共查询到20条相似文献,搜索用时 687 毫秒
1.
为了揭示低温推进剂贮箱的增压规律和热分层特性,在以液氮为贮存介质的低温流体高效贮存平台上,进行了不同充注率下的贮箱自增压及氦气增压实验。得到充注率分别为35%,50%和65%时的贮箱增压速率分别为7.54 kPa·h~(-1),13.02 kPa·h~(-1)和28.26 kPa·h~(-1).获得了达到相同压力水平时各自充注率对应的温度分布,分析了不同充注率时贮箱温度梯度的变化规律。最后使用常温氦气作为增压气体,将贮箱充注率为50%的贮箱分别增压到180 kPa,380 kPa和580kPa,分析了氦气充注过程及达到不同压力水平时贮箱内温度分布变化规律. 相似文献
2.
3.
4.
5.
6.
7.
针对页岩气流动计算中所用耦合机理不同的现状,且为了厘清滑脱和各种扩散之间的关系,首先采用理论分析和数学模型的方法,根据定义和微观运动机制对滑脱和各种扩散进行了分析,然后在考虑吸附层页岩气分子所占空间对气体流动影响的情况下,提出了"壁联扩散"的概念来表征克努森扩散和表面扩散的总效应,并指出壁联扩散和滑脱效应等同,由此提出了壁联扩散和滑脱效应在流动计算中可互换而不重复叠加的耦合新方法.实例验证表明,当毛细管半径从5 nm增大到2000 nm,壁联扩散和滑脱效应的质量通量相对误差较小,在绝大部分范围内都小于10%,且在整个孔径范围内两者平均值相差1.4×10~(-6)kg·m~(-2)·s~(-1),即平均值的相对误差仅为5.8%,该方法可以满足工程计算的需要.考虑到参数选取、机理数学模型有待完善等方面的影响,新方法的论证存在进一步提升的空间.壁联扩散的提出具有实际开发意义和多重研究意义,耦合新方法的提出阐明了滑脱和各种扩散之间的关系,防止了页岩纳米级孔隙中流动机理的重复叠加,能较好改变页岩气流动计算耦合方法不一致的现状,为页岩气开发定量计算指明新方向. 相似文献
8.
针对现代飞机设计对于高效率、高精度飞行载荷分析的迫切需求,建立了面向飞机各设计阶段考虑静气动弹性效应的面元法飞行载荷分析方法,并以此为基础构建了飞机各设计阶段气动弹性优化框架,以加快各阶段的迭代,提高设计效率.概念设计阶段的气动力分析采用低阶面元法,可适应该阶段为确定气动外形参数范围所需的大量计算.初步设计阶段采用高阶面元法开展气动力分析,以兼顾求解精度和效率的需求.详细设计阶段的飞行载荷分析方法在基本面元法的基础上引入了外部高精度CFD气动力或试验气动力,以进一步提高飞行载荷的精度并兼顾求解效率.研究结果表明,所建立考虑静气动弹性效应的面元法飞行载荷分析方法具有较强的工程实用性,可以满足现代飞机各个设计阶段的需要. 相似文献
9.
10.
11.
K. H. Kim H. -J. Ko K. Kim Y. -S. Jung S. -H. Oh K. -J. Cho 《Journal of Engineering Thermophysics》2012,21(1):1-15
The transient thermal behavior in the cryogenic oxidizer tank for the liquid propulsion system of the KSLV-I satellite launching
space vehicle is theoretically investigated for the pressurization process by gaseous helium injection followed by the readiness
check stage. The numerical model is established using the transient mass and energy conservation of oxygen/helium mixtures
both in ullage and liquid regions. At the liquid-gas interface, various modes of heat and mass transfer are considered, including
the liquid evaporation and the helium absorption. The present study focuses on the effects of the increasing pressurization
level on some of important properties that should be considered in the propulsion system design, such as tank pressure, ullage
gas temperature, and evaporation of liquid oxygen. Particularly, the tank pressure drop after the pressurization is investigated
in the proposed design of propulsion system. Also, the effect of the initial loading of liquid oxygen in the oxidizer tank
is studied and discussed. As for the helium absorption into the liquid region, its mass is negligibly small and it should
not be the concern in design and operation of the oxidizer tank system. 相似文献
12.
