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AIAA(Aerospace Reasearch) Journal of Guidance, 

JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS

Vol. 43, No. 6, June 2020

https://arc.aiaa.org/doi/full/10.2514/1.G004813

■ Researchers

Namhoon Cho∗

Agency for Defense Development, Daejeon 34186, Republic of Korea

Youdan Kim†

Seoul National University, Seoul 08826, Republic of Korea

Hyo-Sang Shin‡

Cranfield University, Cranfield, England MK43 0AL, United Kingdom

■ Abstract

This study presents a novel extension to the theory of optimal guidance laws represented by the nontraditional class of performance indices: nonquadratic-type signal Lp norm for the input weighted by an arbitrary positive function. Various missile guidance problems are generally formulated into a scalar terminal control problem based on the understanding of the predictor–corrector nature. Then, a new approach to derive the optimal feedback law, minimizing the nonquadratic performance index, is proposed by using the Hölderian inequality. The proposed extension allows a more general family of formulations for the design of closed-form feedback solutions to various guidance problems to be treated in a unified framework. The equivalence between the proposed approach and other design methodologies is investigated. In general, the type of input norm mainly determines the variability of input during the engagement while trading off against the rate of error convergence. The analytic solution derived in this study is verified by comparison with the solution from numerical optimization, and the effect of the exponent p in the performance index on the trajectory and command is demonstrated by numerical simulations.