多台同步可靠性增长模型存在的问题

探讨多台可靠性增长模型的统计意义,指出多台同步纠正可靠性增长试验丢掉了本可得到的大量的试验信息,失去了统计试验意义,其 AMSAA-BISE模型不能成立,多台同步试验方法不可取     

星载多光谱遥感器太阳定标技术的进展

星载多光谱遥感器的太阳定标器一般选择太阳作为基准光源 ,通过它将太阳辐射引入星载遥感器并调节到星载遥感器的动态范围内 ,对星载遥感器进行绝对辐射定标 ,也可对星载遥感器性能变化进行监测和校正。文章介绍一些最具代表性的星载多光谱遥感器的太阳定标器 ,并进行了分析 ,以反映太阳定标技术的现状与发展。目前采用太阳漫射器的星上定标方法可以实现全视场、全孔径、端点到端点的定标。这一方法的严重缺点是漫射器反射比随时间变化。为了解决这一问题 ,设计一种比辐射计或反射比标定装置来监测漫射器的辐亮度、反射比以及太阳常数。因此这种定标方法是很有前途的 ,在现代一些先进的星载多光谱遥感器上获得应用。通过对此方法的分析 ,提出了在太阳漫射器研制中的一些关键技术。     

车辆导航系统中超前滞后校正方法

分析了车辆导航系统中超前滞后产生的原因,提出了利用地图匹配MM(Map Matching)进行GPS(Global Positioning System)/DRS(Dead Reckoning System)组合导航系统超前滞后校正的方法.该方法是将超前滞后误差归结为GPS误差,先利用GPS沿道路垂直方向上误差的可观测性进行GPS误差校正,再将校正的GPS信息与DRS信息进行卡尔曼滤波,从而减少组合导航系统超前滞后误差.仿真结果表明上述方法是行之有效的.      

基于原始投影正弦图的X-CT硬化校正

在X射线层析成像(X-CT,X-ray Computed Tomography)技术中,X射线束能谱的多色性将导致层析重建图像出现杯状或条状等射束硬化伪迹,降低成像质量.在分析射束硬化现象具有的3个物理属性基础上,提出了一种对原始多色投影正弦图进行操作的硬化校正方法,并从数学上证明了其校正原理. 针对该方法带来的噪声放大问题,研究了一种基于高、低频信息分类处理的噪声抑制方法.计算机仿真和2种典型试件的实际CT扫描数据的硬化校正结果表明了该方法的有效性.与传统基于多项式拟合技术的校正法相比,该方法不需要事先进行建模扫描和计算,校正程序简单、实时,校正结果具有更高信噪比,且不受扫描条件限制.      

复杂外形气动力计算的阻力修正方法

基于气动力计算的位流线化理论,发展了一种亚音速附面层阻力修正方法。采用联合流场求解方法获得复杂外形的表面压力分布,在此基础上,将绕复杂外形物体沿流向面元划分为片条,在片条上,把三维附面层转换为二维附面层,对二维附面层进行数值求解,得到附面层粘性阻力修正。算例表明,该方法计算量小,与实验和N-S数值解结果吻合较好。为复杂气动外形飞行器初期设计、方案选型及评估提供了较为理想的工程设计手段。     

Comprehensive outage compensation of real-time orbit and clock corrections with broadcast ephemeris for ambiguity-fixed precise point positioning

