國立交通大學
應用數學系數學建模與科學計算碩士班
碩士論文
在二維平面上的發射載具導引與控制
Launch Vehicle Guidance and Control on 2D Platform
研究生：劉玠旼
指導教授：林清安教授、莊重教授
在二維平面上的發射載具導引與控制
Launch Vehicle Guidance and Control on 2D Platform
研究生 ：劉玠旼 Student : Chieh-Min Liu
指導教授：林清安 教授 Advisor : Prof. Ching-An Lin
莊 重 教授 Prof. Jong Juang
國立交通大學
應用數學系
數學建模與科學計算碩士班
碩 士 論 文
A Thesis
Submitted to Department of Applied Mathematics College of Science
Institute of Mathematical Modeling and Scientific Computing
National Chiao Tung University
in Partial Fulfillment of the Requirements
for the Degree of
Master
in
Applied Mathematics
July 2012
Hsinchu, Taiwan
中 華 民 國 一百零一 年 七 月
在二維平面上的發射載具導引與控制
學生：劉玠旼 指導教授：林清安教授、莊重教授
國立交通大學 應用數學系數學建模與科學計算碩士班
中文摘要 1957 年以彈道飛彈火箭成功發射第一個衛星之後，迄今欲將衛星發射進入 軌道，火箭仍是目前最常被使用的載具。利用持續的推力將火箭自身及酬載一同 推入高空，並以多節的型式持續加速以節省燃料，以達進入規劃既定的軌道。一 般而言，火箭分成三至四節，從地表開始以垂直或接近垂直的角度發射後，先利 用重力轉彎，到了開始燃燒第二節火箭時才開始進行轉向，最後在第三至第四節 火箭燃燒時，控制載具在軌道上加速，使其在預期的目標軌道上以正確的飛行方 向和速度入軌。本論文是探討在二維平面上發射載具導引與控制的設計，從設計 載具的物理參數和時間參數開始，其後控制火箭轉向，最後在入軌加速階段，先 以「高度回授控制」使得軌道高度符合要求，再以「迫使平飛控制」使得飛行路 徑角更符合要求，進入運行軌道，成功達成預期目標。 ILaunch Vehicle Guidance and Control on 2D Platform
Student: Chieh-Min Liu Advisor: Prof. Ching-An Lin and Prof. Jong Juang Institute of Mathematical Modeling and Scientific Computing
National Chiao Tung University
Abstract
Since the first satellite launched successfully in 1957, rocket is by far the most frequently used vehicle to launch a payload into orbit for its continuous thrust to lift itself and the payload into the high altitude and its multi-stage mode of sustained acceleration to economize the use of propellant. Generally speaking, a rocket contains 3 to 4 stages. In the first stage, after launching vertically or near-vertically from the earth surface, gravity turn was used. Afterwards, the rocket can be steered into proper directions in proper time and positions after activating the second stage. Finally, the payload can be controlled to accelerate and enter the designated orbit with accurate direction and speed-of-flight in the last stages. The objective of this thesis is to investigate the design of launch vehicle guidance and control on 2D platform. It begins with designing the physical parameter and temporal parameter of rocket and then the control of steering and altitude. In the final acceleration stage of entering orbit, “altitude feedback control” is applied to meet the requirement of orbit altitude, and then “forced level flight control” is applied to meet the requirement of zero flight-path angle. Eventually, the payload propelled by the vehicle reaches the target orbit successfully.
