基于振动分析的坦克柴油机汽缸燃烧压力检测方法

针对在坦克实车上不易直接测量柴油机汽缸压力的问题,提出了一种通过测量柴油机汽缸盖振动信号来间接检测汽缸燃烧压力的方法。在某型坦克柴油机上同步测量了汽缸燃烧压力、汽缸盖振动信号和变速箱振动信号,利用自适应滤波方法滤除了汽缸盖振动信号中包含的变速箱振动信号形成的噪声干扰,利用配气相位从时间域分离出由气体燃烧压力激发的振动信号,利用Hilbert变换和小波分解方法分别提取了振动信号和压力信号的特征波形。建立了RBF神经网络模型,以汽缸盖振动信号的包络作为网络输入,实现了汽缸燃烧压力的间接检测。     

关联维数在梁式结构损伤检测中的应用

为探索有效实用的结构损伤检测方法,运用分形理论直接对结构振动信号进行关联维数分析,通过度量系统输出的奇异性来识别结构的局部损伤,提出了基于振动响应关联维数的结构损伤检测方法.简支梁损伤算例结果表明,该方法能够准确地检测出梁式结构单个和多个不同程度的损伤位置,同时关联维数指标变化值会随着损伤程度的增加而增大.与曲率模态指...     

非线性随机动态响应的高效模拟方法

提出了一种分析多自由度非线性系统在随机激励下响应的高效模拟方法。该方法以蒙特卡罗方法为基础,针对动态问题,建立了有效的重要性判别准则,采用俄罗斯轮盘赌与分裂方法来处理响应样本,增加了样本在低失效概率区域出现的几率,提高了模拟效率。通过两个算例表明,该方法操作简单,可以大大地减少计算量,能够适用于实际的工程问题。     

复杂体系的结构分析和建模研究

根据复杂体系的概念及其所呈现出的多种特性,利用复杂体系的使命分解和复杂体系的元素组成对复杂体系进行综合的结构分析,描述了目标分解、功能分解和行为分解的复杂体系使命目标三阶段分解过程以及系统单元、复合元和体系外部环境的复杂体系三元素结构框架。在此基础上,提出了采用一种“两层四级”的设计思想对复杂体系进行有效的结构建模设计,并针对复杂体系内部的相互位置层次及其功能关联定义了度量实体、层级映射、系统关联性和软构层等相关概念,清晰地阐释了复杂体系结构分析和建模时体系层次映射的实质,从而为复杂体系的效能评估以及体系改进和优化提供一定的理论指导。     

An efficient and modular modeling for launch dynamics of tubed rockets on a moving launcher

This paper develops a modular modeling and efficient formulation of launch dynamics with marching fire (LDMF) using a mixed formulation of the transfer matrix method for multibody systems (MSTMM) and Newton-Euler formulation. Taking a ground-borne multiple launch rocket systems (MLRS), the focus is on the launching subsystem comprising the rocket, flexible tube, and tube tail. The launching subsystem is treated as a coupled rigid-flexible multibody system, where the rocket and tube tail are treated as rigid bodies while the flexible tube as a beam with large motion. Firstly, the tube and tube tail can be elegantly handled by the MSTMM, a computationally efficient order-N formulation. Then, the equation of motion of the in-bore rocket with relative kinematics w.r.t. the tube using the Newton-Euler method is derived. Finally, the rocket, tube, and tube tail dynamics are coupled, yielding the equation of motion of the launching subsystem that can be regarded as a building block and further integrated with other subsystems. The deduced dynamics equation of the launching subsystem is not limited to ground-borne MLRS but also fits for tanks, self-propelled artilleries, and other air-borne and naval-borne weapons undergoing large motion. Numerical simulation results of LDMF are given and partially verified by the experiment.     

Noise and vibration measurements in a Viking military vehicle

Noise and whole-body vibration measurements were made in a Viking military vehicle to determine the variation that should be expected during repeat measures, the effect of speed (up to 60 km/h in 5 km/h increments), and during travel over different types of terrain (comprising concrete road, gravel track and rough cross-country). Measurements were made at various crew positions (including the driver and commander) in both the front and the rear cabs in the vehicles. Three translational axes of vibration were measured in each seat. Two speeds were investigated over road (35 km/h and 55–60 km/h) and gravel (20 km/h and 35 km/h) surfaces. The effect of varying speed of the vehicle on the measured noise and vibration magnitudes was also investigated. The highest sound pressure level (L_Aeq) of 104 dB(A) was measured at the commander’s standing position during travel over concrete road at 55 km/h. Higher noise levels occurred for a standing commander compared with when sitting on the seat. A maximum single axis frequency-weighted vibration magnitude of 1.0 m/s² r.m.s. was measured on the driver’s seat during travel over track at 35 km/h. Higher vibration magnitudes occurred during travel over track compared with travel over road. Both noise and vibration exposure of crew within the Viking vehicle increased with increasing speed of the vehicle.     