The main challenge in real-time precise point positioning (PPP) is that the data outages or large time lags in receiving precise orbit and clock corrections greatly degrade the continuity and real-time performance of PPP positioning. To solve this problem, instead of directly predicting orbit and clock corrections in previous researches, this paper presents an alternative approach of generating combined corrections including orbit error, satellite clock and receiver-related error with broadcast ephemeris. Using ambiguities and satellite fractional-cycle biases (FCBs) of previous epoch and the short-term predicted tropospheric delay through linear extrapolation model (LEM), combined corrections at current epoch are retrieved and weighted with multiple reference stations, and further broadcast to user for continuous enhanced positioning during outages of orbit and clock corrections. To validate the proposed method, two reference station network with different inter-station distance from National Geodetic Survey (NGS) network are used for experiments with six different time lags (i.e., 5 s, 10 s, 15 s, 30 s, 45 s and 60 s), and one set of data collected by unmanned aerial vehicle (UAV) is also used. The performance of LEM is investigated, and the troposphere prediction accuracy of low elevation (e.g., 10–20degrees) satellites has been improved by 44.1% to 79.0%. The average accuracy of combined corrections before and after LEM is used is improved by 12.5% to 77.3%. Without LEM, an accuracy of 2–3 cm can be maintained only in case of small time lags, while the accuracies with LEM are all better than 2 cm in case of different time lags. The performance of simulated kinematic PPP at user end is assessed in terms of positioning accuracy and epoch fix rate. In case of different time lags, after LEM is used, the average accuracy in horizontal direction is better than 3 cm, and the accuracy in up direction is better than 5 cm. At the same time, the epoch fix rate has also increased to varying degrees. The results of the UAV data show that in real kinematic environment, the proposed method can still maintain a positioning accuracy of several centimeters in case of 20 s time lag.     

Correction method of airfoil thickness effect in hinge moment calculation of a folding wing

The influences of airfoil thickness on the aerodynamic loading distribution and the hinge moments of folding wing aircraft are presented in this work. The traditional panel method shows deficiencies in the calculation of folding wing’s hinge moments. Thus, a thickness correction strategy for the aerodynamic model with CFD results is proposed, and an aeroelastic flight simulation platform is constructed based on the secondary development of ADAMS. Based on the platform, the developed aerodynamic model is verified, then the flight-folding process of the folding wing aircraft is simulated, and the influences of airfoil thickness on the results are investigated. Results show that the developed aerodynamic model can effectively describe the thickness effect of the folding wing. Airfoil thickness, which cannot be considered by the panel method, has a great influence on the hinge moments during the folding process, and the thickness correction has great significance in the calculation of folding wing’s hinge moments.     

考虑星敏感器安装误差的弹道导弹捷联星光/惯性复合制导

弹道导弹捷联星光/惯性制导是在惯性制导基础上辅以星光修正的一种复合制导方法，能够显著提高导弹制导精度。由于星敏感器捷联安装在弹体上，安装误差会影响恒星测量的精度，进而影响复合制导精度，为此提出一种在线辨识并修正星敏感器安装误差的复合制导方法。建立了星敏感器观测量与数学平台失准角、星敏感器安装误差的关系方程，在导弹主动段关机后测量3颗独立的恒星获得6个观测量，利用最小二乘法估计出失准角和星敏感器安装、误差。改进了星光/惯性复合制导的最佳修正系数确定方程，直接修正了星敏感器安装误差的影响。数值仿真结果表明：所提方法可以有效地估计平台失准角和星敏感器安装误差，提高了捷联星光/惯性复合制导的精度。     

装备研制项目的模糊挣值管理方法

由于装备研制项目广泛存在着技术风险,其预算成本难以用确定数描述,而现有挣值管理技术通常用确定数描述项目费用基线,忽视了项目的技术风险因素。为此,将技术风险引入挣值管理(EVM)方法,提出了一种装备研制项目的模糊挣值管理(FEVM)改进方法。该方法充分考虑了装备研制中的技术风险问题,利用技术成熟度(TRL)对项目计划成本进行估算,在此基础上,利用模糊数学理论,给出了一种基于可能度的高风险项目的成本和进度的模糊评价标准,并对项目的完工成本(ECC)和完工时间(ECT)进行了模糊预测。最后,通过案例对文中的方法进行了阐述。该方法针对装备研制项目技术风险大的特点,进一步拓展了挣值管理的适用性,对于决策者控制风险、保证项目的费用和进度具有一定指导意义和参考价值。     

基于修正面元法的机翼焦点位置变化研究

针对静气动弹性问题中机翼焦点位置求解精度与效率的矛盾,提出采用分段斜率修正面元法来计算气动力,该方法以刚体机翼在不同迎角下的CFD数据作为修正基础,对弹性变形后的机翼下洗采用分段修正,克服了传统面元法无法考虑非线性因素的缺点。通过M6机翼气动焦点位置的计算表明:相对于CFD方法,该方法保持了较高的准确度并且计算效率较高;相对于传统面元法,该方法能够准确地计算焦点位置和弹性机翼焦点位置变化量,适用于工程设计。