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热防护系统
相关语句
  thermal protection system
     Metallic thermal protection system (MTPS) is one of the key technologies for developing reusable launch vehicle (RLV).
     金属热防护系统(MTPS)是可重复使用运载器(RLV)的关键技术之一,而隔热材料是金属热防护系统的主要隔热部件。
短句来源
     Thermal Model Study of RLV Ceramic Thermal Protection System
     RLV陶瓷热防护系统热分析模型研究
短句来源
     History and developments of rlv's metallic thermal protection system
     可重复使用运载器金属热防护系统的历史与发展动态分析
短句来源
     Design and Analysis of Metallic Thermal Protection System Attachment
     金属热防护系统连接结构设计与分析
短句来源
     Development of Insulations for Metallic Thermal Protection System and its Current Status
     金属热防护系统隔热材料的发展与现状
短句来源
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  thermal protect system
     In order to meet the requirement of the fourth generation metal thermal protect system development, it is necessary to prepare large scale high-temperature alloy sheet.
     应第四代金属热防护系统发展的需要,大尺寸高温合金薄板的制备已成为必须攻克的难关。
短句来源
  “热防护系统”译为未确定词的双语例句
     New-typed ARMOR thermal protection systems
     新型ARMOR热防护系统
短句来源
     After C/C and ceramic-matrix composite used in space orbiter,one new-typed thermal protection systems(TPS)-ARMOR TPS is coming forth. ARMOR TPS is means adaptable,robust,metallic,operable,reusable TPS.
     在经历了C/C与陶瓷基复合材料等热防护结构后,一种新型的热防护系统应运而生-ARMOR(Adaptable,Robust,Metallic,Operable,Reusable)热防护系统(TPS)。
短句来源
     Finite Element Analysis of Metallic Thermal Protection Systems Design
     金属热防护系统设计的有限元分析
短句来源
     The effects of several modeling issues on TPS sizing are analyzed,and a change in initial temperature from 40℃ to 0℃ produces the decreases of 7.7% in TPS mass and 17% in thickness.
     分析了模拟条件对热防护系统尺寸设计的影响:初始温度为0℃时比为40℃时最大可以减少17%的厚度和7.7%的质量;
短句来源
     Development of Flexible Thermal Protection for System Inflatable Re-entry Vehicles
     充气式再入飞行器柔性热防护系统的发展状况
短句来源
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  thermal protection system
Heat and mass transfer associated with low-velocity vapor flow in the plane channel of a thermal protection system of the radiat
      
A thermal protection system with evaporation into an inner cavity is considered.
      
Modeling the unsteady heat and mass transfer in the vapor outlet channel of a radiative-evaporative thermal protection system
      
Efficiency of a radiative-evaporative aircraft thermal protection system
      
The coupled boundary-value problem of nonstationary heat and mass transfer within the outer thermal insulation layer and the vapor outlet channel of a combined radiative-evaporative thermal protection system is formulated.
      
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  thermal protection system (tps)
One of the major obstacles hampering a full the realization of the CAV concept is a present lack of lightweight, high-temperature insulation materials which can be used for construction of the CAV's thermal protection system (TPS).
      
A critical element of these vehicles is the thermal protection system (TPS).
      


The background and tasks of thermomechanics of aerospace structures are presented. First its prerequistes are discussed:load spectra and materialCharacteristics.Then some typical structural concepts are introduced,such as:heat protection system during entry, orbital structure, and the use of carbonfiberreinforced polymers in airplanes. From these concepts the tasks of thermome-chanics of aerospace structures are deduced: thermal analysis, structural analysis,thermo- damage mechanics, thermomechanical coupling...

The background and tasks of thermomechanics of aerospace structures are presented. First its prerequistes are discussed:load spectra and materialCharacteristics.Then some typical structural concepts are introduced,such as:heat protection system during entry, orbital structure, and the use of carbonfiberreinforced polymers in airplanes. From these concepts the tasks of thermome-chanics of aerospace structures are deduced: thermal analysis, structural analysis,thermo- damage mechanics, thermomechanical coupling analysis as well as struc- tural testing. Finally, its prospect is given.

