Mathematical modeling of heat transfer process in a variable domain

In this paper, a brief review and generalization of studies on the heat transfer and heat conduction problem in a variable domain are presented. The equations of the process, where the boundary displacement velocity is the control, are obtained taking into account heat inflow. This article was submitted by the authors in English.     

降落伞的流场特性研究

降落伞的流场特性直接关系到降落伞的气动力性能,一直以来是降落伞研究中的核心问题。本文采用计算流体动力学(CFD)方法对降落伞的流场进行数值模拟。通过采用不同的网格生成方法对降落伞的绕流流场进行研究,表明生成网格质量对流场计算精度有很大的影响。在一系列数值实验的基础上,证明采用多块贴体坐标的网格处理方法能够获得良好的网格质量,同时还具有易于寻找伞衣内外面压力,计算稳定性、可靠性高等优点。在此基础上,采用了七孔探针对降落伞绕流流场进行了测量,实验结果和计算结果吻合较好。     

失速改出伞阻力特征面积估算方法

研究了高平尾布局飞机的气动特性。使用失速改出伞是飞机改出深失速的重要途径,但如何确定失速改出伞的关键参数(阻力面积等)却没有现成的方法。以ARJ21-700飞机为例,分别使用公式分析法、类比法综合估算出失速改出伞的关键参数,通过模型自由飞和模拟仿真分析验证其具有足够效能将飞机改出深失速状态。形成了一套新机失速改出伞的设计方法和关键数据图表,可供其他型号飞机失速改出伞的设计研制使用。     

Mathematical modeling of an optimal controlled helicopter flight at vertical regimes

The investigation results on developing a mathematical model of the controlled helicopter flight along the vertical trajectory are presented. For motion optimization the direct approximate method is used. The optimizing functional consists of two main parts: the first part is proportional to the motion time; the second part contains penalties for trajectory constraint violation. The examples of calculations and the results of numerical studies are given, the parameters of optimal program reference trajectories are obtained for the helicopter type chosen.     

Mathematical modeling of thermal modes of thermosyphons in operation with characteristic heat loads of aircraft equipment batteries

Numerical analysis of thermal conditions for a two-phase closed thermosyphon using the ANSYS FLUENT software package has been carried out. The characteristic temperature distribution, streamlines and velocity vectors for various heat loads have been obtained. The study has found the possibility of using the software package for analysis of the energy transfer processes at high thermal loads.     

降落伞充气过程中伞衣外形及流场变化研究

根据降落伞的结构和其在充气过程中的受力特性,以某平面圆形伞为原型,建立了伞衣充气过程中的计算流体力学与结构动力学耦合模型。并采用七孔探针对充满状态的绕流流场进行了定量测量,将该状态的试验结果和计算结果进行对比分析,二者的拓扑结构非常相似,压差系数也相差不大,因此所采用的数学模型是可靠的。在此基础上,对整个充气阶段的流场进行了数值模拟和分析,以详细了解降落伞整个开伞过程中伞衣外形变化及伞衣内外流场的变化情况。研究结果表明:①在初始充气阶段,伞衣展开部分外形基本保持较光滑的直筒形状,而非喇叭形。在主充气阶段:空气首先在伞衣顶部聚集,使伞衣顶部膨胀,然后膨胀部分向伞衣底边扩展,直到伞衣完全张满。②当伞顶孔被气流冲开后,伞衣的结构透气性对流场会产生显著影响。但从内外压力系数的变化来看,透气性对伞衣内滞止压力的影响较小,对伞衣外流场结构的影响较大,从而对伞衣外表面的压力影响较大。③对于此类有伞顶孔的平面圆形伞,当伞衣充气张开后,伞衣尾部出现气流分离,在一个漩涡区内形成两个相反旋转方向的漩涡。且随着伞衣直径扩张,分离区扩大,主流对漩涡区的剪切面积增大,因此漩涡区两个漩涡中外侧的一个漩涡增大,内侧漩涡被挤压至离伞顶更近的区...     

Multisensor resource deployment using posterior Cramer-Rao bounds

The development of a general framework for the systematic management of multiple sensors in target tracking in the presence of clutter is described. The basis of the technique is to quantify, and subsequently control, the accuracy of target state estimation. The posterior Cramer-Rao lower bound (PCRLB) provides the means of achieving this aim by enabling us to determine a bound on the performance of all unbiased estimators of the unknown target state. The general approach is then to use optimization techniques to control the measurement process in order to achieve accurate target state estimation. We are concerned primarily with the deployment and utilization of limited sensor resources. We also allow for measurement origin uncertainty, with sensor measurements either target-generated or false alarms. An example in which the aim is to track a submarine by deploying a series of constant false-alarm rate passive sonobuoys is presented. We show that by making some standard assumptions, the effect of the measurement origin uncertainty can be expressed as a state-dependent information reduction factor which can be calculated off-line. This enables the Fisher information matrix (FIM) to be calculated quickly, allowing Cramer-Rao bounds to be utilized for real-time, dynamic sensor management. The sensor management framework is shown to determine deployment strategies that enable the target to be accurately localized, and at the same time efficiently utilize the limited sensor resources.     

Dynamic analysis of spinning solar sails at deployment process

The spinning deployment process of solar sails is analyzed in this study.A simplified model is established by considering the out-of-plane and in-plane motions of solar sails.The influences of structure parameters,initial conditions,and feedback control parameters are also analyzed.A method to build the geometric model of a solar sail is presented by analyzing the folding process of solar sails.The finite element model of solar sails is then established,which contains continuous cables and sail membranes.The dynamics of the second-stage deployment of solar sails are simulated by using ABAQUS software.The influences of the rotational speed and out-of-plane movement of the hub are analyzed by different tip masses,initial velocities,and control parameters.Compared with the results from theoretical models,simulation results show good agreements.     

