底排弹综合参数测试系统设计+电路图+PCB图
本文首先分析讨论了该数据采集存储系统的总体设计方案、关键技术及其解决方案，详细阐述了硬件部分各组成模块的设计方法，并从模拟通道信号采集、串口数字量转换接收、电源转换、主控单元、Flash存储、程序调试与下载和USB接口通信模块等几个方面给出了相应的电路设计和详细说明;其次，对系统软件部分的设计进行了详细的论述，包括系统的时序控制、多串口和不定长度串口数据的接收、对有要求的数据编码存储的实现、DMA方式传输等，对上位机数据读取与分析软件也进行了介绍;
本文设计的基于STM32的数据采集存储系统具有体积小、功耗低、高可靠性、抗高过载、抗干扰能力强等特点。
关键词 STM32，数据采集，数据存储，DMA
毕业论文设计说明书外文摘要
Title Bottom line projectile comprehensive parameter test system
Abstract
On the basis of theory research for data acquisition and storage system and design principles for engineering system, and for technical specifications of a certain kind of flight measurement system, this thesis is intended for a data acquisition and storage system based on STM32, which uses SPIFlash W25Q16BV NAND Flash as the medium for storage, USB interface to realize the communication between the hardware and PC. It achieves the acquisition and storage for 5 channel analogy signals. And it also accomplishes the data-reading, unpacked.
This thesis first analyzes the overall design scheme of the data acquisition and storage
system. key technology and its solution. And it elaborates the design method of constituent
modules for hardware in detail and outputs the circuit design and detail description from the aspect of the acquisition of analogy signal channel, digital signal conversion and receiving,power supply conversion, main control, Flash storage, trigger judgment and working mode selection, program debugging and downloading and USB interface communication module.
Then the software design is discussed in detail, which including the timing control of system,
receiving of multiple and uncertain-length serial port data, the realization of special
requirements for data encoding and storage, DMA transfer, Ping-pang receiving and storage
and USB communication procedure. The PC data reading and analysis software is also introduced. Finally, the analog channel signal calibration, functional testing method and actual flight test situation of the system are also illustrated.
The data acquisition and storage system designed in this thesis have been promoted in a certain kind of flight measurement system. After the analysis of the relevant live shell test result, it is manifested that the system designed basically lives up to the demands of related index, which is featured with small size, low power consumption, high reliability, overload resistant and high interference resistant.