利用这一模型，可以为不同复杂度的航天动力学建模提供支持，方便构筑面向具体问题的应用。
The models can provide support on various complexity simulation and the application question-oriented can be built expediently.
这次的太阳喷发，即日冕物质抛射，是由美国国家航空航天局(NASA)的太阳动力学观测卫星(SDO)观测到的，它同时还拍到了太阳在不同波长时的一组清晰照片。
The solar eruption, called a coronal mass ejection, was spotted by NASA's solar Dynamics Observatory, which captures high-definition views of the sun at a variety of wavelengths.
这些照片都是在太阳动力学观测站上拍摄到的，它目前是研究太阳这个天体中，最先进的航天器。
The pictures were taken by the Solar Dynamics Observatory (SDO), which is the most advanced spacecraft ever designed to study the Sun.
2010年10月7日，当一轮新月从太空飞船（与地球同步轨道）和太阳之间直接经过时，美国国家航空航天局太阳动力学观测台观测到了圆月的运转。
On Oct. 7, 2010, NASA's Solar Dynamics Observatory, or SDO, observed its first lunar transit when the new moon passed directly between the spacecraft (in its geosynchronous orbit) and the sun.
国外载人航天活动各阶段心脏动力学参数是检测的重点之一。
Cardiac kinetics serves as important cardiovascular parameters during various stages of space activities.
阐述了航天多铰接机械系统类型及其相关的动力学建模方法。
The types of space multi joint mechanical systems and related dynamic modeling methods have been set forth.
以航天光学工程中实际的相机模型为例，重点研究了超单元在模态分析和动力学分析中的适用性。
The applicability research was done importantly for super-elements in the analysis of mode and dynamics, taking a space camera model used in the space-optics engineering for example.
研究带周边式对接机构的航天器在对接捕获过程中的缓冲动力学行为。
The dynamic process of capturing and docking space vehicles with the androgynous peripheral docking mechanism is studied.
将空气的影响视为附加在电池阵上的广义质量，用数值方法模拟了航天器太阳能电池阵在地面试验空气介质中展开时的动力学过程。
Dynamic procedure of deployment of a solar array in the ground environment was simulated by numerical method, where the air influence was regarded as added generalized mass.
实现了对航天可展结构动力学性能在时频域内的“精细”考察，将有助于提高航天器结构的分析与设计水平。
The results provide precise measurements of the dynamics characteristics of the space deployable structure in the time-frequency domain, which are helpful for improving the system analysis and design.
得到的航天器动力学方程具有通用性和程式化的特点，便于计算机编程可视化实现。
The dynamic equations of the spacecraft derived above are universal and programmed and is easy to realized by the computational procedure.
本文的研究结果，对于航天、航空、航海中的充液系统动力学与控制问题，都有重要的参考价值。
The results of this paper are useful for the dynamics and the control of liquid-filled systems in the astronautics and aeronautics and ocean engineering.
介绍了键图理论应用于建立复杂航天器系统的动力学模型的基本思想以及拉格朗日键图的具体应用步骤。
The fundamental idea of dynamic modelling of complex spacecraft system using Bond Graph theory, and the procedure of using Lagrange Bond Graph are discussed.
在激光天文动力学任务概念研究方面，必须对由远程航天器上传回的激光进行讯号的测量与处理。
In carrying out the research projects on laser space Programs, it is necessary to process the laser signal sent back from the remote spacecraft.
建立了两个航天器对接系统的约束动力学方程。
The constrained dynamics equation for two spacecraft docking system is established.
本文简要概述了动力学在航天器设计领域的部分应用情况，着重体现了CAE仿真在工程设计中的应用进展。
In the paper, some successful application of dynamics in the design area of spacecraft are presented and the advance of CAE simulation technique in practical engineering is emphatically discussed.
对航天器姿态动力学模型和姿态控制技术进行了概括和总结。
The model of spacecraft attitude dynamics and the attitude control technology are generalized.
风洞是空气动力学研究的重要地面试验设备，是保证一个国家航空航天处于领先地位的基础研究设施。
Wind tunnels are important ground facilities for aerodynamic research, and basic research establishment to ensure aeronautics and astronautics of a country keeping ahead in the world.
以一个呈现混沌姿态运动的航天器动力学模型为例说明了该控制律的应用。
A mathematical model derived from spacecraft attitude dynamics is treated as an example to demonstrate its application.
在空气动力学平稳鼻锥将在发射航天器的保护。
The aerodynamically smooth nose cone will protect the spacecraft during launch.
高级动力学：刚体，多体，和航空航天应用。
Advanced Dynamics: Rigid body, Multibody, and Aerospace Applications.
利用动量矩定理推导出带挠性伸展附件航天器的动力学方程。
The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.
带伸展柔性附件航天器的动力学方程是刚-柔耦合的时变非线性动力学方程，用传统方法求解其动力学响应时会遇到很大的困难。
The dynamic equation of the spacecraft with extensional flexible appendages system is time variable and nonlinear, so it is very difficult to solve this kind of equation with traditional methods.
首先建立了以变速控制力矩陀螺为执行机构的航天器姿态动力学模型，并给出了全局稳定的姿态反馈控制律。
The attitude dynamic equation of a spacecraft with VSCMG attached and a global asymptotical attitude feedback control law are presented firstly.
本文借助15段的人体模型，使用多刚体动力学的方法建立起航天员转体动作的力学模型。
By using a body model of 15 segments and dynamics of rigid bodies, the astronaut's self rotation is modeled.
研究一类构形为中心刚性带挠性梁的航天器平面快速大角度机动的动力学与控制问题。
This paper is concerned with the dynamics and control for planar, large Angle rapid slew maneuvering of a flexible multi body spacecraft, consisting of a rigid central body and a flexible beam.
所得结果不仅适用于具有大型运动部件的航天器的姿态动力学分析及控制系统设计，也适用于灵敏小卫星的相应研究。
The proposed results are useful to the attitude dynamic analysis and control system design for not only the spacecraft with large rotation parts, but also the agile small satellite.
研究柔性航天器的动力学与控制问题时，通常需要利用柔性附件的模态信息。
Researches on the dynamic and control for the flexible spacecraft usually use the modal of the flexible appendages.
研究柔性航天器的动力学与控制问题时，通常需要利用柔性附件的模态信息。
Researches on the dynamic and control for the flexible spacecraft usually use the modal of the flexible appendages.
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