【作者】 李九人；

【导师】 李海阳；

【作者基本信息】 国防科学技术大学 ， 力学， 2007， 硕士

【摘要】 在轨运行的航天器出现故障时,如果能够从地面发射救援飞行器及时进行救援,则可能避免重大损失。本文对空间紧急救援任务的发射窗口、轨道控制方法等进行了较系统的分析,主要内容包括以下几个方面:1、分析了空间紧急救援的意义,对空间紧急救援中涉及的大机动、快速交会和自主交会等关键技术进行了论述;对空间紧急救援任务过程进行了阶段划分,并概括了各阶段的任务和特性;归纳和总结了空间交会的动力学模型。2、解析推导了空间紧急发射任务的发射窗口,研究了机动布署策略。将紧急发射任务发射窗口问题分解为平面窗口问题和相位窗口问题,分别建立了平面窗口和相位窗口的解析求解模型,导出了发射窗口的解析解。以发射窗口的解析解为基础,对机动发射车的布署做出了分析。3、对寻的段和近距离交会段的制导和控制策略进行了研究。在寻的段,给出了C-W制导的两种修正算法和Lambert制导的两种修正算法,采用这些算法分别进行了制导计算,并对其进行了比较分析。另外,在接近段采用二脉冲制导,在最后逼近段采用视线制导算法进行轨道控制,并对其进行了仿真分析。4、开发了空间紧急救援轨道仿真系统。利用面向对象建模语言UML对仿真系统进行了建模,采用C++面向对象程序语言,在VC++6.0集成开发环境下对软件进行了开发,实现了初步的紧急救援发射任务规划、轨道方案仿真和可视化演示功能。本文工作是对空间紧急救援任务的初步论证和可行性分析。研究表明空间紧急救援任务在技术上具有可行性,但与通常的空间交会任务不同,有很多新问题需要进一步研究。更多还原

【Abstract】 If the spacecrafts in orbit can be rescued in time, heavy loss may be avoided. In this thesis, the launch window, the orbit control strategy etc. are discussed in detail for the mission of space emergency rescue. The main content is presented as follows:Firstly, the significance of space emergency rescue is analyzed, and the key technologies, such as high maneuver, fast rendezvous and autonomous rendezvous are discussed. The mission of space rescue is divided into several phases, and the tasks and characteristics of each phase are analyzed. Then the dynamics models for autonomous rendezvous are summarized.Secondly, the launch window of urgent launch mission is deduced, and the strategy to array the maneuverable launch vehicle is researched. The problem on the launch window is divided into two parts, the plane window problem and the phase window problem. Analytical models of the two problems are established, and the results are deduced in explicit form. Using the analytical results, the strategy to array the maneuver launch vehicle is given.Thirdly, the strategy of guidance and control for the phases of far range rendezvous and close range rendezvous are researched. In the phase of far range rendezvous, the modified C-W algorithms and modified Lambert algorithms are given and put into calculation, and the results are analyzed and evaluated. In addition, two impulses control strategy is used in the phase of closing, whereas the Line-of-sight guidance algorithm is used in the phase of final approach, these strategies are simulated and analyzed.Lastly, software for mission design and orbital analysis is developed. The software is designed by the Unified Modeling Language (UML), and is coded in VC++ 6.0. It has the functions such as space emergency rescue mission planning, orbital simulation and visual demonstration.This thesis is to demonstrate and analyze the feasibility for space emergency rescue mission. The research indicates that the mission is feasible in technology, but is different from common rendezvous missions. There are still many problems to be studied for a practical space emergency rescue mission.更多还原