Composite Zero-Effort-Miss Guidance with Predictor–Corrector Steps for Ballistic Interception

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<jats:p> In this paper, a midcourse guidance law for exoatmospheric interception using a solid-propellant rocket is presented. Existing guidance laws based on the zero-effort-miss concept lack consideration for remaining thrust, potentially resulting in the excessive magnitude and rate of the thrust direction command. To address this issue, the zero-effort-miss concept is combined with an iterative predictor–corrector-based guidance law that is adapted for solid-propellant rockets. To apply the iterative predictor–corrector-based guidance law to the interception problem with a solid-propellant rocket, a composite zero-effort-miss concept is introduced, and the correction step is formulated as an online convex optimization problem. The composite zero-effort-miss consists of two zero-effort-misses. One miss is obtained from current state and the other miss is obtained from predicted state at burnout. Those render the proposed guidance law robust to thrust uncertainty allow for a noniterative approach and eliminate the singularity problem. Also, the proposed guidance law reduces maneuvering during the early part of the midcourse phase, leading to less velocity loss, and resolves intercept performance degradation due to the rate limit of thrust vectoring. Numerical simulations comparing the proposed method with the modified zero-effort-miss guidance demonstrate its effectiveness and robustness. </jats:p>
Publisher
AMER INST AERONAUTICS ASTRONAUTICS
Issue Date
2024-02
Language
English
Article Type
Article; Early Access
Citation

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, v.47, no.2, pp.311 - 325

ISSN
0731-5090
DOI
10.2514/1.g007760
URI
http://hdl.handle.net/10203/319728
Appears in Collection
AE-Journal Papers(저널논문)
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