基于BP 网络与D-S理论相结合的点目标状态下卫星及其伴飞诱饵的识别方法

本文提出的点目标状态下卫星及其伴飞锈饵的识别方法是基于ＢＰ网络与Ｄ－Ｓ理论相结合的信息融合方法。该方法采用目标的红外辐射特征,先用ＢＰ网络对目标进行粗分类,然后用Ｄ－Ｓ理论对ＢＰ网络的多次识别结果进行融合。仿真实验结果表明,Ｄ－Ｓ理论的最后输出比ＢＰ网络的输出识别率得到很大的改善,抗噪能力得到很大的提高     

铝合金薄板表面裂纹弹塑性断裂测试中的两个实验技术

近几年,我们开展了LD10cs 铝合金贮箱表面裂纹弹塑性断裂课题的实验研究。为了得到满意的实验结果,在测试技术上做了一些探讨。本文着重介绍两个实验技术:1.采用夹具代替粘接刀口,配合弓形位移传感器自动绘制P—V 曲线,不但结构简单、使用方便;更为可取的是,由于标距的缩小,提高了P—V 曲线的质量。2.具有很深表面裂纹的贮箱,受载时,容器往往产生先“泄漏”后“断裂”的情况。因此,准确地测定泄漏载荷并研究泄漏发生的条件,是很重要的。在国外对平板试件有的采用压力密封罩的方法测定泄漏载荷,其测试方法较为复杂,在实际结构上应用也是比较困难的。我们将电阻丝片作为敏感元件,配合简单的开关线路测定泄漏载荷,较好地解决了这个问题。     

微分对策在动态评价舰艇作战能力中的应用

作战能力是表征战斗舰艇战术技术性能的一项重要指标,如何正确评价舰艇的作战能力一直是舰载武器系统配置研究的重点,也是军事系统工程的重要研究方向。该文应用微分对策理论提出了一种动态评价舰艇作战能力的思想,首次定量研究了舰艇机动性与舰炮武器系统毁伤概率之间的关系,为综合评价舰艇的作战能力提供了一条可行途径。     

关于机器人力控制器计算机系统的设计方案探讨

本文从机器人力反馈依从控制的任务和要求出发,对机器人控制多处理机系统设计中的几个主要问题,包括总的系统结构、存储器结构、机间互连结构、中断系统结构、并发实时操作系统、处理机选型和多处理机系统的调试等,进行了探讨。     

一种有价值的预防维修策略

当前,在系统的维修性方面,有许多概念是模糊的;许多行为是盲目的,至少是经验主义的。本文针对这些情况,提出了完整的科学维修的概念。以一个有使用价值的预防性维修策略为例,通过讨论,使这种科学维修的概念具体化,并且给出了系统的首翻期、维修周期以及更换期的严格定义和确定方法。     

常规袭击下指挥所生存能力分析

在现代战争中,指挥所是作战部队的核心设施,其生存能力对战争进程和战争胜负有着根本性的制约作用,也成为敌方的首要攻击对象。当前,指挥所的生存能力已经成为各级指挥员极其关注的问题。针对指挥所面临的威胁,分析制约其生存能力的因素,找出有效的应对之策,对作好军事斗争准备将有着重要意义。从指挥所可能面临的常规袭击环境出发,探讨了影响指挥所生存能力的因素,建立了各种袭击模式下的生存能力模型,并应用模拟的方法对指挥所生存能力进行了定量分析,并结合定性分析得出了有益的结果。     

基于灰局势决策理论的维修级别分析方法

简要介绍了某型无人机维修级别分析及灰局势决策理论的一般概念,针对传统维修级别分析中经济性分析的数据来源广、模型可信度较差的情况,研究基于灰局势决策原理建模的一般方法,通过筛选原始数据并修正计算公式,大大减少了冗余计算,最后运用这一模型对某机载无线电设备进行了经济性分析。     

基于智慧校园建设推进军队院校教育现代化路径探究

教育信息化是教育现代化的基本内涵和显著特征。当前,我国正处于由基本实现教育现代化迈向整体实现教育现代化的重要战略期,国家教育从理论和实践层面进行了大量探索。在军队院校教育领域,教育技术应用、训练管理领域网络建设、数字校园建设等均为军队院校教育现代化奠定了创新发展基础,智能教育应用模式的改革探索也为军队院校教育现代化描绘了未来建设愿景。本文认为,推进军队院校教育现代化应发挥智慧校园建设平台的基础作用,充分融入国家教育体系,注重以先进教育理念驱动创新发展、以前沿信息技术提供解决方案、以总体架构设计规范目标功能、以智慧育人环境承载应用服务、以数据资源体系孕育智慧生态,走开军委军种院校三级联动推动创新发展的路子。     

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.     

Pressure relief of underground ammunition storage under missile accidental ignition

Safety of underground ammunition storage is an important issue, especially during the accidental ignition of missiles. This work investigates the pressure and temperature distribution of the multi-layer underground ammunition storage with a pressure relief duct during the accidental ignition process of the missile. A large-scale experiment was carried out using a multi-layered restricted space with a pressure relief duct to simulate the underground ammunition store and a solid rocket motor to simulate the accidental ignition of the missile. The results show that when the motor gas mass flow increased by 5.6 times, the maximum pressure of the ammunition storage increased by 5.87 times. At a certain motor flow rate, when the pressure relief exhaust area at the end of the relief duct was reduced by 1/2, the maximum pressure on the first layer did not change. But the rate of pressure relief was reduced and the time delayed for the pressure of ammunition store to drop to zero. In this experiment, when the motor ignition position was located in to the third layer ammunition chamber, the maximum pressure was reduced by 32.9％ and also reduced the rate of change of pressure. In addition, for the experimental conditions, the theoretical analysis of the pressure relief of the ammunition storage is given by a simplified model. Based on the findings, some suggestions to the safety protection design of ammunition store are proposed.