Thrust compensation control method and system based on multi-duct electric aircraft

By calculating motor thrust distribution through real-time monitoring and numerical optimization methods, the problem of uneven motor load during thrust compensation in multi-duct electric aircraft is solved, the stability and safety of the aircraft are improved, and the motor battery life is extended.

CN120681339AActive Publication Date: 2025-09-23COMAC ERA (SHANGHAI) AVIATION CO LTD
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Patent Information

Application Number
CN202510928320.1
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-07-07
Publication Date
2025-09-23
Estimated Expiration
2045-07-07

AI Technical Summary

Technical Problem

Existing multi-duct electric aircraft do not fully consider torque equivalence and motor thrust differences when compensating thrust, resulting in uneven motor load and power consumption, and may even cause the aircraft attitude to lose control. Existing algorithm research is relatively limited.

Method used

By monitoring the motor operating status in real time, the numerical optimization method is used to calculate the remaining motor thrust distribution to ensure the balance of total thrust and total torque. The optimization algorithm minimizes the motor thrust difference, and thrust compensation is achieved using the fault detection module and electric propulsion control unit.

Benefits of technology

It improves the stability and safety of the aircraft in the event of motor failure, avoids attitude loss of control, ensures uniform motor load, extends motor battery life, and has strong robustness and adaptability.

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Abstract

The invention discloses a thrust compensation control method and system based on a multi-duct electric aircraft, and belongs to the technical field of aviation aircraft control. When the aircraft runs, a motor controller monitors running data of each motor in real time and diagnoses the fault state of each motor in real time, and once a motor triggers power degradation or failure fault, the motor controller can start the motor controller to start the motor controller; and the electric propulsion control unit distributes the thrust of the remaining motors based on an optimization algorithm. Through the above mode, the system can quickly identify the faulty motor and trigger the thrust optimization algorithm in real time by monitoring the running state of the motor in real time, after the fault occurs, the system calculates the current total thrust and total torque according to the initial thrust distribution and the motor position, redistributes the thrust of the remaining non-faulty motors through the optimization algorithm, and the thrust of the non-faulty motors is optimized. The total thrust and the total torque are kept consistent with those before the fault, the attitude of the aircraft is prevented from being out of control, the service life of a motor battery is balanced by minimizing the thrust difference, and the system reliability is improved.
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