Design of Highly Integrated and Low Power Flight Control Computer for eVTOL Vehicles

Aiming at the high safety and lightweight requirements of electric vertical take-off and landing (eVTOL) vehicles, this paper proposes an improved flight control system (FCS) architecture and multiple fault tolerance method based on dual-machine master-standby redundancy. Based on heterogeneous sensor hardware redundancy design and multi-level comparison pairs mechanism, combined with cross channel data link (CCDL), system control logic and asymmetric multi-processing (AMP), the system reliability is improved under limited redundancy. A Markov state model of the system is established, and the reliability of this method is improved by 11.1% compared with the traditional three-coefficient scheme when the fault test coverage is 0.95. The aviation-specific HKSA9201 SoC is selected for the integration design, the weight, power consumption, PCB area, and number of core devices of flight control computer (FCC) are reduced by more than 50%. The result proves that the architecture can significantly reduce the size and cost while meeting the primary failure operation, secondary failure safety (FO/FS) and specific reliability indexes, which can provide technical support for eVTOL applications.