Gimbal Payload Pointing for Stable UAV Antenna Testing
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Solution Overview
Problem
Existing antenna measurement systems on unmanned aerial vehicles (UAVs) face challenges with changing gain due to roll, pitch, and yaw movements, and alignment issues during flight, making accurate measurements difficult.
Innovation Solution
A gimbal stabilisation system with a control assembly and gimbal assembly that adjusts the payload's pointing and alignment based on real-time position information, using multiple axes of rotation to maintain consistent gain and alignment with the antenna under test (AUT).
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a fixed mounted probe antenna system is used on the UAV, then the system structure is simple, but the antenna gain changes depending on UAV roll, pitch and yaw movements
Solution Approach 1:
The patent applies the dynamics principle by implementing a gimbal assembly that enables the probe antenna to move dynamically relative to the UAV body. The gimbal assembly includes multiple rotatable sections that allow the antenna to adjust its orientation independently of UAV movements, maintaining constant alignment with the AUT despite changes in UAV roll, pitch, and yaw.
Solution Approach 2:
The patent implements feedback by using sensors to detect the actual orientation of the probe antenna and comparing it with the desired orientation. The controller receives feedback signals about antenna position and UAV attitude, then automatically adjusts the gimbal assembly to correct any misalignment, ensuring consistent antenna gain throughout the measurement process.
2Measurement precision
If manual adjustment of the fixed probe antenna is performed during flight, then alignment can be maintained, but the operation becomes difficult and time-consuming
Solution Approach 1:
The patent applies self-service by implementing an automated control system that performs alignment adjustments without human intervention. The controller automatically processes sensor data about UAV attitude and probe antenna position, calculates the required corrections, and actuates the gimbal assembly to maintain proper alignment, eliminating the need for manual adjustment during flight.
Solution Approach 2:
The patent replaces manual mechanical adjustment with an automated electromechanical system. Instead of requiring operators to physically adjust the antenna during flight, the system uses electronic sensors, controllers, and motorized gimbal mechanisms to automatically maintain alignment, substituting human操作 with an automated control loop.
3Ease of manufacture
If the probe antenna is fixed to the UAV structure, then the mounting is simple, but the alignment with AUT cannot be maintained during UAV attitude changes
Solution Approach 1:
The patent applies segmentation by dividing the antenna system into separate functional modules: the probe antenna, the gimbal assembly with multiple rotatable sections, and the control system. This modular structure allows the antenna to be mounted simply on the UAV while the gimbal assembly provides the necessary degrees of freedom to maintain alignment independently of the fixed mounting position.
Data Source
AI summary
Methods, apparatus, and systems are provided for controlling a payload of a gimbal stabilisation system for an aircraft during testing an antenna under test (AUT). The gimbal stabilisation system including a payload control assembly coupled via a yaw motor to a gimbal assembly. The gimbal assembling including the payload comprising a first section with a transceiver for use in testing the AUT and a second section rotatably coupled to the gimbal assembly. The payload control assembly including a controller configured to operate the yaw motor and gimbal assembly by: receiving an in-flight position of the aircraft during testing of the AUT; receiving a position of the AUT in relation to the aircraft; and controlling the gimbal assembly by: calculating a pointing direction and alignment of the first section of the payload relative to the AUT based on the received position of the aircraft and the received position of the AUT; and maintaining pointing and alignment of the first section of the payload towards the AUT based on the calculated pointing direction and alignment of the first section of the payload.