航天器结构复杂，运行环境恶劣。
Spacecraft has complex structure, and it needs to work in harsh environment.
利用试验数据修正航天器结构动力模型时，使用缩聚方法使有限元自由度与试验自由度匹配。
When the spacecraft structural dynamic model is updated using test data, the freedom of FEM can be matched with test freedom by means of reduction method.
基于航天器结构的模块化设计概念，设计了一种空间可展开航天器模块化结构构型，即铰链展开式构型。
Based on modular design idea of the spacecraft structure, a hinged deployable configuration for the spacecraft was designed.
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.
斯坦福大学的“专家系统”计划始于1965年，用于美国国家航空航天局航天器收集物质的化学测量二十年，来推算其有机分子的可能结构。
Stanford University's Dendral project, was started in 1965 and used for two decades to extrapolate possible structures for organic molecules from chemical measurements gathered by NASA spacecraft.
研究了GPS在一类没有结构和力约束，但存在运动约束的多航天器系统中的应用。
The applications of GPS in a multi spacecraft system with kinematical restraint but no structural restraint and force action to each other are studied in this paper.
结构系统的振动控制是改善航天器动态特性的重要途径。
Structure vibration control is of great importance for the melioration of spacecraft dynamic property.
航天器的蒙皮是抵御空间碎片超高速撞击的最基本防护结构。
Skin of spacecraft is usually considered as the most basic shield structure against hypervelocity impact of space debris.
航天器不仅给出科学家最想看到的背景辐射，而且建立了描述宇宙历史与结构的科学模型。
The spacecraft has not only given scientists their best look at this remnant glow, but also established the scientific model that describes the history and structure of the universe.
作为应用的例子给出了超高速撞击条件下航天器空间碎片防护结构以及压力容器损伤特性实验研究的结果。
The results of spacecraft space debris shield configuration, as well as pressure vessel damage behavior characteristic under hypervelocity impact conditions are presented as applications.
结构复杂的航天器带有几十米、上百米大型挠性附件，附件末端还带有大质量刚体。
The coupled dynamic equations of a spacecraft with tip mass attached flexible appendage which is deployable are obtained by using the momentum theorem.
太阳帆航天器动力学建模与求解是姿态控制与结构振动抑制的基础，具有重要的理论与工程意义。
Solar sail spacecraft dynamic modeling and solving are the basis of attitude control and structural vibration suppression, and they are of important theoretical and engineering significance.
由于结构、重量、电能及电子系统的要求，航天器上要用到大量的介质材料，某些介质材料还必须直接暴露于空间环境之中。
Because the demand of construction, weight, electric power and electronics system, a lot kinds of dielectrics be used in spacecrafts. Some dielectrics had to be exposed directly in space environment.
结构锁是实现两航天器空间对接的机电装置。
Structural lock is an electromechanical equipment that connects rigidly two space shuttles together.
针对现代航天器对控制任务的需求特点，基于航天器对象特征模型知识描述，提出了具有多层结构的智能自适应控制系统概念。
According to the requirements of modern spacecraft control, this paper presents a hierarchical intelligent adaptive control system based on the description of plant feature model knowledge.
针对挠性航天器执行器卡死与失效故障的姿态稳定控制问题，提出了一种结构简单、计算量小的改进型滑模容错控制策略。
A modified sliding mode fault tolerant controller is developed for flexible spacecraft attitude stabilization control in the presence of loss of actuator effectiveness fault and actuator stuck fault.
介绍弹道式再入航天器烧蚀防热结构设计，文中说明了方案、材料选择、设计和分析计算。
This paper introduces ablative thermal protection structure design of a return module of some satellites.
讨论了一类非最小相位系统的输出跟踪问题。非最小相位系统广泛存在于机器人柔性结构控制、飞机的飞行控制和航天器发射等实际问题中。
Output tracking problems for non minimum phase system existed in many practical problem, such as aircraft flight controlling, spacecraft launching and flexible manipulation, are considered.
针对一类航天器外伸结构的结构振动问题，提出了一种动应变控制方法。
Some space structures have critical vibration problems owing to their low stiffness and low damping.
为解决柔性航天器姿态机动的控制问题，给出了基于输出反馈的变结构跟踪控制算法。
To solve the attitude maneuver of a flexible satellite, this article presents a variable structure tracking control algorithm based on output feedback.
可重复使用运载器的防热瓦故障会使航天器的局部结构产生热源，并在结构中形成温度场。
The malfunction of thermal protection system on reusable launch vehicle will generate a heat source on the part of vehicle.
可重复使用运载器的防热瓦故障会使航天器的局部结构产生热源，并在结构中形成温度场。
The malfunction of thermal protection system on reusable launch vehicle will generate a heat source on the part of vehicle.
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