航天器轨道动力学

根据航天器轨道动力学方程，建立航天器自主导航系统状态方程。

Based on the precise orbit dynamics model , the state function of spacecraft autonomous navigation systerm is established .

针对天文导航系统所采用的状态方程和量测方程对系统的性能和定位精度的影响，介绍了天文导航中常用的两种状态方程，航天器轨道动力学方程和牛顿受摄运动方程。

Different celestial navigation systems , which uses different kinds of motion equations and measurement equations have different navigation performance and precision .

由此，论文主要研究内容如下：首先，建立了天体及航天器轨道动力学模型。

Thus , the main contents of this thesis are organized as follows : First of all , the orbit dynamic model about celestial bodies and the spacecraft is established .

太阳帆航天器的轨道动力学和轨道控制研究

Study on Orbit Dynamics and Control of Solar-Sail Spacecraft

航天器近距编队轨道动力学模型及仿真

Orbital Dynamic Model and Simulation of Spacecrafts Proximity Formation Flying

包括航天器的运动描述、对偶四元数描述方式和传统描述方式的相互转换关系，及前者较后者的不同与优势。第二，研究了对偶四元数应用于航天器姿态轨道一体化动力学建模方法。

Including the description of spacecraft motion , the advantages of dual quaternion compared to the traditional tool and the transformaton between them in description method . Secondly , the integrated dynamics modeling methods for spacecraft attitude and orbit motion was studied .