固液动力探空火箭箭载数据采集系统设计

Design of data acquisition system for solid-liquid dynamic sounding rocket

针对固液动力探空火箭在进行测试、飞行试验时,需要实时测量并记录推力、燃料供给速率以及吹除系统工况信息的问题,设计并工程实现了对箭载重要设备输出信号进行监控和采集记录的数据采集系统.以STM32F103RB微控制器为核心,完成了数据采集、存储、传输等电路的设计,并在Real View MDK集成开发环境下,运用C语言完成了控制、测试程序的编写.最后,通过Real View ULINKR仿真器实现了软硬件的联合测试,验证了系统的供电控制、采样频率、工况记录等功能都满足设计要求,完成了对箭载重要设备监控和采集记录的任务.只需修改微控制器内的操控程序,就可将此数据采集系统应用于不同型号的固液动力探空火箭.

For solidliquid dynamic sounding rocket under test and aero experiment, the realtime data acquisition and storage problem of thrust, fuel supply rate and blowoff sys tem should be solved. A data acquisition system was thus designed and implemented to mo nitor, acquire and save output data of some relevant important facilities on the solidliquid dynamic sounding rocket. Based on STM32F103RB microcontroller, data acquisition, stor age and transmission circuits were designed. Moreover, under the Real View MDK inte grated development environment, the programs of test and control were compiled by lan guage C. Finally, the software and hardware were tested jointly by Real View ULINKR simulator. The joint debugging results verify that the system functions such as power sup ply control, sampling frequency and working condition storage can meet the design require ments, helping to complete supervisory, acquisition and storage missions for important fa cilities on the solidliquid dynamic sounding rocket. The system can be applied to different categories of solidliquid dynamic sounding rocket only through modification of testing con trol program.