Aiming Point Guidance Algorithm Based on Proportional Navigation Guidance Scheme
學年 109
學期 2
出版（發表）日期 2021-03-30
作品名稱 Aiming Point Guidance Algorithm Based on Proportional Navigation Guidance Scheme
作品名稱（其他語言）
著者 Yi-Wei Chen, Kuei-Yi Chen, Yu-Lin Fang
單位
出版者
著錄名稱、卷期、頁數 23(1), 72-81
摘要 The proposed missile guidance algorithm is developed based on proportional navigation guidance scheme and the computation of aiming point. This research calculates the line-of-sight rate and the position of aiming point according to the current dynamics of missile and target, and applies particle swarm optimization to optimize and update the navigation constants of proportional navigation guidance continuously to figure out the missile control commands of lateral acceleration. Therefore, the missile will be guided to the aiming point as the computed target collision position. Simulation experiments prove the proposed guidance algorithm has the satisfied interception performance in a three dimensional engagement space with noise disturbance. The proposed method uses the shorter miss distance and less interception time compared with the proportional navigation guidance law and this could reduce the energy consumption as well. The outstanding guidance ability would be more obvious for intercepting the high agility aircraft. Furthermore, a novel artificial intelligence missile guidance algorithm is reproduced to execute the simulation experiments to compare the guidance technique with the proposed method. The proposed guidance algorithm is feasible to be applied to the real missile guidance system due to the advantages of simplicity and robustness.
關鍵字 Missile; Guidance; Particle swarm optimization; Proportional navigation guidance.
語言 en
ISSN 1454-8658
期刊性質 國外
收錄於 SSCI
產學合作
通訊作者 Yi-Wei Chen
審稿制度 是
國別 ROU
公開徵稿
出版型式 ,電子版