【专题】从系统工程视角看无人机自主控制系统

提升无人机的自主控制能力可有效提高无人机在复杂对抗环境下的作战性能。系统工程是指导复杂系统研制的有效手段,采用系统的思维方法,关注系统的整体效能优化实现。系统工程覆盖复杂工程型号生命周期的全流程活动,包括概念论证、工程开发、生产制造、使用服役、综合保障以及系统退出等过程,能够为系统开发中各工程技术的应用,跨专业工程合作以及项目管理建立切实的技术路径。无人机外部应用背景环境与内部体系结构相互交联,是一个典型的“系统之系统”（System of Systems）。无人机自主控制系统是跨域、跨平台的复杂“系统之系统”。本文从系统复杂性出发,介绍了无人机系统组成、自主控制系统以及无人机自主能力等级,以期为无人机自主控制技术的发展提供参考和借鉴。     

Static and free vibration analyses of functionally graded porous variable-thickness plates using an edge-based smoothed finite element method

The main purpose of this paper is to present numerical results of static bending and free vibration of functionally graded porous (FGP) variable-thickness plates by using an edge-based smoothed finite element method (ES-FEM) associate with the mixed interpolation of tensorial components technique for the three-node triangular element (MITC3), so-called ES-MITC3. This ES-MITC3 element is performed to eliminate the shear locking problem and to enhance the accuracy of the existing MITC3 element. In the ES-MITC3 element, the stiffness matrices are obtained by using the strain smoothing technique over the smoothing domains formed by two adjacent MITC3 triangular elements sharing an edge. Materials of the plate are FGP with a power-law index (k) and maximum porosity distributions (Ω) in the forms of cosine functions. The influences of some geometric parameters, material properties on static bending, and natural frequency of the FGP variable-thickness plates are examined in detail.     

Quasi-steady aerodynamic characteristics of Terminal Sensitive Bullets with short cylindrical portion

The aerodynamic characteristics are vital for short cylindrical Terminal Sensitive Bullets(TSB)with low aspect ratio,especially in terminal trajectory.Currently,there is little research in terms of the TSB and short cylinder with two free ends,and particularly in this trajectory,where the scanning angle β and roll angle α vary over a broad range between 0° and 180°.In this work,wind tunnel experiments are first conducted to learn the effects of Reynolds number and scanning angle on aerodynamic parameters for short cylinder with aspect ratio L/D = 1.Similar to infinite cylinder,for the short cylinder with two free ends,the drag crisis phenomenon still exists in the critical regime 1.7 × 105 ≤ Re ≤ 6.8 × 105.Then 3D simulations are performed to demonstrate the aerodynamic characteristics of short cylinder and TSB over a broad range of Re,L/D,α and β.The sensitivity analysis of time step and grid are presented as well.When β=0°,for short cylinder,the drag crisis phenomenon was also observed in the simulation,but not as obvious as in the wind tunnel test.In some attitudes,there is an obvious Kármán vortex in the wake of short cylinder and TSB.The correlation between time-averaged aerodynamic coefficients and L/D,Re,α&β is discussed.The vortex shedding frequency and shear layer behavior are obtained for quasi-steady and unsteady flow.Finally,the effect of end's shape on drag reduction and vortex shedding frequency is analyzed.     

水下声探测系统载体振动干扰分析及抑制方法

针对水下探测系统载体振动对目标回波信号的微多普勒特征谱产生干扰的问题,从干扰产生的基本原理出发,推导了干扰的近似乘性表达式。在获取振动干扰数据的条件下,提出了针对乘性干扰的干扰抑制算法,并针对推导干扰乘性表达式时的近似条件,分析了近似算法带来的误差。仿真结果表明,该方法可有效抑制水下探测系统平台振动对目标回波信号的微多普勒特征谱产生的干扰,并且在绝大多数情况下,由算法带来的误差可以忽略不计。