| 1. | This system, depicted in figure 1-8, is usually referred to as the apollo spacecraft .
通常所谓的“阿波罗”空间飞行器，其系统如图1-8所示。 |
| 2. | Also, loads and control forces imposed by space vehicle guidance systems are generally small .
此外，由空间飞行器导引系统所产生的载荷与控制力一般是很小的。 |
| 3. | The persistence of wind over varying intervals of time is important in the launch of space vehicles .
在不同时间间隔内风的持续性对空间飞行器的发射量是很重要的。 |
| 4. | Decoupling sliding mode control in a nonlinear spacecraft system
非线性空间飞行器系统的解耦滑模控制 |
| 5. | Microorganisms and plants onboard flight device in near - earth space
近地空间飞行器搭载微生物及植物的研究进展 |
| 6. | Pursuit - evasion barrier of two spacecrafts based on the sightline coordinate system
空间飞行器在视线坐标系中的追逃界栅 |
| 7. | However , launching a spacecraft is a high - cost , high - risk venture
然而,空间飞行器的发射是一项高投入、高风险的任务。 |
| 8. | This system , depicted in figure 1 - 8 , is usually referred to as the apollo spacecraft
通常所谓的“阿波罗”空间飞行器，其系统如图1 - 8所示。 |
| 9. | They would inflict no lasting damage to spacecraft and create no debris in orbit
这些陆基系统不会对空间飞行器造成持久性的伤害并且不会在轨道上生成碎片。 |
| 10. | Problem formulation , modeling and simulation of the spacecraft attitude and trajectory control . 2
空间飞行器姿态和轨迹控制问题的数学分析、建模以及仿真。 |
