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针对某型无人直升机活塞式发动机,通过对其功率特性和负载特性研究建立其动力学模型。根据无人直升机不同阶段对发动机转速的要求,分别对发动机启动、过渡和额定状态设计控制律,并通过MatLab仿真试验和开车试验进行验证。试验结果表明本文制定的控制策略能够有效的实现发动机的安全启动,转速的平滑过渡且在额定工作状态下对负载的干扰有很强的抑制效果。
For a certain type of unmanned helicopter piston engine, through its power and load characteristics of the study established its dynamic model. According to the requirement of engine speed at different stages of unmanned helicopter, the control laws of engine starting, transition and rated state are respectively designed and verified by MatLab simulation test and driving test. The experimental results show that the control strategy developed in this paper can effectively achieve the safe start of the engine, the smooth transition of the speed and the strong restraining effect on the load disturbance under the rated working condition.