The likeness between the model output and the actual output of human operator has been illustrated in experiments with spacecraft dynamics ( 1/ S2).

It is typically difficult to experimentally replicate spacecraft dynamics in an Earth-bound laboratory because of the influences of gravity and friction.

由于地球引力和摩擦的影响，要想在地球上的实验室实际复现航天器动力学无疑是非常困难的。

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Active vibration control of Large Flexible Solar Array ( LFSA) is a challenging subject in the domain of spacecraft dynamics and control.

大型挠性太阳能电池翼的振动控制是航天器动力学与控制领域的挑战性课题。

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Then, attitude control law of an accompanying satellite using Lyapunov function based on spacecraft dynamics is derived.

根据航天器动力学方程，利用李雅普诺夫直接法推导出用四元数表示的空间站伴随卫星姿态控制律，并对该控制律进行了仿真计算。

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A study on large-scale amplitude sloshing of fluid in a propellant container is essential for the detailed analysis of spacecraft dynamics and control.

对在推进剂贮箱中带有自由液面液体大幅晃动问题的研究是一个在充液航天器动力学与控制分析中十分重要的问题。

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Development generalization of spacecraft dynamics

航天器动力学发展概况

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With the development of the aerospace technology, the requirements for spacecraft rendezvous and docking related technologies are getting more and more complex.

随着我国航天技术的发展，空间飞行器的交会对接相关技术的发展迫在眉睫。

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Docking Dynamics Simulation of Spacecraft with Peripheral Docking Mechanism ( Part: I)& Equation of Kinematics Constrained

周边式对接机构航天器的对接动力学仿真（第1部分）&运动学约束方程

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Optical Sensor for Spacecraft Rendezvous and Docking

用于空间交会和对接的光学敏感器

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Ladar is one of the guidance sensors in the spacecraft rendezvous and docking.

激光雷达可以作为空间交会对接过程中的相对导航敏感器之一。

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The practicability of laser radar sensor used for spacecraft rendezvous nd docking have been discussed in this paper.

本文讨论了在航天飞行器的空间交会对接（RVD）技术中采用激光雷达敏感器的可行性。

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The Optical Measurement of Self-Calibration in Orbit for Spacecraft Rendezvous and Docking

空间飞行器交会对接相对位置和姿态的在轨自检校光学成像测量算法

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Laser Radar Sensor for Spacecraft Rendezvous and Docking

空间交会对接用激光雷达敏感器

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A simple and practical single-target system is presented for autonomous spacecraft rendezvous and docking.

提出在航天飞行器的自主交会对接技术中，应采用一种简单、实用的单目标系统。

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Selection and Determination of the Launch Time for Spacecraft Rendezvous and Docking

航天器交会对接发射时间的选择与确定

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Algorithm of Determining Relative States for Computer Vision System Used During Spacecraft Rendezvous and Docking

航天器交会视觉导航系统相对状态确定算法

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Therefore, spacecraft rendezvous and docking technology should be paid much attention.

因此，交会对接技术受到重视。

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So the developing process of a docking mechanism and the research on spacecraft on-orbit docking process dependent on HIL simulation system to test or simulate docking process.

对接机构的研制过程和空间对接过程的研究都需要依靠半物理仿真技术，在地面上完成空间对接过程的试验和仿真、空间对接系统及其子系统的检验和验收。

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One of the key problems of two spacecraft's docking simulation in the period from approach to first contact is to determinate the contact points.

确定接触点问题是航天器对接过程中接近与接触阶段的仿真的关键问题。

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The dynamic model of spacecraft docking test table was studied. The equations with dynamic constrain in contact point and contact force model during the docking process were built, and five-freedom kinematic model of capturing process was built by Newton-Euler method.

对航天器对接试验台的动力学建模问题进行了研究，建立了接触点的动态变约束方程、对接碰撞力模型，并应用牛顿-欧拉方法提出了五自由度下捕获阶段运动学模型。

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Recently, the wide-range six-component force/ torque sensor becomes the urgent need high-tech product, which can be used in thrust testing of rocket engines, flight testing of airplane, testing of spacecraft docking simulation and wind tunnel.

近年来，应用于火箭发动机推力试验、飞机试飞试验、航天器对接模拟试验及风洞试验等领域的大量程六维力传感器，成为急需的高科技产品。

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