臺灣博碩士論文加值系統

本論文之目的在於探討飛彈任務系統與飛行控制系統整合之方法,
並以六自由度剛體飛行運動模擬驗證之.
本文係以一雙進氣道飛彈為分析例題,
以資料庫法估算空氣動力係數,
並據以設計飛行控制系統,
以使飛彈穩定並能追蹤導引任務需求.
本研究之任務部分係應用奇攝動法求其最遠航程軌跡,
由於任務分析所得之最佳控制不適合作為控制六自由度剛體運動之輸入,
本論文改以追蹤任務系統所分析之最佳路徑,
以建立強健的任務及控制系統整合.

The objective of this thesis is to investigate the method of integrating the mission and control systems of a missile.
To validate the method, simulations with a 6-d.o.f. rigid body model are conducted.
In order to obtain a set of aerodynamic coefficient data, a typical configuration of twin-inlet missile is provided
and the data compendium method is used accordingly.
With the estimated aerodynamic data, a control system is designed to stabilize the missile and track the output of
the guidance system.
In this study, the mission is designed to be the maximum range of flight with mass of fuel fixed.
To obtain the optimal trajectory, the singular perturbation is used.
Since the control obtained from the optimal trajectory analysis is not an adequate input for the 6-d.o.f. rigid
body system, tracking the optimal trajectory output of the mission system is chosen to build up a robust integration
of the mission and control systems.

授權書
摘要
Abstract
誌謝
目錄
表目錄
圖目錄
符號表
一、緒論
1.1 研究動機 1
1.2 文獻回顧 2
1.3 系統描述 2
二、雙進氣道飛彈及其任務系統 4
2.1 雙進氣道飛彈資料 4
2.2 重量及慣性矩估算 5
2.3 任務系統設定 6
三、空氣動力分析 10
3.1 空氣動力分析軟體之應用 10
3.2 應用DATCOM估算氣動力係數 14
3.3 氣動力係數估算結果 15
四、飛彈之剛體運動方程式 29
4.1 座標系統定義 29
4.2 剛體運動分析 31
4.3 剛體運動方程式 33
4.4 空氣動力與力矩之分析 33
4.5 六自由度飛彈模擬系統 35
五、飛行控制系統設計 37
5.1 求取配平狀態 37
5.2 控制系統設計 38
六、系統整合與模擬 44
6.1 系統整合架構 44
6.2 六自由度飛行模擬結果 45
七、 結論 50
參考文獻
附錄
A、大氣密度,溫度及音速 52
B、應用奇攝動法求最遠航程軌跡 53
B.1 運動方程式 53
B.2 最遠航程之必要條件 54
B.3 應用奇攝動法求解 56
B.4 零階外解 58
B.5 邊界層第一層內解 59
B.6 邊界層第二層內解 60}
C、應用PANAIR作氣動力係數估算 63
C.1 依平面資料建構網格 63
C.2 PANAIR之輸入檔說明 66
C.3 估算結果 70}
自述

許棟龍, 大氣飛行最佳軌跡課程講義, http://www.iaa.ncku.edu.tw/~donglong/flightmch.htm

Sheu, D. L., Chen, Y. M., Chang, Y. J., and Chern, J. S.,
Optinal Glide for Maximum Range,
Presented in the AIAA Atmospheric Flight Mechanics Conference, Boston, Massachusetts, U.S.A.,
Paper No. AIAA 98-4462, August 10-12, 1998

Hayes, C.,Aerodynamic Characteristics of a Series of Twin-Inlet Air-Breathing Missile
Configurations II - Two-Dimensional Inlets at Supersonic Speeds,
NASA TM 84559, 1983.

Burns, K. A. and Blake, W.B.,
Missile DATCOM USER'S MANUAL - Rivision 6/93,
ADA-264 447, McDonnell Douglas Aerospace, St Loutis, MO, U.S.A., June 1993.

Saaris, G. R., Tinoco, E. N., Lee, J. L., Rubbert, P. E.,
A502I User's Manual - PAN AIR Technology Program for Solving Problems of
Potential Flow about Arbitrary Configurations, BOEING, 1992.