Design And Implementation Of A Certain Missile-borne Multi-parameter Collection Storage Devices

Missile flight test is an important means of the overall performance test of the missile In order to obtain the system's internal state parameters and environmental parameter data of the missile during flight,Will need to install various sensors in the missile, and install data acquisition storage system as a black box, to record the system's work state, such as flight attitude,power supply, gas supply, measure, control and enforcement system, and to evaluate the missile's performance by the data.The Missile-borne multi-parameter acquisition storage device that described in this paper, is a Missile-borne test system.it adopt Storage Testing, FPGA(Field Programmable Gate Array)is the main control unit, use FLASH memory for storage, during the course of the missile launch and flight, to collect and storage environmental parameters such as vibration, overload, temperature and other as well as through the CAN bus to obtain digital information of the missile control system。After the flight test, to find FLASH memory, read data for later analysis.Paper focuses on its design and composition, and analyzes the key technology and difficult issues of the design of this missile-borne multi-parameter acquisition storage device, and puts forward the overall design proposal, mainly illustrates the software and hardware circuit design of the various parts of the data logger.For the problem of analog and digital data to be reliably stored in FLASH at the same time,the paper proposed the design of FPGA on-chip FIFO and the method of signal mixed-frame storage, it can reduce the system peripheral devices and improve system integration level. For the problem of the memory's reliable recovery, proposed separate memory module protection program. Minimized storage module design, and focused on their protection in structural design, ensured the effective recovery of recorded data.By means of the Ground reading device, can achieve itself and the host computer's USB bus data transfer. Combined with this system, the paper has done a comprehensive description of the EMC design from PCB layout, route, grounding, decoupling, filtering and the electromagnetic shielding. The results of the test of co-whole system shows that the system meets the Missile System's EMC requirements, it has been proved by the actual flight test.This paper describes functional test cases of this device in the end, and analyses the results. The results showed that this design in full compliance with mission requirements, high integration, easy operation, high resistance for overload and temperature and other characteristics, high reliability.