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heat conductive equation
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  热传导方程
     A semi-discrete H~1-Galerkin mixed finite element approximation scheme of a heat conductive equation is given,and optimal error estimates between the approximation solution and the exact solution in L~2-norm,H~1-norm are obtained.
     采用H1 Galerkin混合有限元方法对一类热传导方程的初边值问题,提出了半离散H1 Galerkin混合有限元格式,通过误差分析,得到H1 Galerkin混合有限元解与真解的L2模和H1模的最优阶误差估计.
短句来源
     Analysis of H~1-Galerkin Mixed Finite Element Method For a Heat Conductive Equation
     一类热传导方程的H~1-Galerkin混合有限元分析
短句来源
     Based on the heat conductive equation and its boundary,the analytical solutions of interior temperature field and thermal deformation of YVO_4-Nd∶YVO_4 composite crystal were obtained.
     利用热传导方程,得出了YVO4-Nd∶YVO4复合晶体内部温度场及端面热形变的一般解析表达式。
短句来源
     The geometric factor is defined by solving the heat conductive equation, which describes the temperature characteristics in the case of the constant heat transferring coefficient.
     首先由热传导方程导出了求解热传导率随温度改变的部件的温升方程。
短句来源
     Tissue heat conductive equation is set up based on two-layered structure model. Finite difference algorithm is utilized to numerically simulate the temperature distribution in the brain tissue.
     最后以两层组织模型为基础,建立了颅脑组织热传导方程,用有限差分法求解组织内温度场分布。
短句来源
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  相似匹配句对
     Study on heat conductive NR
     导热天然橡胶的研究
短句来源
     Development of Heat Conductive Insulation Adhesive
     导热绝缘胶粘剂的研制
短句来源
     Heat and Firefighters
     Heat and Firefighters(高一适用)
短句来源
     CONDUCTIVE POLYMERS
     导电聚合物的进展
短句来源
     CONDUCTIVE COATING
     导电涂料
短句来源
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The heat conductive equations of coat and substrate materials under laser beam radiations are solved using the method of integral transformation, and the 3D temporal distribution of temperature is given under the some approximations. A numerical analysis is given for Cr-ZG 45 steel as an example .

本文采用积分变换法求解了在激光束辐照下涂层和基体材料中的热传导方程,并在一定的近似条件下,给出了温度场的三维、瞬时分布。以Cr—ZG45钢系统为例,进行了数值分析。

The reentry thermo-protection problem of space shuttle was solved mainly through well-conducted experiments. Chinese engineers now find it feasible and more efficient to supplement experiments with theoretical analysis. This paper presents a method for calculating ablative rate and internal temperature distribution of C-C nose cap of space shuttle. Theoretical analysis of C-C nose cap must overcome two main difficulties. These two difficulties are: 1)Heat-conduction is under moving boundary condition....

The reentry thermo-protection problem of space shuttle was solved mainly through well-conducted experiments. Chinese engineers now find it feasible and more efficient to supplement experiments with theoretical analysis. This paper presents a method for calculating ablative rate and internal temperature distribution of C-C nose cap of space shuttle. Theoretical analysis of C-C nose cap must overcome two main difficulties. These two difficulties are: 1)Heat-conduction is under moving boundary condition. With aerodynamic heating, the ablative consumption of material causes the thickness of thermo-protective layer to become thinner and thinner, resulting in continuously changing of heat-conduction pattern from body surface into its interior. Thus, heat-conductive calculation should take into account the rather difficult problem of moving boundary. 2)With aerodynamic state and thermo-protectiv material previously determined, wall temperature is the decisive factor influencing ablation, but wall temperature itself is much influenced by the heat conducted to structure. On the other hand, the degree of severity of ablation affects not only thermo-effect terms but also the speed of motion of moving boundary and consequently heat-conduction. In other words, ablation and heat-conduction are coupled, and this presents considerable difficulty which must be overcome in theoretical analysis. Besides, material anisotropy and physical properties that change with temperature also make calculations more difficult. In this paper, we establish equations of ablative outline and ablative rate on the basis of aerodynamic-thermochemical model, employ energy balancing method to establish transient heat-conductive equation that takes into account anisotropy and changing physical properties, treat properly the ablative moving boundary through coordinate transformation, and finally, successfully carry out the solution of coupled ablation and heat-conduction. Calculated distributions of ablative rate and temperature in C-C nose cap of shuttle are presented in Figs. 3(b) through . Preliminary tests indicate that our method of calculation shows good promise for perfecting calculations that are in agreement with experimental data.

本文对航天飞机机头的碳-碳热防护层,在再入的气动加热条件下,采用气动热化学烧蚀模型建立烧蚀方程,采用单元体能量平衡法建立各向异性、变物性材料的瞬态热传导方程,通过坐标变换处理烧蚀移动边界,并从物理平面转换到计算平面中去,然后成功地进行了烧蚀和温度场的耦合求解。计算结果表明了航天飞机机头碳-碳热防护层中的烧蚀和温度分布规律。

Basing on thermal interaction between laser and organization, we discussed the mechanism,and utilize heat conductive equation to describe it guantitatively. An evidence of clinical applications of laser acupuncture and moxibustion are obtained.

从激光对穴位组织的热作用,探讨激光针灸的作用机理,利用能量守恒建立穴位组织的热传导微分方程,对针灸作用作量化描述,为激光针灸的临床治疗提供理论基础。

 
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