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MX导弹测试系统多路复用器组合用于采集导弹飞行试验的测量数据。多路复用器组合包括一个多路复用器编程控制单元(MU)、2至32个远置多路复用单元(RU)以及若干个电源检查单元(PSV)。 MU的主要用途是作为可编程序的系统控制器,接收本地输入数据并将这些数据与来自RU的数据一道编成PCM的格式输出。RU通过指令和应答数据总线与MU相接口,进行远距离数据采集。PSV为模拟信号源提供精确的激励电压并控制模拟信号的偏移以进行校验检查。 32个RU中有31个通过飞行器上的两对数据总线与MU相接,余下的1个RU经脐带或数据总线接到飞行器。这个留在地面上的RU与飞行器上的相同,但对其功能要求却完全不同。它主要用来装入并校验MU程序。飞行器上的每条数据总线最长可达130英尺,脐带总线最长为250英尺。MX导弹无法使用理想的终端负载总线,因为导弹分离时总线的配置要改变。级间分离时电缆将发生开路或短路。为保证总线上剩余的RU正常工作,接口隔离变压器绕有电流和电压绕组以提供最大的次级信号电平而反射失真最小。数据总线使用Manchester Ⅱ型码,工作频率为3.2MHz。 MU可对160个本地差分模拟信道进行采样,增益与偏移可编程,最大采样率为170,665次/秒。由96个离散通道中可以编程的灵活组合方式取出8路离散输入,采样率可达每秒51,200次。MU还可以接受4路串行数据通道的数据并提供向8条命令通道的输出。命令可在飞行前从地面发出,发射后这些命令按时间事件驱动的方式编程,同时也按在两种工作之间来回重复的格式编程。PCM码速率为1.6Mbps。MU在16位4096字的CMOS RAM存贮器中存贮5种格式供飞行中选用。每个RU可访问28条模拟通道和8条数字通道,并可控制2条命令通道和6条检验通道。PSV不同数据总线相连,对它的控制通过MU或RU命令通道执行。系统可由外部同步或按内部时钟工作,传送方式经过仔细考虑,从而减少数据丢失。系统主要特点是体积小、重量轻、功耗低和可靠性高。弹内装载的监测器和计算机控制的全自动测试设备提供了快速和可观的参数检测手段,从而在很大程度上减少了故障。
MX missile test system multiplexer combination for acquiring measurement data from missile flight tests. Multiplexer combinations include a multiplexer program control unit (MU), 2 to 32 remote multiplex units (RU), and several power-check units (PSVs). The main purpose of the MU is to act as a programmable system controller to receive the local input data and output the data in PCM format along with the data from the RU. RU through the command and response data bus and MU phase interface for long-distance data acquisition. The PSV provides an accurate excitation voltage for the analog signal source and controls the offset of the analog signal for verification. Thirty-two out of thirty-two RU are connected to the MU through two pairs of data buses on the aircraft and the remaining one RU to the aircraft via the umbilical or data bus. The RU that stays on the ground is the same as on the aircraft, but its functional requirements are quite different. It is mainly used to load and verify the MU program. Each data bus on the aircraft can be up to 130 feet and the umbilical can be up to 250 feet. MX missiles can not use the ideal terminal load bus, because the bus configuration to change the missile separation. The cable will be open or shorted during interstage separation. To ensure that the remaining RU on the bus is working properly, the interface isolation transformers are wound with current and voltage windings to provide the maximum secondary signal level with minimal reflection distortion. The data bus uses Manchester II type code, the working frequency is 3.2MHz. The MU samples 160 local differential analog channels with programmable gain and offset, with a maximum sample rate of 170,665 bps. Eight channels of discrete input are available in a flexible, programmable combination of 96 discrete channels at 51,200 samples per second. The MU also accepts data from 4 serial data channels and provides output to 8 command channels. Commands can be issued from the ground prior to flight, programmed in a time-event-driven manner after launch, and also programmed in a repetitive format between the two jobs. PCM code rate of 1.6Mbps. The MU stores five formats for use in flight in 16-bit, 4096-word CMOS RAM memory. Each RU can access 28 analog channels and 8 digital channels, and can control 2 command channels and 6 test channels. PSV different data bus connected to its control through MU or RU command channel implementation. The system can be synchronized externally or by an internal clock, with careful consideration of the delivery method to reduce data loss. The main features of the system are small size, light weight, low power consumption and high reliability. The on-board monitor and computer-controlled fully automated test equipment provide fast and predictable parameter detection to a large extent reduce malfunctions.