Electric aircraft power load controller system and working method thereof

By designing an electric aircraft power load controller system including main power module, precharge module, drainage module and monitoring and control module, the problem that the existing technology is difficult to meet the capacitive load and arc protection requirements of high-voltage DC power grid of electric aircraft is solved, and dynamic management and arc protection of high-voltage and high-power electrical loads are realized.

CN119682997AActive Publication Date: 2025-03-25COMAC ERA (SHANGHAI) AVIATION CO LTD
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Patent Information

Application Number
CN202411809232.1
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-12-10
Publication Date
2025-03-25
Estimated Expiration
2044-12-10

AI Technical Summary

Technical Problem

Existing mechanical power load controllers and solid-state power controllers are difficult to meet the capacitive load and arc protection requirements of high-voltage DC power grids of electric aircraft.

Method used

An electric aircraft power load controller system is designed, including the main power module, the precharge module, the discharge module and the monitoring and control module. By connecting the solid-state power switch and the high-power mechanical switch in parallel, dynamic management and arc protection of high-voltage and high-power electrical loads are realized.

Benefits of technology

This system can be used for high-voltage and high-power electrical loads of electric aircraft, with good capacitive load adaptability and arc protection, realizing dynamic management of high-voltage and high-power electrical equipment, and avoiding the generation of high-voltage arcs.

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Abstract

The invention discloses an electric aircraft power load controller system and a working method thereof, and belongs to the technical field of electric aircraft controllers, and the electric aircraft power load controller system comprises a main power module, a pre-charging module, a discharging module, a monitoring control module, a power supply module, a communication module and a terminal. Through the mode, the solid-state power switch and the high-power mechanical switch are connected in parallel, and the control time sequence of the two switches is set, so that the high-voltage high-power electric load circuit can be suitable for the application scene of a high-voltage high-power electric load of an electric aircraft, and has good capacitive load adaptability and electric arc protection performance; and controllable pre-charging of the equivalent capacitance of the high-voltage line is realized by controlling the semiconductor power switch by utilizing the impedance characteristic of the semiconductor power switch in the saturation region through the pre-charging module, so that the complexity and the weight of equipment are reduced.
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