基于CPLD设计的火箭发动机涡轮泵转速测量产品

针对现有火箭发动机涡轮泵转速模拟式测量产品测量精度较低信号传输稳定性较差的问题,提出了基于复杂可编程逻辑器件设计的数字式的火箭发动机涡轮泵转速测量产品;选用AD620仪用放大器对涡轮泵转速信号进行前端放大和处理,选用ispLSI1032 CPLD器件对涡轮泵转速信号进行数字式测量,利用VHDL语言进行了编程和仿真,进行了实物验证测试;实验结果验证了利用复杂可编程逻辑器件测量火箭发动机涡轮泵转速的可行性,表明数字式测量比模拟式测量方法具有更高的精度;最后对数字式涡轮泵转速测量产品下一步应用于火箭飞行试验任务还需进行的测试项目和试验内容进行了说明。

Speed measurement of rocket engine turbine pump based on CPLD

In order to solve the problem of low measuring accuracy and poor stability of signal transmission of the existing rocket engine turbine pump speed analog measurement products. This paper presents the design of a digital rocket engine turbine pump speed measuring product based on complex programmable logic device. The AD620 instrument is used to amplify and process the speed signal of the turbine pump by using the amplifier. Digital measurement of turbine pump speed signal using ispLSI1032 CPLD device. The programming and simulation are carried out using VHDL language. Physical verification test was carried out. The experimental results verify the feasibility of using complex programmable logic device to measure the speed of the rocket engine turbine pump. The experimental results show that the digital measurement method has higher accuracy than the analog measurement method. Finally, this paper describes the test items and test contents of the digital turbine pump speed measurement product in the next step of the rocket flight test mission.