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reentry flight
相关语句
  再入飞行
     Several Mechanics Problems in Computer Simulation of Reentry Flight
     再入飞行仿真的几个力学问题
短句来源
     Angle-of-attack and sideslip-angle estimation of reentry capsules of spacecraft in reentry flight
     飞船返回舱再入飞行迎角和侧滑角估计
短句来源
     These topics are as follows, the significance of optimal reentry trajectory calculation and control, performances of reentry trajectories, the approximate computation and accurate numerical solution of optimal reentry trajectory, reentry guidance and control system,optimal aeroassisted orbit transfers, the hybrid navigation system of space vehicle, the dynamics and control of small reentry vehicle, the penetration and interception during reentry flight, and the mutual relations among some reentry problems.
     这些专题是最优再入轨迹计算与控制问题的提出及意义,再入飞行轨迹的性能指标,最优再入轨迹的近似计算与精确数值解,再入制导与控制系统,各类最优气动辅助变轨问题,航天器的组合导航系统,小型再入体的动力学特性及控制问题,再入飞行中的突防与拦截问题,一些再入问题的相互关系等。
短句来源
     On the reasonable assumption of match AOA(angle of attack) flight,the mathematics simulation model of the reentry flight of a spaceship is formulated in this paper.
     在配平迎角飞行的合理假设下,建立了描述载人飞船再入飞行段弹道的数学仿真模型。
短句来源
  “reentry flight”译为未确定词的双语例句
     To overcome the disadvantages of the present sectional control method in lift reentry flight,the slid variable structure control and neural network dynamic counter control were used in out-loop and inner-loop for the reentry control respectively according to the dynamic mode in this paper.
     为克服升力式再入飞行器现有分段控制方法的缺陷,根据动力学模型,将滑模变结构控制和神经网络动态逆法控制分别用于飞行器再入控制的外环与内环回路。
短句来源
     Statistical Analysis of Safety Factor for Non-Controled Warhead in the Maximum Transverse Load Case of Reentry Flight Phase
     无控弹头再入段最大横向过载情况安全系数的统计分析
短句来源
     Reentry Flight Using Negative Lift of Space Vehicle
     航天运载器采用负升力返回再入研究
短句来源
     Advanced Control Method Research for Lift Reentry Flight
     升力式再入飞行器的先进控制方法研究
短句来源
     2) The nominal trajectory-based techniques include the methods to compute the reentry flight corridor, the reference trajectory and the track law of the reference trajectory.
     2) 标准轨道法。 给出了再入走廊的计算方法,阐述了参考阻力加速度-速度剖面的规划和跟踪问题。
短句来源
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  相似匹配句对
     and reentry flight time,etc.
     再入段飞行时间等
短句来源
     The Global Stability Analysis of Reentry Capsule Transonic Flight
     飞船返回舱跨声速全局稳定性研究
短句来源
     FLIGHT OF THE PHOENIX
     凤凰劫
短句来源
     Flight to Mercury
     飞向水星
短句来源
     EUROPEAN ATMOSPHERIC REENTRY DEMONSTRATOR
     欧洲再入大气层试验飞行器
短句来源
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Cryogenics has been widely applied in modern aeronautical and astronautical science. In this paper, application principles of cryogenic techniques in aerospace are discussed rather in detail. Their recent advances abroad and in China are briefly discussed, including the following five parts: (Ⅰ) Characteristics and application status of rockets propelled by cryogenic liquid hydrogen/liquid oxygen fuels and principles and characteristics of a new generation cryogenic liquid propellants for rockets, i. e. liquid...

Cryogenics has been widely applied in modern aeronautical and astronautical science. In this paper, application principles of cryogenic techniques in aerospace are discussed rather in detail. Their recent advances abroad and in China are briefly discussed, including the following five parts: (Ⅰ) Characteristics and application status of rockets propelled by cryogenic liquid hydrogen/liquid oxygen fuels and principles and characteristics of a new generation cryogenic liquid propellants for rockets, i. e. liquid oxygen/liquid light hydrocarbon; (Ⅱ) Characteristics and status of liquid hydrogen/liquid oxygen fuelled aeroplanes and liquid hydrogen, liquified natural gas (LNG) fuelled airplanes; (Ⅲ)Principles and working envelopes of cryogenic wind tunnels to carry out aerodynamic experiments at full-scale Reynolds number; (Ⅳ) Main application fields of cryogenics in the space technology and their requirements for the refrigeration temperature and load, characteristics and application status of various space cooling techniques; (Ⅴ) Application of cryogenics in the fields such as cooling reentry flight vehicles, space simulation facilities, environmental control system for flight vehicles and life support system, etc.

低温技术在现代航天航空科学中已获得广泛应用,本文从以下几个方面较全面地讨论了低温技术应用原理并简要介绍了它们在国内外航天航空中的一些重要应用及其进展。1.低温液体液氢/液氧推进剂火箭的特点,应用现状及新一代低温液体推进剂——液氧/轻烃火箭的原理和特点;2.液氢/液氧燃料空天飞机及液氢、液化天然气燃料航空飞机的特性和应用现状;3.低温风洞可在全雷诺数范围内进行气动试验的原理及工作特性;4.低温技术在空间科学中应用的主要领域及所需温度和制冷量范围,各种空间低温制冷方法的特点和应用现状;5.低温技术在再入飞行器冷却、空间环境模拟器、飞行器环境控制系统、生命保障系统等领域中的应用原理和特点。

In the paper, a parameter optimization method is used on the basis of the multiple shooting technique to calculate optimal trajectories. Choosing American shuttle orbitor as example, we calculate the optimal reentry trajectories with several performance indices and constraints. The calculated results are discussed comparing with the actual reentry flight trajectory of the shuttle orbitor. The effectiveness of the method and program is summrized.

本文采用基于多重打靶技术的参数优化方法,以美国航天飞机轨道器为例,选取了几种目标函数和约束条件,对其最佳再入轨迹进行了计算.将计算结果与美国航天飞机的实际再入轨迹作了比较,并对文中采用的算法和程序的适用性进行了小结。

The optimal reentry trajectory is designed with the help of Drag Reference Profile (DRP). The DRP is first selected in the reentry flight corridor formed by fundamental contraints, such as, maximal dynamic pressure, maximal heating rate, maximal acceleration overload and maximal surface temperature limits. Then the DRP is adjusted to satisfy the required footprint and the terminal guidance demands. Finally, the DRP is determined by optimization of minimal total heat load input with satisfication of above...

The optimal reentry trajectory is designed with the help of Drag Reference Profile (DRP). The DRP is first selected in the reentry flight corridor formed by fundamental contraints, such as, maximal dynamic pressure, maximal heating rate, maximal acceleration overload and maximal surface temperature limits. Then the DRP is adjusted to satisfy the required footprint and the terminal guidance demands. Finally, the DRP is determined by optimization of minimal total heat load input with satisfication of above two considerations. The guidance law for the Shuttle reentry is given and some numerical calculations using the data of American Space Shuttle are made to verify the method. The results are satisfied.

本文研究航天飞机受过载、动压及加热约束情况下,总加热量最小的最优再入轨迹与制导问题。文中给出了确定阻力参考型、再入飞行走廊的方法与模型,建立了相应的制导律,以总加热量最小为性能指标,通过适当选取阻力参考型的变化,将再入轨迹的优化转换成参数的优化问题。并以美国航天飞机数据为例进行了模拟计算,得到了满意的结果。

 
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