折叠机翼展开过程气动特性实验研究

针对某型无人机大展弦比折叠机翼展开过程,对其缩比模型在不同迎角、不同机翼掠角状态下的气动特性进行了风洞实验.实验结果表明,布局的气动外形满足巡航设计要求,纵向与横航向稳定性较好,多面组合式机身表面可为全机升力带来有利影响,研究结果可在无人机、巡飞导弹等研究领域得到应用.     

Spacecraft on-orbit deployment anomalies: What can be done?

On-orbit anomalies related to the deployment of spacecraft appendage and possible causes of such failures are considered. The discussion covers mechanical launch loading, on-orbit thermal and solar concerns, reliability of spacecraft pyrotechnics, and practical limitations of ground-based deployment testing. Lessons learned from the successful recovery of the Telesat Canada Anik-E2 satellite in 1991 are examined     

关于数学实验

从数学实验的产生、基本做法、内容选取、特点和意义几方面，阐述了开设数学实验的必要性和重要性，通过例子－库存系统的领导具方法，探讨教学实验是如何培养学生的创新意识和独立思考能力的。     

液压系统数学模型的辨识

系统辨识是获得液压系统数学模型的最有效方法之一。本文研究了液压系统数学模型辨识的实验设计技术、介绍了自行开发的辨识软件的原理与功能,并给出了对液压转台进行辨识的结果。     

飞机配载方法的数学分析

飞机配载常用的方法是平衡图表法,亦即每一种机型需要专门的平衡图表。利用旅客、行李、邮件和货物等参数,用数学方法来分析飞机的平衡,从而帮助配载人员从本质上去理解平衡图表,实现对旅客、行李、邮件和货物的合理配载。     

计算物理中的数学实验方法

论述了计算物理与数学实验的关系,以及数学实验对计算物理的重要性,并通过实例说明,利用数学实验方法可以简化计算,突出物理概念,使问题得到更好的解决。     

Successful deployment of commercial ATE to an Air Force I-level (back-shop) repair facility

In today's world of constrained budgets, one of the problems the military faces is the challenge of trying to maintain organic maintenance capabilities. Historically, the US Air Force has desired to achieve an autonomous capability to maintain the equipment it uses. This has been achieved, traditionally, by setting-up three levels of maintenance: organizational; intermediate (back-shop); and depot. The I-level back-shops often utilize militarized automatic test equipment (ATE) and test program sets (TPSs) to test today's complex aircraft line replaceable units (LRUs). And even though this is still a cost-effective maintenance philosophy, it has become costly to develop militarized ATE. The Department of Defense (DoD) has been very active in trying to reduce the total ownership cost of ATE in the government inventory. One approach is to utilize commercial, instead of Mil-Spec, ATE. However, utilizing commercial ATE at an USAF back-shop is not without its tradeoffs and challenges as it represents a significant deviation from the way the USAF maintenance squadrons are accustomed to "doing business." This paper documents the current success story of replacing the legacy C-17 I-level ATE with a commercial ATE.     

A Mathematical Analysis of the Problem of Pointing

This paper contains a mathematical analysis of the problem of automatically pointing a sighting device, mounted on a moving vehicle, at a fixed target. The results apply to situations such as automatic sighting devices for aircraft and helicopters, automatic camera aiming for airborne photography, etc. Basic mathematical relations, which govern all forms of such automatic pointing devices, are derived.     

机载数据总线拓扑结构的数学描述

机载数据总线作为现代作战飞机的神经中枢,主要用于数据传输,以达到信息共享的目的.规定了总线线路传输模式、差分传输、多总线和余度的数学符号表示,分别分析了RS-232、RS-422、RS-485、ARINC429和MIL-STD-1553B总线的拓扑结构,并结合实例给出了相应的数学描述.简洁、严谨、无歧义的数学描述有利于对机载数据总线拓扑结构的理解,为进一步的总线拓扑结构可视化和航空电子系统的系统集成提供了理论基础.     

直升机飞行动力学数学模型研究特点分析

根据国内外直长机数学模型研究情况,从飞行动力学角分析直升机数学模型的特点。重点讨论了不同研究目的直或机飞行动力学模型的区别,即分别对以非实时数值仿真,实时数值仿真和控制律设计为目的的直升机模型进行分析,阐述其在模型的运动方程数学形式,子模型的复杂性和选取,模型精度以及模型的应用范围等方面的特点,并简要介绍了目前用于直升机飞行动力学特性研究的综合分析软件系统和试验相关性研究。     

Dynamic modeling of flexible multibody structures

This work is primarily concerned with the development of a mathematical formulation capable of treating the problems of maneuvering and control of flexible multibody structures. The analytical formulation is based upon equations of motion in terms of quasi-coordinates derived for each substructure independently. The individual substructures are made to act as a single structure by means of a consistent kinematical synthesis. In recognition of smaller elastic motions, a perturbation approach is developed whereby the rigid-body maneuvering of the system defines the zero-order kinematical dynamics, while the elastic motions and perturbations from the rigid-body maneuvering define the first-order kinematical synthesis. As a numerical example, the Planar Articulating Controls Experimental (PACE) test article is maneuvered according to a bang-bang control law by means of torque applied to the shoulder and the elbow. The numerical simulation shows a close match with the detailed modal survey