不同分散剂对纳米SiO_2水中分散的影响

选取六偏磷酸钠(SHMP)、十二烷基苯磺酸钠(SDBS)及KCl作分散剂,并采用超声分散方法,制备纳米SiO2悬浮液,对纳米SiO2的水中分散性能进行研究。测试分散体系中纳米SiO2粒子的粒径及分布、Zeta电位及透光率,探讨了不同分散剂对纳米SiO2分散性能的影响。结果表明:不同分散剂对纳米SiO2的粒径都有明显影响,但粒径分布宽度差别较大;同在分散粒径较小的条件下,分别添加3种分散剂的悬浮液体系具有不同的稳定性,其中含SDBS的分散体系因静电和空间位阻的作用而表现出良好的分散稳定性。     

基于Bayes方法的射击密集度评估

以某远程武器射击密集度鉴定问题为对象,研究了运用Bayes 理论从仿真试验数据中提取有用信息,从而实现在少量试验样本情况下有效完成射击密集度试验鉴定任务的方法.将最大熵法应用于射击密集度估计,介绍了运用自助(Bootstrap)法从仿真试验结果中获取验前信息的基本思想和一般方法,以及在获得验前信息后结合现场试验样本进行射击密集度鉴定的方法.     

武装直升机火箭弹对地攻击方式与散布的关系

根据某型武装直升机火箭弹对地靶试数据,计算了火箭弹弹着点的中间偏差,通过弹道计算反推出该机载武器系统的散布角,再由散布角计算了不同攻击方式下火箭弹的弹着点散布,得出了攻击方式与弹着点散布的关系,最后拟合出散布的通用计算式,为飞行员提供了一个如何选择武装直升机火箭武器对地攻击方式以形成所需散布的依据.     

武装直升机装备子母弹作战效能分析

提出了一种分析武装直升机作战效能的方法——概率分析法,并建立了机动目标坦克的数学模型,子弹散布模型,利用蒙特卡罗方法计算了子母弹杀伤概率Ｐ杀伤,并分析了影响武装直升机作战效能的相关因素。     

一种不精确推理模型与模糊关系代数

提出一种不精确推理的模型以及模糊关系代数,定义了模糊集合的并、交、差和笛卡尔积等运算,从而对非精确数据及知识描述中不确定性进行有效地处理。     

考虑验前信息可信度时的Bayes估计

研究了考虑验前信息可信度时的验前分布和Bayes估计算法,给出了正态总体参数的Bayes估计方法。以导弹落点散布的估计为例,说明了考虑验前信息可信度时Bayes估计有明显的改善,即具有更好的可信度。     

再入飞行器落点准确度的统计分析

本文研究再入飞行器的落点准确度(系统性偏差)的检验和估计方法。首先,文中引入了准确度的容许限的概念,在此基础上给出了Bayes验后加权概率比检验方法。关于落点系统偏差的估计,讨论了Bayes估计方法及带有约束的Bayes估计方法。文中注意了充分运用试验前的信息,以便使落点系统偏差的评估能在小子样场合下进行。     

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.     

MEFP战斗部结构的正交优化设计

以多爆炸成型弹丸(MEFP)为计算模型,应用显式有限元程序LS-DYNA,分析了药型罩间距、锥角、壁厚、装药高度和装药直径5种因素对MEFP发散角的影响规律。结果表明:随着药型罩间距、壁厚和装药直径的增加以及药型罩锥角、装药高度的减小,MEFP的发散角在减小。在此基础上以MEFP发散角为命中和毁伤概率指标,应用正交优化方法针对5种结构因素对MEFP发散角的影响主次关系进行了分析研究。结果表明药型罩壁厚是MEFP战斗部命中和毁伤概率的主要影响因素,并得到了5种结构因素各水平的最优组合。     

Q_2黄土调整吸力的非饱和三轴压缩试验研究

通过对Q2黄土进行调整吸力的非饱和三轴压缩试验,研究了浸水湿化程度对Q2黄土力学特性的影响。试验表明:不同浸水湿化程度的Q2黄土,其应力应变曲线为弱软化型,浸水湿化程度越高,软化程度越弱,浸水湿化至饱和时可近似看作理想硬化型;轴向应变较小时,Q2黄土的天然结构保持良好,应力随应变的增大而增大,随着轴向应变进一步增大,其天然结构逐渐被破坏,应力随之先缓慢上升后逐渐减小直至稳定;浸水湿化会同时引起土体应力状态和土体结构的改变,屈服应力随浸水湿化程度的提高而减小,在浸水湿化接近饱和时屈服应力变化最快,土体结构变化最大;形成年代早的Q2黄土细粒质量分数高,结构特征区别于Q3黄土,因而呈现出不同的力学特征。