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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ispLSI1032CPLD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。
Aiming at the problem of poor measurement accuracy and low signal transmission stability of the existing rocket engine turbo-pump speed measurement measurement system, a digital rocket engine turbo-pump speed measurement product based on complex programmable logic device is proposed. The AD620 instrument Amplifier turbo pump speed signal front-end amplification and processing, the choice of ispLSI1032CPLD turbopump speed signal digital measurement, the use of VHDL language programming and simulation, the physical verification test; experimental results verify the use of complex programmable logic device The feasibility of measuring the rotational speed of a rocket engine turbo pump shows that the digital measurement has higher accuracy than the analog measurement method. Finally, the test items and tests to be applied to the rocket flight test mission of the digital turbo pump speed measurement product The content is described.