导　　师： 顾逸东

学科专业： 081203

授予学位： 硕士

作　　者： ;

机构地区： 中国科学院研究生院

摘　　要： 本论文构造了一个轨道仿真软件，介绍了轨道仿真软件的设计思想和实现过程。 轨道仿真程序核心部分是轨道计算，本文首先介绍了轨道动力学基础，包括轨道摄动问题，以及飞行器姿态控制等基础知识。 轨道计算主要用来模拟飞行器的飞行过程，前提是建立动力学模型。由于空间问题的复杂性，造成了动力学模型的多样性。具有通用性的轨道仿真程序，应该包含各种不同的动力学模型，能够简化航天任务的分析、设计工作量，提高工作效率和可靠性。因此，仿真程序应该具有良好的可扩展性、可复用性。 本文介绍如何使用UML和设计模式实现仿真程序的复用。使用这些设计方法，可以做到仿真程序模块化，同时降低各模块之间的耦合度，增加了仿真软件的通用性和可复用性。 利用仿真程序，实现了仿真一个正在预研的天文卫星——硬X射线调制望远镜HXMT观测X射线源的过程，分析了天球覆盖、HXMT接收的光子流强度的变化和太阳轨道面夹角的变化，说明了选取高度为550KM，倾角43o的近地圆轨道作为HXMT的运行轨道是合理的选择。 Li Qiang /(computer engineering and applications/) Directed by Gu Yidong This thesis introduces the design and implementation of an orbit simulation program. The orbit simulation program mainly concentrates on orbit calculation. This thesis first introduces the fundamental knowledge of orbit dynamics, including orbit perturbation and spacecraft attitude control. The main function of orbit calculation is to simulate the flight procedure of spacecraft, before that, the dynamics model of orbit must be established. The complexity of space environment brings the diversity of dynamics model. And a general-purpose orbit simulation program which should include varieties of dynamics model will simplify the process of analyzing and designing of spacecraft mission. This thesis then introduces how to use UML and Design Pattern to design a general and reusable orbit simulation program. Implementing these technologies, the simulation program will be modularized, with the coupling between modules reduced. The simulation program has been implemented to simulate the procedure of HXMT detecting X-ray source. The simulation result has been used to analyze the overlay region in celestial sphere, the variation of photon current intensity and the variation of the angle between sun and orbit, which demonstrate the reason why to select a 550 km height and 43o inclination low earth orbit as HXMT's orbit.

关 键 词： 飞行器 轨道计算 软件复用 设计模式

分 类 号： [TP391.9]

领　　域： [自动化与计算机技术] [自动化与计算机技术]