Citation

Shim SW, Hong SM, Moon GH, Tahk MJ. Int. J. Aeronaut. Space Sci. 2018; 19(1): 217-226.

Copyright

(Copyright © 2018, Korean Society for Aeronautical and Space Sciences, Publisher Holtzbrinck Springer Nature Publishing Group)

DOI

10.1007/s42405-018-0004-8

PMID

unavailable

Abstract

This paper proposes a guidance law which considers the constraints of seeker field-of-view (FOV) as well as the requirements on impact angle and time. The proposed guidance law is designed for a constant speed missile against a stationary target. The guidance law consists of two terms of acceleration commands. The first one is to achieve zero-miss distance and the desired impact angle, while the second is to meet the desired impact time. To consider the limits of FOV and lateral maneuver capability, a varying-gain approach is applied on the second term. Reduction of realizable impact times due to these limits is then analyzed by finding the longest course among the feasible ones. The performance of the proposed guidance law is demonstrated by numerical simulation for various engagement conditions.

Language: en