C~2系统的信息论建模

该文论述了基于信息论的信息处理组织与决策组织的建模与分析方法。首先介绍了用于决策者建模的基本图示工具Petri Net 和基本数学工具信息划分定律。然后介绍了用上述工具建立起来的单个决策者和决策组织的数学模型,而后又评述了分析决策组织结构的方法,说明了该领域的研究状况,最后对这一研究的应用前景作出了分析。     

二维带限信号代数正则外推算法

用代数正则化方法直接将连续的数学模型离散化,然后用Tikhonov正则化方法求解代数方程组,构造稳定的正则化算法,并进行数值仿真,结果是满意的。     

武器精度截尾SPOT 检验最大风险计算

就正态圆分布的武器命中精度的截尾序惯验后加权检验犯两类错误概率上界的计算问题,指出了目前沿用的计算公式的错误,推导了新的计算公式,并给出了算例,分析了计算结果的合理性;同时,指出了目前截尾点选取方法存在的问题     

混合物薄膜折射率与膜孔洞率关系研究

本文对TiO_2和Ta_2O_5混合膜进行了单源共蒸发实验研究。在实验结果的基础上,提出了一个拟合TiO_2、Ta_2O_5混合膜系孔洞率的经验公式,并对混合膜的折射率的计算过程进行了改进。结果表明:理论计算与实验数据符合较好;混合物薄膜可能形成孔洞率较小的膜层,从而导致混合物薄膜折射率随混合百分比的变化曲线出现峰值。     

基于面向对象技术的载人长征二号F应急救生半实物仿真系统

概要介绍了基于面向对象技术的长征二号F火箭应急救生半实物仿真系统的组成和应用.     

WINDOWS系统中的QoS保障机制研究

针对微软提出的常规服务质量(GeneralQualityofService,简称GQoS)的QoS解决方案,讨论了WINDOWS系统中的QoS保障机制。通过WINSOCK2的API函数设计程序,进行了Win98上的QoS性能测试。结果表明,在QoS启用的情况下,数据的传输时间和延迟抖动明显减小,说明WINDOWS系统中的QoS保障机制有效。     

Sr2FeNbO6的晶体结构

系统地研究了Sr2FeNbO6的晶体结构,并利用步进扫描的X光数据成功地确定了Sr2FeNbO6的晶体结构,利用Rietveld方法精修出Sr2FeNbO6是空间群为Pnma(62)的正交结构,其中,晶胞参数分别为a=5.616 1A,b=7.971 7A,c=5.613 0A.     

The effect of al particle size on thermal decomposition,mechanical strength and sensitivity of Al/ZrH2/PTFE composite

To study the thermal decomposition of Al/ZrH2/PTFE with different Al particle size as well as mechanical strength and impact sensitivity under medium and low strain rates, molding-vacuum sintering was adopted to prepare four groups of power materials and cylindrical specimens with different Al particle size. The active decomposition temperature of ZrH2 was obtained by TG-DSC, and the quasi-static me-chanics/reaction characteristics as well as the impact sensitivity of the specimen were studied respec-tively by quasi-static compression and drop-hammer test. The results show that the yield strength of the material decreased with the increase of the Al particle size, while the compressive strength, failure strain and toughness increased first and then decreased, which reached the maximum values of 116.61 MPa, 191％, and 119.9 MJ/m respectively when the Al particle size is 12—14μm because of particle size grading. The specimens with the highest strength and toughness formed circumferential open cracks and reacted partly when pressed. Those with developmental cracks formed inside did not react. It is considered that fracture of specimens first triggered initial reaction between Al and PTFE to release an amount of heat. Then ZrH2 was activated and decomposed, and participated in subsequent reaction to generate ZrC. The impact sensitivity of the specimens decreased with the increase of Al particle size.     

Dynamic necking of a near α titanium alloy at high strain rates:Experiments and modelling

The tensile behaviour of near α Ti3Al2.5 V alloy, conceived for applications in aerospace and automotive engineering, is characterized from quasi-static to high strain rates. The material is found to present noticeable strain rate sensitivity. The dynamic true strain rate in the necking cross-section reaches values up to ten times higher than the nominal strain rate. It is also observed that beyond necking the dynamic true stress-strain curves present limited rate dependence. The experimental results at different strain rates are used to determine a suitable constitutive model for finite element simulations of the dynamic tensile tests. The model predicts the experimentally macroscopic force-time response, true stress-strain response and effective strain rate evolution with good agreement.     

Supercritical carbon dioxide as a new working medium for pneumatic launch: A theoretical study

Compared with the conventionally gaseous or liquid working media, the specific internal energy of supercritical carbon dioxide (SCD) is higher at the same temperature and pressure, and the critical temperature of carbon dioxide is close to room temperature, making SCD a potential new working medium for pneumatic launch. To analyze the feasibility of this conception, an analytical model of a pneumatic catapult is established on basis of the conservations of mass and energy. The model consists of a high-pressure chamber and a low-pressure chamber connected by multiple valves, and there is a movable piston in the low-pressure chamber that can push an aircraft to accelerate. The effects of the launch readiness state of SCD in the high-pressure chamber, the initial volume of the low-pressure chamber and the valve control on the movement of the aircraft are analyzed. It is found that there is a restrictive relation between the temperature and pressure of the launch readiness state of SCD, i.e., there is a maximum allowable launch readiness pressure when the launch readiness temperature is fixed. If this restrictive relation is not satisfied, the working medium in the low-pressure chamber will drop to its triple point within a few milliseconds, leading to a launch failure. Owing to this restrictive relation, there is an optimal launch readiness state of SCD with the highest working capacity for any allowable launch readiness temperature. The pressure of the low-pressure chamber will decrease significantly as the initial volume increases, leading to a decreased acceleration of the aircraft. The ac-celeration can be controlled below a critical value by a designed sequential blasting technique of multiple valves. The calculated results show that a 500 kg aircraft can be accelerated from 0 to 58 m/s in 0.9 s with 36 kg of carbon dioxide. This research provides a new technique for the controllable cold launch of an aircraft.