图像采集系统中 CCD 靶面有效尺寸的测量

提出一种通过双光束干涉条纹间距来确定ＣＣＤ靶面的有效尺寸及有效象素间距的方法。详细介绍了该方法的原理,通过实验测量了所用面阵ＣＣＤ靶面有效宽度,并验证了测量结果。     

Aerodynamic Interactions Between Contralateral Wings and Between Wings and Body of a Model Insect at Hovering and Small Speed Motions

In this paper, we study the aerodynamic interactions between the contralateral wings and between the body and wings of a model insect, when the insect is hovering and has various translational and rotational motions, using the method numerically solving the Navier-Stokes equations over moving overset grids. The aerodynamic interactional effects are identified by compar-ing the results of a complete model insect, the corresponding wing pair, single wing and body without the wings. Horizontal, vertical and lateral translations and roll, pitch and yaw rotations at small speeds are considered. The results indicate that for the motions considered, both the interaction between the contralateral wings and the interaction between the body and wings are weak. The changes in the forces and moments of a wing due to the contralateral wing interaction, of the wings due to the pres-ence of the body, and of the body due to the presence of the wings are generally less than 4.5%. Results show that aerodynamic forces of wings and body can be measured or computed separately in the analysis of flight stability and control of hovering in-sects.     

一种精确鲁棒的刚体航天器特征轴旋转控制策略(英文)

特征轴旋转表征了两个方位之间的最短角路径,通常被看做是一种拟最小时间的快速姿态机动策略。本文在动力学方程中考虑了外部扰动和系统参数不确定性,基于时变滑模控制技术(TVSMC)研究了刚体航天器特征轴旋转的鲁棒控制问题。首先,通过一个TVSMC算法揭示了所提出鲁棒特征轴旋转策略的主要特点,并且证明了全局滑模的特点和闭环系统的稳定性,给出了特征轴旋转的必要条件。然后,为了抑制全局抖振,提高控制精度,提出了一种基于扰动观测器的时变滑模控制(DOTVSMC)算法。其中,采用边界层方法来削弱抖振并设计了扰动观测器来补偿不期望的影响。在航天器的姿态表征参数选择上,采用了没有冗余性的修正罗德里格斯参数(MRP)。最后,采用数值仿真来验证提出方法的有效性,并采用调宽调频(PWPF)技术来调制开关推力器。     

基于混合规划策略的自由漂浮冗余机械臂减振运动规划(英文)

对自由漂浮柔性冗余机械臂系统的减振运动规划问题进行研究。首先,采用拉格朗日方法建立系统的动力学模型,并给出了减振运动规划的模型。其次,提出一种基于高斯伪谱法与直接打靶法的混合规划策略,用于求解运动规划问题。先利用高斯伪谱法将运动规划问题转化为一个非线性参数优化问题,并用遗传算法确定近似解,随后利用直接打靶法建立优化模型,将得到的近似解作为优化变量的初值,并采用序列二次规划算法求得精确解。最后,对算例进行分析,验证了基于混合规划策略得到的关节运动轨迹能够明显减小柔性臂杆的全局振动以及残余振动。数值计算的结果表明该方法对减振运动规划问题的求解是有效且稳定的。     

Effects of Staged Injection on Supersonic Mixing and Combustion

The three-dimensional (3D) reacting flow in a staged supersonic combustor is examined numerically. In order to obtain the optimum stream-wise vortices, a swept ramp injector is chosen as the second-stage wall injection combined with the first-stage central strut injection. The performance of the two-staged injection is compared with that of a one-staged injection, while the strut is kept installed in both cases. The two-staged injections can make full use of the residual oxygen near the wall and release more heat. The second-stage injection further downstream avoids the strong shock waves in the isolator and results in a rising wall pressure and good burning effects after the wall injection. Therefore, it allows more fuel to be injected into the supersonic combustor without causing thermal choking. Parallel injection from the second-stage swept ramp shows low total pressure loss and the best burning efficiency, compared with the other injection angles.     

