The electromagnetic environment of spacecraft is analyzed, and several EMC problems in spacecraft system design are pointed out.
分析了空间飞行器所处的电磁环境，指出总体设计中的若干电磁兼容性问题；
The SOC design and implementation of the spacecraft system bus was studied, for example of the 1553b bus controller.
以1553 B总线控制器为例，采用SOC设计方法，研究了航天器系统总线的设计和实现。
The companies will provide data related to the development of their Crew Transportation System (CTS) design, including a spacecraft, launch vehicle, ground and mission operations and recovery.
这些公司将提供开发他们乘员运输系统(CTS)设计的有关数据，航天器，运载火箭，地面和任务运转以及回收。
During the design of spacecraft cryogenic system, some factors must be considered, including space cooler lifetime, power distribution, mass and vibration isolation requirements.
根据寿命、电能分配，质量和防振要求，提出在进行航天器低温系统设计时需要考虑的因素。
It is very important to find design defects and to improve the system reliability when digital human models based on anthropometric data are applied in simulation of manned spacecraft design scheme.
将基于人体测量参数的数字人体模型应用于载人航天器设计方案的仿真评价对发现设计缺陷，提高整个系统的安全可靠性具有重要意义。
In this paper, the basic theory of the inverse system method is introduced, and is used in the design of a spacecraft attitude control system.
本文首先介绍了逆系统方法的基本思想，然后将其用于航天器非线性姿态控制系统的设计中。
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.
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 problem of the experimental object design for ground experiment system of neutral buoyancy was one of the key to achieving demonstration effectually of the development of spacecraft.
中性浮力地面实验系统的实验体设计问题是有效实现空间飞行器研制阶段地面演示验证实验的关键技术之一。
For the multidisciplinary design optimization (MDO) of spacecraft with sub-vehicles, system mission requirements and disciplinary coupling relations are analyzed.
针对带子星航天器总体参数多学科设计优化（MDO）问题，进行系统任务分析和学科耦合关系分析。
Based on the results, a normal matrix design approach for spacecraft attitude control systems is developed by using a feedback perturbation description for system uncertainties.
基于正规性分析结果，使用系统不确定性反馈摄动描述对姿态控制系统的正规矩阵设计方法进行研究。
Based on the results, a normal matrix design approach for spacecraft attitude control systems is developed by using a feedback perturbation description for system uncertainties.
基于正规性分析结果，使用系统不确定性反馈摄动描述对姿态控制系统的正规矩阵设计方法进行研究。
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