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This is to discuss and design the path forward for a number of key architectural changes that will enable greater robustness, fault tolerance, and redundancy.
Problem
Failure to detect vibration induced inertial navigation failures early enough during system integration or operation has contributed to a number of vehicle loss incidents
The current practice of using the IMU’s internal DLPF is a major blocker for the following reasons:
IMU internal sampling is then limited to 1kHz which makes the ADC step susceptible to aliasing on airframes with high RPM/geared motors and high blade count propellers
The use of the IMU’s internal DLPF means that high frequency vibration clipping of the ADC cannot be detected externally until it has affected the INS
Data cannot be logged at the ADC sampling frequency so it is not possible to use a data driven approach to resolving vibration induced navigation failures.
Under construction
Project Board: https://github.com/PX4/Firmware/projects/23
This is to discuss and design the path forward for a number of key architectural changes that will enable greater robustness, fault tolerance, and redundancy.
Problem
Failure to detect vibration induced inertial navigation failures early enough during system integration or operation has contributed to a number of vehicle loss incidents
The current practice of using the IMU’s internal DLPF is a major blocker for the following reasons:
High Level Architecture
WIP - https://drive.google.com/file/d/13Mcztqcvcaa82bg5UD3o95UAd-6uKu50/view?usp=sharing
Specific problems and solutions
Incremental work towards solutions
Side issues that we might want to eliminate or at least reconsider along the way
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