Spacecraft dynamics

Development generalization of spacecraft dynamics

航天器动力学发展概况

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。

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。

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。

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。

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

文中还以飞船动力学（1/S~2）实验为例，说明模型输出与人操作者实际输出的拟合程度。

The flexible multibody dynamics , second-order model reduction and attitude control of a small satellite are studied in this thesis . Firstly , the research situation of flexible multibody spacecraft dynamics is summarized .

本文以某小卫星为研究对象，重点研究了小卫星刚柔耦合多体系统动力学、二阶系统模型降阶和姿态控制等问题。首先综述了多柔体航天器动力学的研究现状。

Then , new requirement for analysis and design technology of spacecraft dynamics is presented because of development of Chinese complicated spacecraft in early days of 21st century , some key technology must be broken and solved emphatically ;

然后，阐述了21世纪初期中国复杂航天器的发展对航天器动力学分析设计技术提出的新要求，重点分析了在动力学分析、仿真、优化与试验方面必须突破和解决的若干关键技术；

A control law , that constrains the state to follow the sliding mode in the state space , is designed on the basis of a nonlinear , simplified model of the completely liquid-filled spacecraft dynamics .

基于充液飞行器的简化模型，在状态空间中设计控制规律以约束状态至滑模。

Firstly , the paper gives a sufficient condition of the system 's stability , and analyzes its stability . Afterwards , a nonlinear spacecraft dynamics is decomposed into some subsystems , for which a decentralized adaptive controller is proposed .

首先给出该系统稳定的充分条件，分析其稳定性，然后针对一种空间飞行器的非线性动力学模型，通过变换分解成若干个子系统，进而对每个子系统进行分散自适应控制。

The model of spacecraft attitude dynamics and the attitude control technology are generalized .

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。

Simulation Framework for Spacecraft Attitude Dynamics and Control Based on Matlab / Simulink

基于Matlab/Simulink的航天器姿态动力学与控制仿真框架

Numerical simulation of spacecraft docking dynamics in capture process

空间飞行器对接捕获阶段动力学的数值仿真研究

A mathematical model derived from spacecraft attitude dynamics is treated as an example to demonstrate its application .

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。

With PD and optimal control of classical control theory model of the spacecraft attitude dynamics modeling , and conducted a detailed MATLAB simulation .

并用PD及最优控制等经典控制理论对航天器姿态动力学模型进行了建模，并运用MATLAB进行了详细的仿真，得到了仿真结果。

Topics extend to analysis of both aircraft flight dynamics and spacecraft attitude dynamics , based upon presented principles and equations of motion .

课题扩展分析了航天器飞行动力学和太空船飞行姿态动力学，这些建立在当前的运动理论和方程式上。

In this paper , the irregular sphere gravitational potential is given based on adapting to a tri-axial ellipsoid model of a small body , and the spacecraft orbital dynamics equation around a small body is established .

针对可以用三轴椭球体近似建模的小天体，给出了非球形引力势函数，建立了航天器绕飞小天体的轨道动力学方程。

The asteroid Ivar is modeled as a tri-axial ellipsoid , its sphere gravitational potential is given , and spacecraft orbital dynamics equation around the asteroid Ivar is established .

将小行星Ivar近似为三轴椭球体，给出了非球形引力势函数，建立了航天器环绕小行星Ivar的轨道动力学方程。

Depending upon configuration , air-bearing systems provide some combination of translational and rotational freedom ; the three degrees of rotational freedom provided by a spherical air bearing are ideal for investigation of spacecraft attitude dynamics and control problems .

气浮台系统通过配置可具备若干平动或转动的自由度，采用球形气浮轴承则可以提供三轴的转动自由度，是研究空间飞行器姿态动力学与控制问题的理想平台。

Global simulation of spacecraft appendage deployment dynamics by variable topology

变拓扑航天器附件展开动力学的全局仿真

In order to verify the dynamics characteristic of a space remote sensing camera , spacecraft and camera dynamics coupling test is needed .

为了检验空间遥感相机的动力学特性，需要对相机与飞船进行动力学耦合试验。

The simulation results demonstrate the feasibility and effectiveness of the proposed method . A robust active control approach is presented for the attitude tracking control and vibration damping of a spacecraft with actor dynamics .

针对带有执行机构动态特性的挠性航天器姿态跟踪问题，基于后步滑模及主动振动控制技术提出一种鲁棒主动控制策略。

A new method is promoted for flexible spacecraft control by describing flexible spacecraft dynamics equations as T-S fuzzy model and designing a PDC fuzzy controller .

将挠性航天器姿态动力学方程描述为T-S模糊模型为挠性航天器控制提供了新思路；