为了满足高分辨率光谱仪高灵敏度、高分辨率、低噪声的技术要求,设计了用于微光成像系统的背照式CCD驱动电路及主控电路.线阵CCD采集系统采用Altera公司的MAX X系列FPGA作为核心控制器件,为线阵CCD提供多路驱动信号;线阵CCD探测器输出模拟信号经过信号预处理及AD采样,变换为数字信号后通过USB接口模块发送给光谱仪.通过将线阵CCD采集系统安装到高分辨率光谱仪,对汞灯谱线进行特征峰测试,光谱分辨率可以达到0.062 nm,满足高分辨率光谱仪的探测要求.

光电搜索跟踪系统是战场态势感知、信息获取、目标捕获、跟踪定位等武器装备的核心光电设备，其跟踪精度是表示光电搜索跟踪系统作战能力的关键参数。针对该参数的需求，提出了一种基于OLED发光的平行光管阵列式目标模拟器设计方案，其动态目标模拟角速度范围为1°/s～100°/s，角度定位精度为0.8″。对动态目标模拟器的角速度模拟进行了分析，得出角速度模拟的相对扩展不确定度可达0.6%～0.8%。

以西安石油大学干气密封装置为实验平台,选择常用的螺旋槽干气密封,分别在相同转速不同压力和相同压力不同转速的工况下,测量干气密封的泄漏量.通过分析得到转速和压力与干气密封泄漏量之间的关系,为干气密封的研究提供实验指导.

随着大气污染日益严重,工业烟气的脱硫已成为各大高排放企业的重要任务之一.本文对影响氨法脱硫效力的几个主要工艺参数进行了定性试验研究,得到了主要工艺参数变化与脱硫效力的关系,可为法脱硫工艺流程的优化及脱硫塔的设计提供参考.

The LOS drift caused by the earth’s rotation is a knotty problem to the tank fire control system. A LOS drift suppression method based on inertial system parameters is proposed. By virtue of the vehicle inertial system,geographic coordinates and attitude information of aiming mirror are obtained,and the earth rate components respect to the stabilized aiming mirror frame is calculated. A stabilized control system is used to control two directional channels by adding the respective compensations and then the influence of earth rotation is counteracted. As a result,in view of the observer,LOS is still following the goal and not need operator to manually fine-tune it. This method is not only suitable for tank combat training system,but also can be used in stabilized sighting device of shipboard or airborne system.

Aiming at the inherent disadvantage of inertial navigation system (INS )that the posi-tioning error are accumulated over time ,the method of compensating errors in INS /dead reck-oning(DR) integrated system was put forward .The main factors which begot errors in dead reckoning were analyzed ,and the positioning error equation was given ,then the Kalman filter was built for errors compensation of integrated system .The difference of velocity between INS and DR was used as the input of Kalman filter ,the attitude error ,velocity error ,positioning error and the scale factor error of odometer were to be estimated which compensated the errors of integrated navigation system by feedback closed loop rectification .Two non-closed paths were selected in verification experiments .The positioning error of the first path is 3 .49‰ and 2 .3‰ before and after compensation respectively .And that of the second path is 2 .4‰ and 2‰before and after compensation respectively .Experiment results indicate that the system posi-tion accuracy is improved effectively by dead reckoning compensation method .

For choosing right gyro and accelerometer to design a good strapdown inertial navigation system(SINS) according to its precision need ,a new error analysis method combining theory with engineer design experience was proposed .The functions of inertial sensor‐error ,velocity‐position error and attitude error under difference working conditions of SINS were set up .One method that for designing a SINS with the position‐error less than 100 m during 2 min was suggested .