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固体火箭发动机点火装置是固体火箭的重要组成部分,它必须在极短的时间内可靠地点燃发动机主燃药,使发动机安全稳定的工作。直列式点火系统应用于固体火箭发动机上,极大地提高了发动机的可靠性。完整的直列式钝感点火系统由直列式全电子安全与解除保险装置、脉冲功率装置、冲击片点火管组成。针对这一系统,利用Labview设计一个可视化的固体火箭发动机直列式点火实验控制系统,该系统通过PC机可与单片机进行串口通信,单片机按照安全解保时序向直列式全电子安全与解除保险装置传输上电信号,当解保时序正确且接收到高压监测信号时触发点火管,同时采集功率脉冲装置中高压储能电容的电压。试验表明,该系统可准确地按照固体火箭发动机直列式点火时序完成点火实验。
Solid rocket engine ignition device is an important part of solid rocket, it must be a very short period of time to reliably ignite the main engine of the engine, the engine safe and stable work. In-line ignition system used in solid rocket engine, which greatly improves the reliability of the engine. The complete in-line insensitive ignition system consists of in-line full electronic safety and deflashing devices, pulsed power devices and impact plate ignition tubes. In view of this system, a visual solid rocket motor in-line ignition experimental control system is designed by using Labview. The system can communicate with the microcontroller via serial port through the PC, and the SCM transmits to the in-line full electronic safety and release safety device according to the timing of the safety release. When the power-on signal is correct and the high-voltage monitoring signal is received, the ignition pipe is triggered, and at the same time, the voltage of the high-voltage storage capacitor in the power pulse device is collected. Experiments show that the system can be accurately in accordance with the solid rocket engine inline ignition timing to complete the ignition experiment.