The invention belongs to the technical field of high-speed aircraft structure thermal tests, and particularly relates to a high-speed aircraft structure thermal test heating system which comprises a quartz lamp tube, a silicon controlled rectifier, a controller, a first thermocouple and a second thermocouple. A plurality of quartz lamp tubes are arranged side by side and are arranged close to the test piece; the first thermocouple is arranged on the test piece; the second thermocouple is suspended between the quartz lamp tube and the test piece; the thyristor is connected with the quartz lamp tube; the controller is connected with the first thermocouple, the second thermocouple and the quartz lamp tube; the controller, the first thermocouple and the quartz lamp tube form outer ring indirect negative feedback control for controlling the temperature of the test piece; the controller, the second thermocouple and the quartz lamp tube form inner ring direct negative feedback control for controlling the temperature of a suspension point; the outer loop indirect negative feedback control takes the target temperature of the test piece as a control target value, and the inner loop direct negative feedback control takes the output value of the outer loop indirect negative feedback control as a control target value.
本申请属于高速飞行器结构热试验技术领域,具体涉及一种高速飞行器结构热试验加热系统,包括石英灯管、可控硅、控制器、第一热电偶、第二热电偶;石英灯管有多根,并排设置,靠近试验件布置;第一热电偶设置在试验件上;第二热电偶悬空设置在石英灯管、试验件之间;可控硅连接石英灯管;控制器连接第一热电偶、第二热电偶、石英灯管;控制器、第一热电偶、石英灯管构成对试验件温度控制的外环间接负反馈控制;控制器、第二热电偶、石英灯管构成对悬空点温度控制的内环直接负反馈控制;外环间接负反馈控制以试验件目标温度为控制目标值,内环直接负反馈控制以外环间接负反馈控制的输出值为控制目标值。
High-speed aircraft structure thermal test heating system
一种高速飞行器结构热试验加热系统
2025-02-25
Patent
Electronic Resource
Chinese
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