of the AUT based on the geographic position of the AUT relative to the position of the base station.

The computer-implemented method as claimed in any preceding claim, wherein the payload further comprises a camera located at the first end of the payload, and receiving the position of the AUT further comprising:

• analysing one or more image(s) from the camera to identify a position of the AUT;
• and
• calculating the position of the AUT based on the identified position of the AUT in said one or more analysed images.

The computer-implemented method as claimed in any preceding claim, wherein the AUT includes a beacon signal and receiving the position of the AUT further comprising:

• receiving the beacon signal associated with the AUT;
• and
• determining the position of the AUT based on the received beacon signal.

The computer-implemented method as claimed in any preceding claim, further comprising maintaining pointing of the first section of the payload towards a designated position in relation to the AUT.

The computer-implemented method as claimed in any preceding claim, wherein the communication sensor interface is a transceiver, the method further comprising controlling the gimbal assembly to perform at least one or more from the group of:

• pointing an RF transmitting feed horn of the transceiver at a specified geometric point associated with the AUT;
• cancelling any movements or motion of the aircraft to maintain pointing of the RF transmitting feed horn at the specified geometric point or the AUT;
• maintaining alignment of the RF transceiver feedhorn polarization with the corresponding AUT transceiver feedhorn polarisation during testing of the AUT.

A gimbal stabilisation system for an aircraft comprising a control assembly rotatably coupled to a gimbal assembly comprising a payload, the control assembly comprising a controller configured to operate the gimbal assembly to maintain pointing of a first section of the payload towards an antenna under test, AUT, with a second section of the payload rotatably coupled to the gimbal assembly, wherein the first section comprises a communication sensor interface for use in testing the AUT.

A system as herein described with reference to the accompanying drawings.

A method as herein described with reference to the accompanying drawings.

An apparatus as herein described with reference to the accompanying drawings.

A computer program product as herein described with reference to the accompanying drawings.