Suboptimal mid-course guidance algorithm for accelerating missiles

This paper deals with the closed-loop form of mid-course guidance law design for accelerating missile system, whose acceleration is approximately constant. A midcourse guidance algorithm of feedback form is proposed to satisfy the engagement geometry conditions at the burn-out time for terminal homing performance enhancement. The effect of velocity change due to missile acceleration is explicitly considered in the derivation of the guidance law. The terminal constraint update algorithm is proposed under the assumption that the target trajectory is predicted precisely. Simulation results are provided to show the performance and characteristics of the proposed algorithm.
Publisher
SAGE PUBLICATIONS LTD
Issue Date
2017-09
Language
English
Keywords

INTERVAL PROPULSIVE MANEUVERS; MIDCOURSE GUIDANCE; VELOCITY; DESIGN; LAW

Citation

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, v.231, no.11, pp.2032 - 2047

ISSN
0954-4100
DOI
10.1177/0954410016664928
URI
http://hdl.handle.net/10203/225658
Appears in Collection
AE-Journal Papers(저널논문)
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