基于极限应力分析的十字形双向拉伸试件设计

十字形试件双向拉伸实验是实现复杂加载路径的有效方法,是研究板料后继屈服行为和成形极限可行的实验手段,解决十字形试件中心区的大变形、应力均匀性、应力测量计算方法等是其应用的主要问题.通过试件中心区减薄实现了中心区大变形以致颈缩破裂,给出了3种不同形式的中心区减薄形状,从应力均匀性、最大变形出现位置和避免应力集中等方面进行了优化对比分析,并探讨了计算中心区应力的解析方法.结果表明,中心区方形减薄的十字形试件有更好的中心区应力分布均匀性,更容易实现大变形以致破裂发生在中心区,能较好地控制应力集中,是更适用于板料成形极限应力图研究的实验装备.      

地球资源技术卫星地面轨迹控制原理及调轨周期的选择

1.引言 在整个任务执行期间,要求资源卫星在一个复盖周期里的地面轨迹中心线与另一个复     

Weibull分布下任务时间可靠度的置信限研究

为解决高可靠度要求的产品系统可靠度的评定问题，针对产品系统的工作时间服从威布尔分布，采用Fiducial方法，提出了只凭工作时间的‘小子样、零失效’可靠性试验样本，求取任务时间可靠度各置信限的方法及公式。给出算例，计算和分析了不同试验样本下系统任务时间可靠度的置信限。结果表明利用数个‘长寿’的‘小子样、零失效’工作时间试验样本，可以获得高置信度下系统任务时间可靠度的大下限；单凭非‘长寿’情况下的‘小子样、零失效’试验样本，只能得到任务时间可靠度的最高限，如能补充辅助可靠性信息，就能得到系统任务时间可靠度的可用置信估计。     

航母纵摇对舰载机弹射起飞的限制研究

舰载机在航空母舰上弹射起飞时易受舰面摇荡的影响，当航母在海浪作用下摇荡到一定程度时，就限制了舰载机的正常起飞，从海浪特性出发，通过对舰面摇荡运动的初步描述，探讨了舰面摇荡对舰载机起飞的限制范围，着重分析了舰面纵摇对舰载机弹射起飞的影响，确定了保护安全起飞的纵摇范围，从中得出一些有益的启示。     

狭缝内乙烯/氧气预混气体爆轰几何极限的实验

为研究狭缝内爆轰波传播极限,实验得到了不同初始压力(0.004~0.04MPa)下化学恰当比的乙烯/氧气预混气体在狭缝高度为1.0~4.0mm狭缝内的爆轰性能.采用烟膜板记录爆轰波运行轨迹,高速摄影捕捉火焰面.结果表明:狭缝高度越小,爆轰极限对应的临界初始压力越高.对于近极限条件内不稳定爆轰传播模式,包括"结巴"爆轰和驰振爆轰,其对应的初始压力范围随着狭缝高度的降低而变宽.考虑初始和边界条件,将水力直径与胞格宽度之比作为合理的爆轰敏感性参数描述预混气体爆轰特性,得出在不同狭缝通道内爆轰极限范围为,即该比值在0.326~0.403之间.      

A fast numerical approach for Whipple shield ballistic limit analysis

Whipple shield is widely used on manned spacecraft, numerical simulation is an important way for obtaining the ballistic limit. The large population of particles and the large space span of Whipple shield simulation model restrict the computational efficiency. A fast numerical approach is presented for Whipple shield ballistic limit analysis. First, the critical penetration analysis of the rear walls is converted into specific impulse analysis delivered by the secondary debris cloud, because the maximum of specific impulse is the main determinant of the penetration. The dual plate simulation model is then converted into single plate model and the population of particles is reduced. Second, based on the isotropic expansion theory of secondary debris cloud, the specific impulse analysis is further converted into particle position and velocity analysis when the stable secondary debris formed. The space span of the simulation model is reduced. An example of Whipple shield ballistic limit analysis is provided for the verification of the fast numerical approach, it shows that this approach can significantly increase the computation efficiency with acceptable accuracy.     

A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures

During a recent experimental test campaign performed in the framework of ESA Contract 16721, the ballistic performance of multiple satellite-representative Carbon Fibre Reinforced Plastic (CFRP)/Aluminium honeycomb sandwich panel structural configurations (GOCE, Radarsat-2, Herschel/Planck, BeppoSax) was investigated using the two-stage light-gas guns at EMI. The experimental results were used to develop and validate a new empirical Ballistic Limit Equation (BLE), which was derived from an existing Whipple-shield BLE. This new BLE provided a good level of accuracy in predicting the ballistic performance of stand-alone sandwich panel structures. Additionally, the equation is capable of predicting the ballistic limit of a thin Al plate located at a standoff behind the sandwich panel structure. This thin plate is the representative of internal satellite systems, e.g. an Al electronic box cover, a wall of a metallic vessel, etc. Good agreement was achieved with both the experimental test campaign results and additional test data from the literature for the vast majority of set-ups investigated. For some experiments, the ballistic limit was conservatively predicted, a result attributed to shortcomings in correctly accounting for the presence of high surface density multi-layer insulation on the outer facesheet. Four existing BLEs commonly applied for application with stand-alone sandwich panels were reviewed using the new impact test data. It was found that a number of these common approaches provided non-conservative predictions for sandwich panels with CFRP facesheets.     

飞机结构装配间隙超差分析与对策

飞机结构装配过程中,间隙、阶差超差类问题比较普遍,如机身部段之间、舵面与结构之间、相邻整流罩壁板之间等.通过对典型的间隙、阶差超差案例进行分析,总结造成间隙、阶差超差的主要原因,并提出解决间隙及阶差超差类问题的系统思路及指导方法.     

精益生产模式的理论渊源研究

市场经济环境下,低成本制造技术是武器装备制造业的发展方向。为此,对最精益生产理论渊源进行了研究,比较了其与大批量生产模式、敏捷制造模式的异同,阐明了其与先进制造模式、先进生产模式、先进管理模式的关系。     

永磁式双凸极电机系统稳态运行模型研究

以一台12/8极永磁式双凸极电机为研究对象,以有限元法对电机内电磁场分析结果为基础,对双凸极电机系统在不同控制方式下的稳态运行过程进行分析,得到与之相应的一阶非线性常微分方程。在Matlab编程环境下对各微分方程进行求解并结合电机的数学模型,建立永磁式双凸极电机系统稳态运行仿真模型,并将仿真得到的电流波形和机械特性曲线与实测得到的相关波形对照,二者间有很好的一致性。表明提出的双凸极电机系统研究方法具有一定的实用价值。