本文给出航天结构热力力学的应用背景和工作任务.首先讨论它的先决条件:载荷谱和材料特征.其次介绍一些典型的热力力学结构:再入热防护系统,轨道空间结构,以及碳纤维增强复合材料板件.然后,介绍热力力学的工作内容:热分析,经典结构分析,热损伤力学,以及热力力学耦合和结构试验.最后为简单展望.

The corridor and trajectories of space vehicle during reentry flight using negative lift are studied. Numerical results are obtained for the corridors and trajectories using negative and positive lift respectively.Then the conclusions are obtained as:Under the circumstances of larger lift-drag-ratio,the first one third reentry corridor using negative lift is wider than the one using positive lift,the total mass cost(TMC)by negative lift is smaller than the one by positive lift,where TMC is the total mass of...

The corridor and trajectories of space vehicle during reentry flight using negative lift are studied. Numerical results are obtained for the corridors and trajectories using negative and positive lift respectively.Then the conclusions are obtained as:Under the circumstances of larger lift-drag-ratio,the first one third reentry corridor using negative lift is wider than the one using positive lift,the total mass cost(TMC)by negative lift is smaller than the one by positive lift,where TMC is the total mass of the fuel consumption for the vehicle to deorbit from the mission orbit and thermal protection system of the vehicle;under the circumstances of smaller lift-drag-ratio,the two kinds of reentry trajectories produced by positive lift and negative lift are approximately the same.Therefore, the concept of return flight using negative lift is superior to the one using positive lift.

研究了采用负升力返回时航天器的再入走廊与轨迹,通过数值仿真和与正升力再入时的结果比较,得到结论:在大升阻比情况下,采用负升力再入时的返回走廊前三分之一段较采用正升力的相应部分宽度有较大增加,离轨点所耗燃料质量与热防护系统质量之和较正升力再人时的情况有一定减小;在小升阻比情况下,正、负升力再入时轨道特性、有效载荷基本相同。从而得出,负升力再入概念在提高有效载荷上明显优越于正升力再入概念。

The paper stuidied how to obtain the maximum payload by the optimal reentry trajectories under the following circumastances: When TPS mass of space vehicle is not determined, the maximum payload is obtained by the optimal return trajectory design, then TPS mass is determined; when TPS mas of the space vehicle is determined, the maximum payload is obtained by the design of optimal reentry trafetory; when the TPS mass is enough large, the maximum payload of the vehicle can be obtained by multipe-pass atmosphere....

The paper stuidied how to obtain the maximum payload by the optimal reentry trajectories under the following circumastances: When TPS mass of space vehicle is not determined, the maximum payload is obtained by the optimal return trajectory design, then TPS mass is determined; when TPS mas of the space vehicle is determined, the maximum payload is obtained by the design of optimal reentry trafetory; when the TPS mass is enough large, the maximum payload of the vehicle can be obtained by multipe-pass atmosphere. The conclusion of the paper provides a design method for the reentry trajectory/TPS of the vehicle.

本文研究的目的是想获得具有最大有效载荷的航天器最优再入轨迹。返回段航天器的最大有效载荷等价于航天器离轨点所耗燃料质量与热防护系统(TPS)质量之和达极小。文中把最大有效载荷的再入轨迹分三种情况作了分析:航天器TPS质量不确定时,通过返回轨迹优化来获得航天器的最大有效载荷,并选择确定相应TPS的质量;TPS质量已确定时,通过再入轨迹优化来获得航天器的最大有效载荷;TPS质量足够大时,通过多次穿越大气层来获得航天器的最大有效载荷。本文的结论可为航天器再入轨迹与TPS的一体化选择提供思路。

 
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