基于网络理论的体系作战能力建模

在分析信息化体系作战能力"跃迁"特征的基础上,进行了作战体系的网络化结构建模分析;研究了感知网络、指控网络以及执行网络能力模型,构建了基于网络理论的体系作战能力综合模型。结合仿真算例分析,探讨了体系信息结构力的产生机理,为体系作战能力综合研究提供了借鉴和支撑。     

轮胎侧偏特性对汽车前轮角阶跃输入瞬态响应影响的研究

为了分析轮胎侧偏刚度对汽车前轮角阶跃输入下车身横摆角速度瞬态响应的影响,建立汽车运动的二自由度平面模型,解析分析了轮胎侧偏刚度对瞬态响应的影响。利用在ADAMD/Car中建立的整车模型进行仿真试验验证,解析分析结果与虚拟试验基本相符,得出适度增大后轮侧偏刚度,有利于提高汽车转向时的操纵稳定性的结论。     

油品管输带电问题

以油品管输带电问题为专题,参考大量国外文献,结合笔者近年的研究,以便于石油储运工程技术人员掌握、应用和研究为目的,阐明油流带电的原因是油品与管壁接触后产生双电层,油流带走扩散层中的电荷形成冲动电流;论述冲动电流大小与油品物性、管道结构、油流速度等因素的关系;指出金属管道接地可消除管壁电荷、防止电荷聚积,但不能导走油流里的电荷;说明绝缘管道的要害是管壁会聚积电荷,可能导致刷形放电和击穿放电,缩短管子寿命,危及管输安全。     

高速数字电路信号完整性设计

随着电子产品日愈复杂,电路板工作频率不断提升,从而导致信号完整性问题。从工程应用角度阐述了高速电路的概念,列举了典型的信号完整性问题,如反射、串扰、电源和地噪声、定时等,提出信号完整性设计中所应遵循的设计方法,如控制走线长度、特征阻抗控制与计算,仿真技术等,并讲解了真实的设计案例,具有工程应用实际参考价值。     

扩张状态观测器的观测误差前馈补偿设计

在"总和"扰动模型未知的前提下,针对线性扩张状态观测器跟踪时变信号精度不高的问题,设计出一种前馈观测补偿器。在分析线性扩张状态观测器观测原理的基础上,通过对扰动项的线性近似、误差系统动态响应的忽略,在时域内推导出观测静差的量化表达式,进而使用扰动微分项的估计值替代真值对观测作前馈补偿。理论分析了替代的可行性,证明了补偿器减小观测误差幅值、超前校正观测相位滞后的作用。将这一补偿思想推广至非线性扩张状态观测器中。通过仿真对补偿器提高观测精度、加快误差收敛的有效性进行检验,实验结果进一步表明,补偿器的引入能显著提高整个自抗扰控制系统的控制精度,从而证明了这种补偿思路的可行性。     

SpaceWire网络混合路由机制设计

针对星上系统总线多元性导致的星载网络接口和协议不能标准化的发展瓶颈,基于SpaceWire总线协议,通过将静态路由(时间触发)与动态路由(事件触发)机制结合,实现了控制数据和载荷数据共用网络。静态路由完全遵循SpaceWire-D协议,在保证确定性传输的同时,通过启发式调度算法首次实现了多时间窗并行调度,并提出利用最大公约数法设计时间窗,以提高网络吞吐量;动态路由通过对随机事件和载荷数据分配优先级,实现传输路径冲突时对紧急任务的优先处理。在OPENT中搭建网络系统仿真模型,对所提出的路由机制进行了仿真。实验结果表明,静态路由时段网络吞吐量较现有调度算法有明显提高,动态路由实现了紧急事件优先传输。     

二次流引射对保形非对称喷管性能的影响

发动机与飞机后体结构设计合理与否直接影响发动机的部件匹配和性能。利用三维雷诺平均N-S方程和k-ωSST湍流模型对飞翼布局无人机保形非对称喷管在典型飞行状态下开展了内外流流场特性的数值分析,获得了后体尾喷管推力性能和三维流动特征随二次流压力比的变化趋势。结果表明:发动机喷管落压比条件一定的前提下,通过合理优化二次流通道、增大二次流压力比,可以有效改善后体/喷管主流流场特性;当二次流与主流的流量比在0. 2%～1. 86%内时,后体尾喷管轴向推力系数的变化幅度大约为3%,在一定程度上能够减弱发动机主流的过膨胀程度,减小发动机推力损失,无人机后体尾喷管性能得到显著提高。     

认知域的公域特性及其关键技术

伴随着“认知域”作战概念被引入军事领域,现代战场已经形成了物理域、信息域、认知域三大作战维度。认知域已经成为美国战略空间拓展的主要战场之一。按照习主席关于要打好意识形态领域“制脑权”战争的思想,更需要重视认知域的攻防,研究相关技术,才能在没有硝烟的战场上不落下风。     

Experimental research on the instability propagation characteristics of liquid kerosene rotating detonation wave

In order to study the instability propagation characteristics of the liquid kerosene rotating detonation wave (RDW), a series of experimental tests were carried out on the rotating detonation combustor (RDC) with air-heater. The fuel and oxidizer are room-temperature liquid kerosene and preheated oxygen-enriched air, respectively. The experimental tests keep the equivalence ratio of 0.81 and the oxygen mass fraction of 35% unchanged, and the total mass flow rate is maintained at about 1000 g/s, changing the total temperature of the oxygen-enriched air from 620 K to 860 K. Three different types of instability were observed in the experiments: temporal and spatial instability, mode transition and re-initiation. The interaction between RDW and supply plenum may be the main reason for the fluctuations of detonation wave velocity and pressure peaks with time. Moreover, the inconsistent mixing of fuel and oxidizer at different circumferential positions is related to RDW oscillate spatially. The phenomenon of single-double-single wave transition is analyzed. During the transition, the initial RDW weakens until disappears, and the compression wave strengthens until it becomes a new RDW and propagates steadily. The increased deflagration between the detonation products and the fresh gas layer caused by excessively high temperature is one of the reasons for the RDC quenching and re-initiation.     

Characteristics structure analysis on debris cloud in the hypervelocity impact of disk projectile on thin plate

In this paper, the gauge points setting is introduced in the SPH simulation to analyze the debris cloud structure generated by the hypervelocity impact of disk projectile on thin plate. Compared with the experiments, more detailed information of the debris cloud structure can be classified from the numerical simulation. However, due to the solitary dispersion and overlap display of the particles in the SPH simulation, accurate comparison between numerical and experimental results is difficult to be performed. To track the velocity and spatial distribution of the particles in the debris cloud induced from disk and plate, gauge points are locally set in the single-layer profile in the SPH model. By analyzing the gauge points’ spatial coordinate and velocity, the location and velocity of characteristic points in the debris cloud are determined. The boundary of debris cloud is achieved, as well as the fragments distribution outside the main structure of debris cloud.