运载火箭随机振动环境试验条件的变带宽设计方法

针对运载火箭随机振动环境试验条件提出了基于能量等效思想的变带宽设计方法,通过采用分数倍频程数据处理方法,并确保各个频带内的均方根值与原随机振动环境的均方根值相同,有效解决传统的等带宽随机振动环境试验条件总均方根过高的问题。为了验证所提方法的有效性,通过典型管路产品进行了随机振动响应计算。结果表明,该方法既能够有效地对产品进行考核,又不至于对产品造成过考核。所提变带宽设计方法可为运载火箭随机振动环境条件的合理设计与分析提供有效手段。     

自动变速车辆换挡规律的研究

研究了自动变速车辆的换挡规律的算法,制定了车辆的动力性换挡规律和经济性换挡规律,建立了车辆动力学仿真模型.通过仿真,分析了不同换挡规律对车辆性能的影响.     

装甲车辆远程故障诊断技术

基于网络的远程故障诊断是诊断系统的发展趋势,在论述远程故障诊断的基本概念、优势及关键技术的基础上,提出了构造装甲车辆远程故障诊断系统的总体框架结构和工作模式,阐述了系统实施的可行性及在部队应用的重大意义.     

高空长航时无人机编队协同侦察任务规划

针对高空长航时无人机侦察任务规划特点,分析了高空长航时无人机执行侦察任务过程中的飞行航线约束和通信条件约束,以最小化无人机总飞行航程和最终编队飞行时间为优化目标,建立无人机编队协同侦察任务规划问题模型。同以往的通用侦察任务模型相比,该模型突出考虑了高空长航时无人机执行侦察任务过程的特点。以基本粒子群算法为基础,通过粒子群离散化和结合遗传算法进行改进,使其适用于求解复杂组合优化问题。仿真结果验证了算法求解复杂任务规划问题的有效性。     

基于公共燃气排导结构的共架发射系统武器选择与布局方法

公共燃气排导结构和同心筒结构的共架发射系统由于燃气排导机理不同,其对武器发射的影响及在武器选择、布局等方面均存在较大差异.针对公共燃气排导结构的共架发射系统分析了公共燃气排导对武器发射的影响,提出了武器选择与布局方法,通过算例进行了验证并得出结论:公共燃气排导结构的共架发射系统武器布局上应采取分散布局,武器选择上应优先选择“无发射活动、对应武器数量较多、烧蚀值较小”的模块,且按照模块编号依次交替在不同模块进行武器发射.     

战场环境下无人车辆战术机动路径规划方法

针对不同类型威胁体存在的战场环境中无人车辆战术机动路径规划问题,提出了一种基于威胁代价地图的粒子群优化（Particle Swarm Optimization,PSO）方法。借助极坐标系中关键点的极角进行路径描述,并使用分段3次Hermite插值方法形成光滑路径,将路径规划问题转化为关键点极角的参数优化问题。针对基本PSO（BPSO）算法存在的早熟收敛和后期迭代效率低的缺陷,借鉴以群集方式生活的物种按照不同任务对种群进行分工的机制,提出了一种基于多任务子群协同的改进粒子群优化（Particle Swarm Optimization based on the Multi—tasking Subpopu—lation Cooperation,PSO-MSC）算法。借助该算法的快速收敛和全局寻优特性实现了最优路径规划。实验结果表明：该算法可以快速有效地实现战场环境下无人车辆的战术机动路径规划,且规划路径安全、平滑。     

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.     

A novel launch dynamics measurement system for multiple launch rocket system and comparative analysis with numerical simulations

In this paper,a novel launch dynamics measurement system based on the photoelectric sensor pair is built.The actual muzzle time(i.e.a time duration that originates from the initial movement to the rocket's departure from the muzzle)and the muzzle velocity are measured.Compared with the classical methods,the actual muzzle time is obtained by eliminating the ignition delay.The comparative analysis method is proposed with numerical simulations established by the transfer matrix method for multibody systems.The experiment results indicate that the proposed measurement system can effectively measure the actual muzzle time and reduce the error of classical methods,which match well with the simulation results showing the launch dynamics model is reliable and helpful for further analysis and design of the MLRS.     

电磁装甲技术研究综述

介绍了电磁装甲的种类、防护原理以及国内外的研究状况 ,阐明了电磁装甲的特点及其应用前景 ,最后提出了我国进行电磁装甲研究的思路     

基于ADAMS软件的轮式车操纵稳定性仿真分析

为了更好地设计评价轮式车辆的操纵稳定性,利用ADAMS软件进行仿真建模分析,再依照相关国家标准进行评价得到客观结论。在汽车设计、评价过程中广泛应用ADAMS软件可以在设计前期对车辆性能进行预测,提高设计质量,缩短设计周期。