胶铆混合连接复合材料层合板结构的弹性分析

基于MSC．Patran／Nastran软件隐式非线性模块,建立复合材料层合板的铆接、胶接及胶铆混合连接三维有限元模型．计算得到不同连接方式下的应力场及位移场,通过对所得数据的对比,分析不同连接方式可能发生的破坏形式及其破坏最有可能出现的位置,得到胶铆混合连接的适用性。     

Application of Active Flow Control Technique for Gust Load Alleviation

A new gust load alleviation technique is presented in this paper based on active flow control. Numerical studies are conducted to investigate the beneficial effects on the aerodynamic characteristics of the quasi "Global Hawk" airfoil using arrays of jets during the gust process. Based on unsteady Navier-Stokes equations, the grid-velocity method is introduced to simulate the gust influence, and dynamic response in vertical gust flow perturbation is investigated for the airfoil as well. An unsteady surface transpiration boundary condition is enforced over a user specified portion of the airfoil’s surface to emulate the time dependent velocity boundary conditions. Firstly, after applying this method to simulate typical NACA0006 airfoil gust response to a step change in the angle of attack, it shows that the indicial responses of the airfoil make good agreement with the exact theoretical values and the calculated values in references. Furthermore, gust response characteristic for the quasi "Global Hawk" airfoil is analyzed. Five kinds of flow control techniques are introduced as steady blowing, steady suction, unsteady blowing, unsteady suction and synthetic jets. The physical analysis of the influence on the effects of gust load alleviation is proposed to provide some guidelines for practice. Numerical results have indicated that active flow control technique,as a new technology of gust load alleviation, can affect and suppress the fluid disturbances caused by gust so as to achieve the purpose of gust load alleviation.     

运输机空投控制器设计(英文)

重物空投过程中,飞行器各飞行参数随着货物舱内移动发生连续的变化,当货物投放瞬间则发生突变。随着空投货物重量的增加,这一过程将严重恶化飞行器飞行品质和操控特性。本文在简化的空投飞行方程基础上,研究反演和切换控制方法以解决这一过程中的飞行状态保持和扰动抑制(包括大范围飞行状态,飞行员操纵误差和系统量测延迟等)问题,所得控制策略也可用于驾驶员空投操纵的指令参考。利用反演理论,推导了自适应控制器以稳定运输机飞行状态,并提出了协调的切换控制方法解决飞机在货物离机过程中出现的状态跳变问题。仿真结果表明所提控制方法在不仅能有效保持系统状态,并能在较大飞行范围内具有较好的鲁棒性。     

Space Debris Reentry Analysis Methods and Tools

The reentry of uncontrolled spacecraft may be broken into many pieces of debris at an altitude in the range of 75-85 km. The surviving fragments could pose great hazard and risk to ground and people. In recent years, methods and tools for predicting and analyzing debris reentry and ground risk assessment have been studied and developed in National Aeronautics and Space Ad-ministration (NASA), European Space Agency (ESA) and other organizations, including the group of the present authors. This paper reviews the current progress on this topic of debris reentry briefly. We outline the Monte Carlo method for uncertainty analysis, breakup prediction, and parameters affecting survivability of debris. The existing analysis tools can be classified into two categories, i.e. the object-oriented and the spacecraft-oriented methods, the latter being more accurate than the first one. The past object-oriented tools include objects of only simple shapes. For more realistic simulation, here we present an object-oriented tool debris reentry and ablation prediction system (DRAPS) developed by the present authors, which introduces new object shapes to 15 types, as well as 51 predefined motions and relevant aerodynamic and aerothermal models. The aerodynamic and aerothermal models in DRAPS are validated using direct simulation Monte Carlo (DSMC) method.     

单模块超燃冲压发动机一体化流场数值计算

采用数值计算方法求解了单模块超燃冲压发动机内外流一体化流场，得到了流场详细结构和单模块发动机的性能参数，并对不同工况下的发动机性能进行了对比研究，探讨了发动机在有、无进气道侧压情况下的性能差异，分析了其中的原因。计算结果表明，研究工作中所发展的数值计算软件可以用于超燃冲压发动机的一体化流场计算，正确给出发动机的各项性能。计算结果还显示了发动机设计模型中存在的不足。