13.
14.
Dynamic analysis of solid propellant grains subjected to ignition pressurization loading 总被引:2,自引:0,他引:2
Shiang-Woei Chyuan 《Journal of sound and vibration》2003,268(3):465-483
Traditionally, the transient analysis of solid propellant grains subjected to ignition pressurization loading was not considered, and quasi-elastic-static analysis was widely adopted for structural integrity because the analytical task gets simplified. But it does not mean that the dynamic effect is not useful and could be neglected arbitrarily, and this effect usually plays a very important role for some critical design. In order to simulate the dynamic response for solid rocket motor, a transient finite element model, accompanied by concepts of time-temperature shift principle, reduced integration and thermorheologically simple material assumption, was used. For studying the dynamic response, diverse ignition pressurization loading cases were used and investigated in the present paper. Results show that the dynamic effect is important for structural integrity of solid propellant grains under ignition pressurization loading. Comparing the effective stress of transient analysis and of quasi-elastic-static analysis, one can see that there is an obvious difference between them because of the dynamic effect. From the work of quasi-elastic-static and transient analyses, the dynamic analysis highlighted several areas of interest and a more accurate and reasonable result could be obtained for the engineer. 相似文献
15.
16.
17.
In this paper infrared emission spectra of the solid propellant combustion using remote Fourier transform spectroscopy have been studied. Both the infrared spectral radiance distributions and gas quantitative method for solid propellant combustions by remote Fourier transform infrared emission spectroscopy have been presented. In the method we utilize estimating temperature measuring models, which are modified by Junde Wang, based on emission fundamental band measurements of HCl or HF. Through measuring the temperature both the infrared spectral radiance distributions of the solid propellant combustions and their emisivities can be obtained. A remote measured gas concentration model based on combustion temperature, spectral radiance and emissivity has been developed. Field single-ended measurements at long distances for solid propellant plumes at temperature 1700—3500K can be extended to measuring fluctuations of instantaneous temperature and combustion reaction products. 相似文献
18.
We present a study of the one-dimensional flame structure of combusting solid propellants that focuses on the effects of thermal expansion and variable thermal properties in the condensed phase. A nonlinear heat equation is derived for a burning thermo-elastic solid with temperature-dependent specific heat, thermal expansion, and thermal conductivity coefficients. It is solved for different modelling approximations both analytically and numerically. Explicit expressions are derived for the regression rate of the propellant surface as functions of surface temperature and thermal expansion parameters. A simple one-step reaction model of the gas phase is used to study the full structure of propellent flame and illuminate the influence of temperature-dependent material properties on the regression rate, surface temperature, and flame stand-off distance. Results are displayed for HMX and compared with experimental data and numerical simulation with fair success. 相似文献
19.
为了更好地描述变燃速发射药的膛内燃烧及内弹道过程,对中心开孔式双层结构的变燃速发射药建立了一维两相流内弹道数学模型,在Φ30 mm火炮装填条件下采用二阶精度的Lax-Wendroff差分格式进行计算,得到了数值解。计算结果表明:膛内压力和炮口初速度变化曲线的计算值与实测值符合较好,说明此两相流内弹道模型可以准确地反映变燃速发射药的内弹道过程;变燃速发射药可以有效地减少膛内压力波的产生,对于安全射击具有重要意义。通过对气、固相速度及膛内压力波等计算参数进行分析,可以对变燃速发射药的内弹道过程研究起指导作用。 相似文献
20.
This paper reports the results of numerical studies carried out for a periodic sandwich propellant geometry with two-dimensional unsteady gas and condensed phase. A non-planar regressing surface along with a kinetic model of two reaction steps in the gas phase was used. This paper discusses the importance of lateral momentum equation to the combustion of sandwich propellants. It demonstrates that the instabilities in sandwich combustion reported in literature are due to neglect of lateral momentum equation and incorrect boundary conditions at the regressing surface. It demonstrates that neglect of momentum equations will lead to a different result from the one obtained considering the momentum equations for sandwich propellants. 相似文献