引信与武器系统的适配性分析

引信是弹药武器系统的重要子系统,引信只有与其它子系统多方面适配,才能充分发挥武器系统的效能。通过分析引信与武器系统中其它子系统之间在任务与功能、信息的利用与传输、能源、材料与结构等方面的适配关系,提出了设计中引信与战斗部、火控、制导等子系统间的适配关系,并采用适配性方法设计引信。     

二维抛板极限速度的相似性与古尼公式的采用

本文分析影响被炸药驱动下抛板极限速度的重要因素,讨论了一些经验公式的适用范围;提出了根据二维抛板的数值计算得到的两个重要规律:①在炸药与抛板的质量比相同的情况下,抛板的极限速度之间具有一定的相似关系;②修正的古尼公式可用来计算二维抛板的极限速度。     

关系抽取中远监督错误标注消除

目前远监督方法被广泛应用于关系抽取任务。然而,远监督方法中存在大量错误标注现象,给远监督方法的学习效果带来了很大的影响。提出利用语义Jaccard度量关系短语与依存词间语义相似性的错误标注消除方法。消除错误标注后的训练数据用于训练模型,完成关系抽取。实验结果表明:该方法可以有效消除错误标注,提高关系抽取的性能。     

基于灰色关联的目标识别模型

在分析研究空中目标特征指标的基础上,提出并建立了基于灰色关联的目标识别模型。通过实例说明,利用该方法进行目标识别简单、有效。     

基于Vague集模糊值线性序法的雷达抗干扰效能评估

针对已有评估方法存在的不足,提出了一种基于Vague集模糊值线性序法的雷达抗干扰效能评估方法。分析了影响雷达抗干扰效能的指标因素,给出了各评价指标的模糊值表示,建立了基于Vague集模糊值线性序法的雷达抗干扰效能综合评价模型,得到了评价其效能的排序方法。最后通过实例分析验证,该方法评估结果准确,具有一定参考价值。     

空空协同作战指挥控制系统

论述了研究与发展空空协同作战指挥系统的必要性 ,探讨了空空协同作战指挥系统的概念及系统的建模、结构模式 ,指挥决策的制定与优化、人机关系的处理、作战效能的评估与通讯共享集等几个问题     

均匀设计法在建立PELE爆裂效应关系模型中的应用

为了研究钢壳体PELE爆裂效应与影响因素之间的数学关系,对钢壳体PELE侵彻钢板进行了数值仿真和试验。采用均匀设计法设计仿真工况,将仿真结果进行回归分析,得出爆裂效应与影响因素之间的数学关系式,实弹侵彻实验结果与仿真结果基本吻合。研究表明,影响因素均与壳体爆裂长度成非线性关系,增大靶板厚度、弹芯长度和着速或减小壳体厚度均有利于提高钢壳体的爆裂效应。相关结论为PELE的工程设计和应用提供了理论基础。     

鲁迅与魏晋南北朝诗歌

鲁迅以魏晋诗人的人格理想对诗性精神的影响为思考脉络,来考察这一时期的文化风貌之于诗歌的意义,并用“魏晋风度”来概括。在精神文化传承上,鲁迅和魏晋诗人都对酒情有独钟,借助于酒文化获得精神上的超越。在艺术创作上,鲁迅诗歌与魏晋南北朝诗歌都有着沉郁、苍劲的特点,也都呈现出率真自然的风格。     

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。     

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.