热和振动复合环境中人体热调节的数值模拟

本文针对热和振动复合环境对人体的影响特点，建立了该复合环境中二维人体热调节系统的数学模型．采用数值方法对人体热调节系统数学模型进行求解，计算了不同热和振动复合环境条件下人体温度分布及动态响应，计算结果与实验结果相符较好，相对误差小于５％．     

《中国儒教史》反思：中国文化宗教论－－兼与李申先生商榷

李申的《中国儒教史》其思想方法是对中国化进行彻底的宗教化，与任继愈的“儒教是教说”一样承诺了否定中国化的价值取向，并且比“儒教是教说”有过之而无不及。中国化宗教论是对中国化的歪曲和否定，应该对其反思批判、正本清源。     

Numerical simulation and transonic wind-tunnel test for elastic thin-shell structure considering fluid–structure interaction

Aerodynamic force can lead to the strong structural vibration of flying aircraft at a high speed. This harmful vibration can bring damage or failure to the electronic equipment fixed in aircraft. It is necessary to predict the structural dynamic response in the design course. This paper presents a new numerical algorithm and scheme to solve the structural dynamics responses when considering fluid–structure interaction(FSI). Numerical simulation for a free-flying structural model in transonic speed is completed. Results show that the small elastic deformation of the structure can greatly affect the FSI. The FSI vibration tests are carried out in a transonic speed windtunnel for checking numerical theory and algorithms, and the wind-tunnel test results well accord with that of the numerical simulation. This indicates that the presented numerical method can be applied to predicting the structural dynamics responses when containing the FSI.     

稳定控制回路振铃现象的消除及其关键参数的选择

针对飞航平台稳定控制回路对象讨论Dahlin控制器设计问题,在复频域分析的基础上,探讨了二阶对象期望闭环传递函数的合理形式。通过对期望闭环传递函数和控制对象的分析,找到了导致二阶对象Dahlin控制器产生振铃的原因,给出了判定振铃产生的条件,并且提出了修正设计方法以及振铃现象中关键参数的选择方法。     

一种基于首发货运飞船的姿态控制试验方案研究

针对首发货运飞船的任务特点,兼顾未来空间站的需求,提出姿态控制试验系统方案,用于首发货运飞船。在基本不改变标准平台状态的前提下,可在轨验证满足后续型号任务需求的扩展平台功能,减少自主飞行与离轨推进剂消耗量共计560~690 kg,更好地满足了其他飞行任务与试验的推进剂需求,同时还可提前验证空间站关键单机。分析了三轴对地、连续偏航、90°俯仰对地、俯仰机动、组合体CMG融合使用等姿控模式,并进行了仿真,验证了方案的可行性。     

涡轮第一级导向叶片的气膜冷却仿真

气膜冷却是保证航空发动机涡轮导向叶片正常工作的重要方法之一。为研究在较高涡轮前温度条件下气膜孔布置对叶片前缘降温的效果,采用ANSYS CFX的RNG k‐ε模型对选定叶片进行了叶片前缘气膜冷却仿真。根据驻点、流动分离点等条件确定了气膜孔位置,并根据仿真效果对气膜孔布置进行调整。通过仿真结果表明,调整好位置的气膜孔对叶片前缘的冷却效果比较明显。     

Measuring air traffic complexity based on small samples

Air traffic complexity is an objective metric for evaluating the operational condition of the airspace.It has several applications,such as airspace design and traffic flow management.Therefore,identifying a reliable method to accurately measure traffic complexity is important.Considering that many factors correlate with traffic complexity in complicated nonlinear ways,researchers have proposed several complexity evaluation methods based on machine learning models which were trained with large samples.However,the high cost of sample collection usually results in limited training set.In this paper,an ensemble learning model is proposed for measuring air traffic complexity within a sector based on small samples.To exploit the classification information within each factor,multiple diverse factor subsets (FSSs) are generated under guidance from factor noise and independence analysis.Then,a base complexity evaluator is built corresponding to each FSS.The final complexity evaluation result is obtained by integrating all results from the base evaluators.Experimental studies using real-world air traffic operation data demonstrate the advantages of our model for small-sample-based traffic complexity evaluation over other stateof-the-art methods.     

数学形态学在遥测数据处理中的应用研究

叙述了数学形态学的基本算法。讨论了数学形态学算法在遥测数据处理中的应用。提出了结构元素的选择要求,并对实测数据进行了效果分析。     

Calculation of axial gasodynamic forces,disk friction losses and overflow in semiopen impellers of centrifugal compressors

The methods for calculating axial forces, disk friction losses and overflow are developed on the basis of experimental data on the radial pressure distribution at both sides of the semi-open impeller, disk friction and overflow through clearances between the blades and the case.     

Investigation of landing gear wheel shimmy taking into account damper frequency characteristics

A mathematical model and a technique for calculating the rolling motion stability of the damper-equipped landing gear wheel are presented; the dependence of dynamic damper rigidity on frequency found experimentally is used in the investigation. The results of calculating the shimmy boundaries with and without regard for the dependence indicated are given.