The embodiment of the invention discloses a yaw moment suppression method for a distributed electric propulsion aircraft. The yaw moment suppression method comprises the steps that system state parameters of a distributed electric propulsion system are obtained; aircraft characteristic parameters are obtained; according to the state parameters of the driving motor in the distributed electric propulsion system and the characteristic parameters of the airplane, yaw moment generated by the internal fault of the distributed electric propulsion system is obtained; obtaining a constraint condition of the distributed electric propulsion system, and calculating a target rotating speed of each driving motor in the distributed electric propulsion system according to the constraint condition; the target rotating speed of each driving motor is adjusted through a control unit in the distributed electric propulsion system, and yaw moment suppression or elimination caused by internal faults of the distributed electric propulsion system is achieved. According to the technical scheme provided by the embodiment of the invention, the problem that the flight attitude of an existing distributed electric propulsion aircraft is unstable due to the fact that the number of driving motors is large, and yawing torque is generated when the driving motors break down is solved.
本发明实施例公开了一种分布式电推进飞机的偏航力矩抑制方法,包括:获取分布式电推进系统的系统状态参数;获取飞机特征参数;根据分布式电推进系统中驱动电机状态参数和飞机特征参数,获取由分布式电推进系统内部故障所产生的偏航力矩;获取分布式电推进系统的约束条件,根据约束条件计算分布式电推进系统中各个驱动电机的目标转速;通过分布式电推进系统中控制单元完成各个驱动电机目标转速调节,实现因分布式电推进系统内部故障导致的偏航力矩抑制或消除。本发明实施例提供的技术方案解决了现有分布式电推进飞机,由于驱动电机的数量较多,在驱动电机故障时产生偏航力矩,从而导致飞机的飞行姿态不稳定的问题。
Yawing moment suppression method for distributed electric propulsion aircraft
一种分布式电推进飞机的偏航力矩抑制方法
2024-01-19
Patent
Elektronische Ressource
Chinesisch
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