基于最优误差动力学的时间角度控制制导律

Translated title of the contribution: Time and angle control guidance law based on optimal error dynamics

Bin Li*, Defu Lin, Shaoming He, Bing Bai

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

10 Citations (Scopus)

Abstract

To solve the missile guidance with constraints of impact time and terminal impact angle, a time and angle control guidance law based on optimal error dynamics is designed, and a definite performance index is given. The expression of time to go estimation under generalized optimal angle control guidance law is derived. To reach zero tracking error in the finite time with the optimal convergence pattern, the designed guidance law adds the feedback of impact time error to the generalized guidance law of optimal angle control and considers the impact time error as the tracking error, achieving the joint control of the impact time and the terminal impact angle. The effectiveness of the proposed guidance law is validated through numerical simulations under different conditions.

Translated title of the contributionTime and angle control guidance law based on optimal error dynamics
Original languageChinese (Traditional)
Article number322215
JournalHangkong Xuebao/Acta Aeronautica et Astronautica Sinica
Volume39
Issue number11
DOIs
Publication statusPublished - 25 Nov 2018

Fingerprint

Dive into the research topics of 'Time and angle control guidance law based on optimal error dynamics'. Together they form a unique fingerprint.

Cite this