Modeling and simulation of kinetic optimal midcourse guidance law for air-to-air missiles

Chao Chang; De Fu Lin

doi:10.1109/ICIC.2009.194

Modeling and simulation of kinetic optimal midcourse guidance law for air-to-air missiles

Chao Chang^*, De Fu Lin

^*Corresponding author for this work

School of Aerospace Engineering

Beijing Institute of Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

3 Citations (Scopus)

Abstract

A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta-Grade numerical method is proposed to solve the optimal trajectory. An air-to-air missile example is used to compare the kinetic optimal midcourse guidance law with both the kinematic optimal guidance law and singular perturbation sub-optimal guidance law. Wherein, the latter two guidance laws are modified by adding vertical g-bias command for the sake of trajectory shaping. The simulation results show that the new kinetic optimal midcourse guidance law can conserve more energy and maximize terminal velocity effectively.

Original language	English
Title of host publication	2009 2nd International Conference on Information and Computing Science, ICIC 2009
Pages	329-332
Number of pages	4
DOIs	https://doi.org/10.1109/ICIC.2009.194
Publication status	Published - 2009
Event	2009 2nd International Conference on Information and Computing Science, ICIC 2009 - Manchester, United Kingdom Duration: 21 May 2009 → 22 May 2009

Publication series

Name	2009 2nd International Conference on Information and Computing Science, ICIC 2009
Volume	2

Conference

Conference	2009 2nd International Conference on Information and Computing Science, ICIC 2009
Country/Territory	United Kingdom
City	Manchester
Period	21/05/09 → 22/05/09

Keywords

Optimal guidance law
Simplified runge-kutta-grade method
Terminal velocity component

Access to Document

10.1109/ICIC.2009.194

Cite this

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title = "Modeling and simulation of kinetic optimal midcourse guidance law for air-to-air missiles",

abstract = "A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta-Grade numerical method is proposed to solve the optimal trajectory. An air-to-air missile example is used to compare the kinetic optimal midcourse guidance law with both the kinematic optimal guidance law and singular perturbation sub-optimal guidance law. Wherein, the latter two guidance laws are modified by adding vertical g-bias command for the sake of trajectory shaping. The simulation results show that the new kinetic optimal midcourse guidance law can conserve more energy and maximize terminal velocity effectively.",

keywords = "Optimal guidance law, Simplified runge-kutta-grade method, Terminal velocity component",

author = "Chao Chang and Lin, {De Fu}",

year = "2009",

doi = "10.1109/ICIC.2009.194",

language = "English",

isbn = "9780769536347",

series = "2009 2nd International Conference on Information and Computing Science, ICIC 2009",

pages = "329--332",

booktitle = "2009 2nd International Conference on Information and Computing Science, ICIC 2009",

note = "2009 2nd International Conference on Information and Computing Science, ICIC 2009 ; Conference date: 21-05-2009 Through 22-05-2009",

}

Chang, C & Lin, DF 2009, Modeling and simulation of kinetic optimal midcourse guidance law for air-to-air missiles. in 2009 2nd International Conference on Information and Computing Science, ICIC 2009., 5169078, 2009 2nd International Conference on Information and Computing Science, ICIC 2009, vol. 2, pp. 329-332, 2009 2nd International Conference on Information and Computing Science, ICIC 2009, Manchester, United Kingdom, 21/05/09. https://doi.org/10.1109/ICIC.2009.194

Modeling and simulation of kinetic optimal midcourse guidance law for air-to-air missiles. / Chang, Chao; Lin, De Fu.
2009 2nd International Conference on Information and Computing Science, ICIC 2009. 2009. p. 329-332 5169078 (2009 2nd International Conference on Information and Computing Science, ICIC 2009; Vol. 2).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

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AU - Lin, De Fu

PY - 2009

Y1 - 2009

N2 - A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta-Grade numerical method is proposed to solve the optimal trajectory. An air-to-air missile example is used to compare the kinetic optimal midcourse guidance law with both the kinematic optimal guidance law and singular perturbation sub-optimal guidance law. Wherein, the latter two guidance laws are modified by adding vertical g-bias command for the sake of trajectory shaping. The simulation results show that the new kinetic optimal midcourse guidance law can conserve more energy and maximize terminal velocity effectively.

AB - A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta-Grade numerical method is proposed to solve the optimal trajectory. An air-to-air missile example is used to compare the kinetic optimal midcourse guidance law with both the kinematic optimal guidance law and singular perturbation sub-optimal guidance law. Wherein, the latter two guidance laws are modified by adding vertical g-bias command for the sake of trajectory shaping. The simulation results show that the new kinetic optimal midcourse guidance law can conserve more energy and maximize terminal velocity effectively.

KW - Optimal guidance law

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KW - Terminal velocity component

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Modeling and simulation of kinetic optimal midcourse guidance law for air-to-air missiles

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Keywords

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