自由時間収束誤差ダイナミクスに基づくミサイル誘導則設計
Missile guidance law design based on free-time convergent error dynamics
誤差ダイナミクスと自由時間収束法を用いて、初期状態や誘導パラメータに依存せず収束時間を自由に設定できる統一的なミサイル誘導則を提案し、先行角・衝突角・衝突時間制約を考慮した誘導則を導出した。
著者: Yuanhe Liu, Nianhao Xie, Kebo Li, Yangang Liang
分類: eess.SY, cs.RO, cs.SY, math.DS
原文アブストラクト
The design of guidance law can be considered a kind of finite-time error-tracking problem. A unified free-time convergent guidance law design approach based on the error dynamics and the free-time convergence method is proposed in this paper. Firstly, the desired free-time convergent error dynamics approach is proposed, and its convergent time can be set freely, which is independent of the initial states and the guidance parameters. Then, the illustrative guidance laws considering the leading angle constraint, impact angle constraint, and impact time constraint are derived based on the proposed free-time convergent error dynamics respectively. The connection and distinction between the proposed and the existing guidance laws are analyzed theoretically. Finally, the performance of the proposed guidance laws is verified by simulation comparison.