混杂纤维复合材料的剪切特性（一 ）：夹芯结构

对三种类型的混杂纤维复合材料层压板的层间剪切特性进行了试验与研究,从理论上描述了层间剪切应力分布状态。与此同时,对层间剪切强度和破坏位置分别进行了估算和预测,其结果与实验较为吻合。     

星载SAR的多普勒中心频率估计的新探索

本文对几种经典的多普勒中心频率估计算法的从滤波的角度加以分析，分析了符号相关算法的实质，并提出一种了简单适用的非线性滤波方法，对雷达回波方位功率谱周期图进行平滑，在满足成象要求下，可以快速估计出多普勒中心频率。     

基于场景模型的视频无线信道鲁棒传输

根据无线信道的特点，提出了一种基于场景统计模型的联合信源信道编码和网络拥塞控制的多媒体鲁棒传输系统。首先进行场景统计模型和特性分析，采用MPEG-4分级编码将所有的层划分成几类，接着由码流对网络拥塞和重建视频质量的影响将其分成两个传输优先级队列。在传输过程中，依据信道误码率和网络丢包率进行自适应的信源不同保护等级编码和网络拥塞控制策略。试验数据表明，本方案与以前文献中提出的IPB等方案相比，能够明显的提高重建视频质量。     

复合推进剂的细观失效机理分析

建立了颗粒填充复合推进剂的细观有限元模型,计算了颗粒与基体粘结完好和存在脱粘两种情况下颗粒与基体内的应力分布,分析了复合推进剂的细观失效机理。结果表明,在细观结构下,复合推进剂中的应力分布是不均匀的,推进剂一般首先在极区产生脱粘,颗粒的大小对推进剂的力学性能有较大影响。     

用导弹"视频遥测"信号推算导弹脱靶量

论述了采用某导弹战斗弹遥测系统中的“视频遥测”信号推算导弹靶试时脱靶量的原理，介绍了两种处理脱靶量的方法。根据该导弹某次靶试时的遥测数据，对导弹的脱靶量进行了推算。推算结果证明，遥测数据的处理结果与光测数据的处理结果相近，用导弹“视频遥测”信号推算导弹脱靶量的方法具有一定的参考意义。     

混杂纤维复合材料的界面

本文首先揭示和分析了混杂复合材料的特异现象—混杂效应,并认为混杂效应产生的主要原因是混杂界面。从而对混杂界面进行了研究和论述。指出混杂界面层与单一纤维复合材料界面层不同,为更加不均匀过渡,并以多相、多层次方式存在使混杂复合材料得以多种功能综合于一体。     

关于我国低空空域管理问题的思考

低空空域管理的目的是为了在确保国家安全的前提下,更好地开发利用空域这个重要的国家资源,在避免影响军事航空、公共运输航空飞行的基础上,尽可能满足并促进通用航空的发展。因此,我们从低空空域使用者的需求特点和发展需求入手,借鉴航空发达国家的先进经验,从国家空域系统的发展方向进行分析,阐述了实现上述低空空域管理目标的设想。一、低空空域与通用航空(一)低空空域属性空域是国家重要资源,其资源价值体现在为公共运输、通用航空和军事航空(包括警用飞行)服务。低空空域是国家空域体系的重要组成部分,按照国际民航组织的空域分类标准,…     

落儿岭-土地岭断裂几何结构及晚第四纪活动特征初探

落儿岭-土地岭断裂是东大别地区重要的发震构造,然而限于自然地理条件等因素,前人对其的研究并不充分。本文以发生多次中强地震的落儿岭-土地岭断裂为研究对象,在高精度卫星影像解译的基础上,通过详细的野外地质地貌调查,尤其是对典型断层剖面进行分析,研究落儿岭-土地岭断裂的断错地质地貌特征、几何结构及活动特征。通过野外调查并结合其他资料分析认为落儿岭-土地岭断裂为发育于大别造山带内部的一条走向NE、向NW陡倾的断裂带。依据地质地貌特征及地震活动性,断裂可以划分为杨树沟-黑石渡段和黑石渡-横塘岗乡段两个几何段落。断裂最新活动时代为中更新世晚期—晚更新世早期,断裂最新活动继承了中生代以来的运动方式,以兼具右旋走滑的拉张正断为主。     

A lunar cargo mission design strategy using variable low thrust

A design technique for a near optimal, Earth–Moon transfer trajectory using continuous variable low thrust is proposed. For the Earth–Moon transfer trajectory, analytical and numerical methods are combined to formulate the trajectory optimization problem. The basic concept of the proposed technique is to utilize analytically optimized solutions when the spacecraft is flying near a central body where the transfer trajectories are nearly circular shaped, and to use a numerical optimization method to match the spacecraft’s states to establish a final near optimal trajectory. The plasma thruster is considered as the main propulsion system which is currently being developed for crewed/cargo missions for interplanetary flight. The gravitational effects of the 3rd body and geopotential effects are included during the trajectory optimization process. With the proposed design technique, Earth–Moon transfer trajectory is successfully designed with the plasma thruster having a thrust direction sequence of “fixed-varied-fixed” and a thrust acceleration sequence of “constant-variable-constant”. As this strategy has the characteristics of a lesser computational load, little sensitivity to initial conditions, and obtaining solutions quickly, this method can be utilized in the initial scoping studies for mission design and analysis. Additionally, derived near optimal trajectory solution can be used as for initial trajectory solution for further detailed optimization problem. The demonstrated results will give various insights into future lunar cargo trajectories using plasma thrusters with continuous variable low thrust, establishing approximate costs as well as trajectory characteristics.     

Experimental investigation on impingement-effusion film-cooling behaviors in curve section

A new series of test pieces with different geometrical configuration and geometry dimensions are designed to experimentally investigate on impingement-effusion cooling behavior in curve effusion wall of combustion chamber. The test results show that the discharge coefficient increased with the increasing blowing ratio. The effusion hole–hole spacing has an effect on the discharge coefficient and the discharge coefficient commonly decreased with the increment of effusion hole–hole spacing. The blowing ratio greatly effects cooling behavior. The bigger blowing ratio is favorable for improving cooling characters. At the curved effusion wall, to begin with, cooling effectiveness increased slowly and kept a steady value in subsequence. But, for the rear end of curved effusion wall, it decreased slowly. With decreasing of effusion hole angle and effusion hole–hole spacing, cooling effectiveness is enhanced. Meanwhile, blowing ratio, effusion angle and effusion hole–hole spacing take an evident effect on the discharge coefficient.