自調式比例導引律

機構典藏 > College of Engineering > Graduate Institute & Department of Aerospace Engineering > Proceeding > Item 987654321/38467

Please use this identifier to cite or link to this item: https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/38467

Title:	自調式比例導引律
Other Titles:	A heuristic adaptive proportional navigation guidance law
Authors:	邱元宏;田豐;Chiou, Yuan-Horng;Tyan, Feng
Contributors:	淡江大學航空太空工程學系
Keywords:	比例導引律;數值模擬;最佳化Proportional Navigation;Numerical Simulation;Optimization
Date:	1998-12
Issue Date:	2010-01-11 15:19:21 (UTC+8)
Publisher:	逢甲大學
Abstract:	本文主旨的探討純比例導引律對飛彈性能的影響, 經數值模擬分析結果可知在一般狀態下, 令導航係數為常數表現並不是很好, 例如在尾追時取導航係數值較大表現較好, 但在側擊時如取相同導航係數值, 則可能會導致加速度需求過大; 因此在文獻中有人用最佳化的觀念, 導出取導航係數值疊代法來改善, 缺點為所需的資訊要求較多,計算負荷較大。故本文為克服上述問題, 提出一自調式比例導引律方法, 僅用視線角及視線角變化率為變數來調整導航係數值。雖然此方法沒有嚴謹的理論推導, 但經由數值模擬分析結果可知, 此導引律能使飛彈運用較適當之加速度命令與能量來完成擊靶。 The purpose of this paper is to develop and investigate the pure proportional navigation missile guidance law. Numerical examples show that letting proportional coefficient be a constant is not a good choice. Some literatures used optimal control method to obtain a proportional coefficient, but the information required is more than just line of sight angle and angle rate and the load of calculation is heavy [11,13]. To solve this question we suggest a heuristic adaptive proportional navigation guidance law. In spite of the method have not driven strictly. But the results of numerical analysis indicate that the method made missile use proper acceleration command and energy to intercept target.
Relation:	中國航空太空學會八十七年年會暨第四十屆學術研討會論文集(下冊)，頁575-579
Appears in Collections:	[Graduate Institute & Department of Aerospace Engineering] Proceeding

Files in This Item:

File	Description	Size	Format
index.html		0Kb	HTML	152	View/Open
自調式比例導引律_中文摘要.docx	摘要	13Kb	Microsoft Word	202	View/Open
自調式比例導引律_英文摘要.docx	摘要	13Kb	Microsoft Word	93	View/Open

Loading...