载荷识别及其精度改善

本文系统地建立了载荷识别方法,详细探讨了提高载荷识别精度的途径,得到了载荷识别过程中信号处理加窗原则和试验的一般技术要求,使识别精度明显提高。     

潜艇承载力分析和动力抗沉操纵方法研究

在分析潜艇受力的基础上,根据潜艇的操纵规则,给出承载力的计算方法,分析了影响潜艇承载力的因素,设计了一套用于指导潜艇动力抗沉操纵的承载力图谱.以某一假想潜艇为例,说明了承载力图谱的绘制和使用方法.     

载荷分布对六自由度运动平台动力学性能的影响

用Newton-Euler方法,分析了运动平台的力矢和力矩,建立了统一的六自由度运动平台动力学方程。利用该方程研究了不同载荷分布时六自由度运动平台各液压缸的受力情况,并用Matlab进行了计算。结果表明,不同载荷分布时,某些液压缸的驱动力的最大值成倍增加,变化极为复杂,为六自由度运动平台的设计及控制提供了理论指导。     

传统的方位定义应用局限性研究

本文分析了传统的方位定义与计算存在的应用局限性根源,提出了适合航海及各种规模军事演练需求的改进的方位定义和计算方法,并分析了两种方位定义下的方位计算误差及适用条件.     

Interval uncertain optimization for damping fluctuation of asegmented electromagnetic buffer under intensive impact load

Aiming at the problems of demagnetization effect of electromagnetic buffer (EMB) caused by high ve-locity under intensive impact load and the difficulty and error of machining composite thin-walled long tube, a segmented EMB is proposed. The inner tube and air-gap are divided into initial segments and the traversing segments. Through theoretical analysis, impact test and simulation, it can be found that the RRF curve has two peaks. Firstly, in order to reduce the resultant resistance force (RRF) peaks, the sensitivity analysis based on optimal Latin hypercube design (OLHD) and polynomial regression was performed. The results show that the smallest contribution ratio to the dynamic response is the seventh and ninth segments of the inner tube, which are less than 1％. Then, fully considering the uncertain factors, important parameters are selected for uncertain optimization after sensitivity analysis. The in-terval order and interval probability degree methods are used to establish interval uncertain optimiza-tion model of the RRF considering robustness. The model was solved using an interval nested optimization method based on radial basis function (RBF) neural network. Finally, the Pareto front is obtained and numerical simulation is performed to verify the optimal value. It indicates that the two kinds of RRF peak is obviously reduced, and the optimization object and strategy are effective.     

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.     

钢管初应力对方钢管混凝土构件性能的影响研究

在14根方钢管混凝土构件试验的基础上,分析了初应力系数、荷载偏心率、混凝土强度、试件长细比等因素对承载力的影响,给出了钢管初应力对方钢管混凝土压弯构件承载力的影响系数,采用ANSYS有限元分析程序进行了非线性全过程分析.     

Unpacking the various meanings of redundancy: from refining the concept to military planning

The authors engage in the debate over waste in military force structure planning by rigorously deconstructing the concept of “redundancy.” First, a typology of redundancy is constructed that provides a common framework for identifying variety among redundant structures. These are labeled “true redundancy,” “expanded capacity,” “portfolio diversification,” and “mission overlap.” Further, a number of mechanisms are identified that produce these types of structures, and show the conditions under which planners may utilize redundant structure in the search for optimization. In sum, the article provides refined concepts for analysts and planners to identify when redundancy is deleterious or beneficial.     

带宽受限下频谱分离对提高RDSS入站容量的影响分析

用户入站容量是RDSS系统设计的一个重要指标,主要受限于入站信号之间的多址干扰.提高扩频码速率可以增加人站容量,但卫星转发器带宽限制了扩频码速率的最大值,从而限制了单个扩频频谱入站信号容量最大值.在卫星转发器带宽受限情况下,提出了采用分离扩频频谱的方法来提高入站容量,并分别对扩频频谱分离为两个和三个的情况进行了详细分析,得出了两种分离扩频频谱方案下扩频码速率的最优值.仿真结果表明,在现有转发器带宽内分离为两个扩频频谱可以提高入站容量29％,分离为三个扩频频谱可以提高人站容量37％.     

飞行器点火爆炸通用测量装置的设计

针对飞行器试验用点火器的通用测量装置,提出了一种柱形爆炸容器的设计方法,从容器壁厚、反射超压、应用材料、容器结构以及点火器爆炸当量等方面进行考虑,计算柱形爆炸容器的压力瞬间载荷,并利用COSMOS Works软件进行应力仿真,最后通过实际飞行试验环节进行验证,回收采集系统所记录的试验数据并间接分析出点火器的工作状态,结果表明:试验结果和理论分析完全吻合,容器设计合理,从而为飞行器研制试验用点火器驱动动力装置提供必要的数据参考和支撑。