受钉传载荷含边缘裂纹板的解析变分解法

采用复变-变分法求解受钉传载荷含边缘裂纹各向异性与各向同性板的应力强度因子。首先建立满足所有各向异性弹性力学基本方程和钉孔合力平衡条件及位移单值条件的应力和位移级数表达式,然后应用变分原理满足板的边界条件,从而确定应力强度因子。计算表明,级数收敛迅速,数值解和实验结果吻合,而所需机时较少。     

物流系统中要素冲突问题探讨

物流系统各要素之间在目标、产权和运作上存在冲突，这些冲突会影响到物流系统功能的发挥。对此，提出了处理物流系统要素冲突问题的基本原则，即系统思考、区别对待、重点突出、适度控制。并按照霍尔的系统工程的思路构建了处理物流系统要素冲突问题的三维结构框架图，给出了主要冲突的解决思路和方法，如采用一体化和供应链管理的思想来解决效益悖反问题，选择适当的战略联盟伙伴促进物流要素间的能力均衡及信息共享，加快推进物流标准化以解决设备不匹配、票据不统一的问题，旨在加强要素间的协同作用，通过企业、政府、行业协会的共同努力，合理引导冲突，从而促进物流系统的功能跃迁。     

长波定时ASF修正的GIS软件

论述的长波定时ASF修正的GIS软件能快速数字化可视化显示和调用服务区域的地形地理信息、大地电参数和大气折射率等多种数据源。使用此软件可以非常方便容易地用不同模型计算在广阔区域接收到的多个长波信号在各种典型路径上的ASF和地波传播时间延迟,并提高定时精度。     

MD-82型飞机的腐蚀损伤及影响因素分析

统计了原中国北方航空公司7架MD-82型飞机的腐蚀损伤情况。就相对湿度、空气中含盐量、工业大气和空运海鲜产品4个因素，分析了各因素对MD-82型飞机腐蚀损伤的影响。     

逆向卸荷式气体减压阀的动态特性仿真

考虑到摩擦力、阻尼力及流体流动作用力等主要非线性因素对减压阀动态特性的影响,建立了逆向卸荷式气体减压阀的动态特性数学模型,并对其启动过程与负载变化下的动态响应特性进行了仿真计算,研究了动态过程的压力、温度、流量以及阀芯位移等参数变化情况,分析了不同的参数对减压阀启动特性的影响,提出了改善减压阀动态响应特性的措施。     

影响图理论及其评价算法研究

本文介绍了Howard R A等人近年来提出的一种新的决策分析工具——影响图(Influence Diagram),并对影响图的计算机自动评价作了初步的研究。探讨了在R&D研究中的应用。     

Analytical and semi-analytical investigations of geosynchronous space debris with high area-to-mass ratios

This paper provides a Hamiltonian formulation of the averaged equations of motion with respect to short periods (1 day) of a space debris subjected to direct solar radiation pressure and orbiting near the geostationary ring. This theory is based on a semi-analytical theory of order 1 regarding the averaging process, formulated using canonical and non-singular elements for eccentricity and inclination. The analysis is based on an expansion in powers of the eccentricity and of the inclination, truncated at an arbitrary high order.     

环境压强对电弧喷射推力器性能的影响

为了详细研究环境压强对电弧喷射推力器性能的影响,对低功率氮氢电弧喷射推力器在不同环境压强下的工作性能进行了比较计算。采用二阶精度无波动、无自由参数的耗散差分格式(NND格式)和经典龙格库塔方法求解耦合电磁源项的N-S方程组,采用高斯-塞德尔超松弛迭代方法数值求解电磁场方程。计算结果给出了不同环境压强下推力器的推力、比冲、推进效率和出口平面冲量密度分布。结果分析定量地阐释了环境压强对推力器性能的影响,能为推力器的实验研究及空间应用提供参考。      

某型飞机平尾间隙研究和改进

分析某型飞机平尾安装和使用过程中间隙问题产生的原因,探讨影响锥形衬套与平尾转轴、大轴承内圈之间间隙的因素,从理论上对平尾转轴的受力状况和安装间隙之间的关系进行了研究,找出现有飞机存在的问题并进行排故和处理,为后续飞机提出设计改进措施。     

Modeling and analysis of Earth’s gravity field measurement performance by inner-formation flying system

The Earth’s gravity field can be measured with high precision by constructing the purely gravitational orbit of the inner-satellite in Inner-formation Flying System (IFS), which is independently proposed by Chinese scholars and offers a new way to carry out gravity field measurement by satellite without accelerometers. In IFS, for the purpose of quickly evaluating the highest degree of recovered gravity field model and geoid error as well as analyzing the influence of system parameters on gravity field measurement, an analytical formula was established by spectral analysis method. The formula can reflect the analytical relationship between gravity field measurement performance and system parameters such as orbit altitude, the inner-satellite orbit determination error, the inner-satellite residual disturbances, data sampling interval and total measurement time. This analytical formula was then corrected by four factors introduced from numerical simulation of IFS gravity field measurement. By comparing computation results from corrected analytical formula and the actual gravity field measurement performance by CHAMP, the correctness and rationality of this analytical formula were verified. Based on this analytical formula, the influences of system parameters on IFS gravity field measurement were analyzed. It is known that gravity field measurement performance is a monotone decreasing function of orbit altitude, the inner-satellite orbit determination error, the inner-satellite residual disturbances, data sampling interval and the reciprocal of total measurement time. There is a match relationship between the inner-satellite orbit determination error and residual disturbances, in other words, the change rate of gravity field measurement performance with one of them is seriously restricted by their relative size. The analytical formula can be used to quantitatively evaluate gravity field measurement performance fast and design IFS parameters optimally. It is noted that the analytical formula and corresponding conclusions are applied to any gravity satellite which measures gravity field by satellite perturbation orbit.