三角形微沟槽飞艇蒙皮表面的流场分析

微米尺度的沟槽是临近空间飞艇大面积减阻的一种可行的减阻形式．以临近空间飞艇减阻为研究背景,通过采用k-ω SST湍流模式,对微米尺度的三角形沟槽进行了流场分析,得到了三角形沟槽壁面流的速度场和压力场． 通过计算不同尺寸三角形微沟槽的减阻率和沟槽内的流线形状,分析了微米尺度沟槽的减阻机理和不同沟槽尺寸对减阻能力的影响．研究表明,沟槽内的流线形状对沟槽的减阻能力有重要影响,尺寸合适的沟槽可以减小流体和壁面之间的切应力,减小流动阻力,对临近空间飞艇的蒙皮设计和减阻研究提供了一定参考．     

Wrinkling analysis of creased rectangular membrane

In this paper,the wrinkle-crease interaction behavior of a rectangular membrane under edge tension is simulated.The creased membrane is modeled by using a Modified Two-Parameter model.In this model,two crease parameters,i.e.the effective modulus of creased membrane and the residual stress from creasing,are computed by using MacNeal’s method that was firstly applied directly in a flat membrane with the local crease.We have proposed a method to solve the wrinkling computing issue of the creased membrane by using a Direct Perturb-Force technique in our previous work.Based on our method,the effects of crease location on the wrinkle-crease interaction behavior can be evaluated accurately.These results will be of great benefit to the analysis and the control of the wrinkles in the membrane structures.     

逆向迭代的点阵式充气翼三维保形分析

充气翼在充气变形后与预期设计目标之间会产生偏差,这样的偏差会影响充气翼正常工作下的气动外形,不利于充气翼的精细化分析．针对该问题,提出了一种逆向迭代充气翼三维保形分析方法,来寻找目标构型给定下充气翼未加载时的三维初始形态．运用APDL参数化设计完成了对一种新型点阵式充气翼的逆向迭代保形分析,并通过非接触测试进行实验验证．结果表明:逆向迭代法可以有效的得到满足精度要求的充气翼三维初始构型,分析效率高、收敛性好且可靠性高．     

DBC型燃烧器点火油枪的节油改造

<正>我公司4 600t/d生产线于2012年6月28日点火,窑头配置DBC-2900-550-8000燃烧器,最大喷煤量16.9t/h,采用原装风压雾化油枪,最大燃油量为120~1 200L/h。在生产前期,油枪雾化效果差、耗油量大,给生产带来了诸多困难。1出现的问题初次升温烘窑时,先烧油10h,再油煤混烧124h,柴油消耗量约70t,平均每小时耗油650L;平时停窑检修的点火升温,一般先烧油0.5~1h,再油煤混烧10.5~11h,柴油消耗量6~7t,平均每小时耗油680L,点     

空间充气天线反射器受冲击气体质量损失分析

为了获得空间粒子撞击对结构性能的影响规律,开展了对某型号空间充气展开天线反射器受空间粒子冲击作用下的内部气体质量损失和内部充气压力变化的分析.结果表明:气体质量损失与时间呈平方递增关系,且随入射粒子的直径以及内部充气压力的增加而增加.消除反射面薄膜褶皱的最优内部充气压力为12 Pa.薄膜材料的充气圆环内部充气压力至少要达到16.8 kPa.分析结果为空间充气展开天线反射器表面精度控制提供依据.     

哈尔滨松仁小肚加工工艺

1原辅料1.1原料 猪肌肉、绿豆淀粉、猪膀胱等。1.2辅料 食盐、花椒面、乳化胶、白糖、味精、香油、香精等。2主要设备     

Wrinkling analysis of square space membrane structure under corner tension forces

An analytical approach based on the bifurcation theory is presented, in which the wrinkles are treated as the local buckling phenomena of the elastic thin plate with little bending stiffness. The average wrinkling wavelength was determined by incorporating the stress field and the out-of-plane force equilibrium condition of the wrinkled membrane. The wrinkling amplitude was then obtained by associating the characteristics of wrinkling texture with the obtained wrinkling wavelength. Results reveal that the wrinkled pattern exhibits a noticeable difference when the tension load is changed gradually, and two wrinkling styles are identified. The first style occurs for symmetric and moderately asymmetric loading, and it is characterized by small, radial corner wrinkles; the second style occurs for strongly asymmetric loading and is characterized by a deep, large diagonal wrinkle. The analytical predictions on the wrinkling characteristics and the developed rules are validated against wrinkling experimental observations.     

平流层飞艇气动阻力的参数分析

为了研究环境参数及外形布局对平流层飞艇气动阻力的影响,在验证CFD数值模拟方法的基础上,从气动阻力包括压差阻力与摩擦阻力的角度探讨了风速、动力粘度系数、空气密度、Re数、长细比及尾翼对飞艇气动阻力的影响规律及机理。结果表明：气动阻力系数随风速与空气密度的增加而减小,随动力粘度系数的增加而增加;气动阻力系数随Re数减小的趋势,取决于摩擦阻力系数随Re数的减小趋势;随长细比的增加,摩擦阻力系数呈现增加趋势,但气动阻力系数呈现先减小后增加的趋势;尾翼对气动阻力系数的影响主要体现在压差阻力系数的改变。     

受弯充气锥台的褶皱特性分析

充气锥台是空间充气膜结构的主要承载力构件单元之一,膜面褶皱是导致其承载力降低的关键因素。该文基于薄膜理论分析了受弯充气锥台的褶皱特性。借助褶皱的应力判定准则对褶皱特征参数进行了预报,得到了初始起皱位置和起皱力随充气锥台两端半径比的变化规律,并得到了数值分析结果的验证。该文的结果为空间充气薄膜结构的承载能力预报提供重要依...     

Prediction of wrinkles in the membrane

This paper presents an analytical approach for predicting the detailed out-of-plane wrinkle deformation that formed in the membrane. The analytical wrinkle model is based on the assumption that the membrane is able to resist small compressive stress once it has wrinkled. This model is developed for the cases of the rectangular membrane subjected to pure shear and local tension by using the equilibrium equation of the membrane in the deformed configuration. Predictions from this model are compared with the finite element simulation based on the nonlinear buckling finite element method and the results are found to be accurate.