Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint

Duo Zheng; Xinghua Xu; Ruyi Yan; Defu Lin

doi:10.1007/978-981-13-3305-7_187

Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint

Duo Zheng^*, Xinghua Xu, Ruyi Yan, Defu Lin

^*Corresponding author for this work

School of Aerospace Engineering

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

Abstract

In this paper, a new optimal linear-quadratic guidance law with terminal acceleration constraints is proposed for intercepting maneuvering target. Because the angle of attack is approximately proportional to the normal acceleration for aerodynamic control missile, not only miss distance, but also terminal acceleration is required to converge to zero for increasing effectiveness of the warhead for destroying armored target in the proposed guidance law. The gain characteristic of proposed guidance law is studied by comparing with traditional optimal guidance law with considering autopilot dynamics lags. Numerical simulations are performed to examine performance of the proposed optimal guidance law, and its robustness with respect to the time constant of autopilot dynamic lags is also studied by considering time constant typical errors.

Original language	English
Title of host publication	The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Editors	Xinguo Zhang
Publisher	Springer Verlag
Pages	2310-2330
Number of pages	21
ISBN (Print)	9789811333040
DOIs	https://doi.org/10.1007/978-981-13-3305-7_187
Publication status	Published - 2019
Event	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 - Chengdu, China Duration: 16 Oct 2018 → 18 Oct 2018

Publication series

Name	Lecture Notes in Electrical Engineering
Volume	459
ISSN (Print)	1876-1100
ISSN (Electronic)	1876-1119

Conference

Conference	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Country/Territory	China
City	Chengdu
Period	16/10/18 → 18/10/18

Keywords

Autopilot dynamics lags
Optimal guidance law
Robustness with time constant
Terminal acceleration constraint
Terminal zero angle of attack

Access to Document

10.1007/978-981-13-3305-7_187

Cite this

Zheng, D., Xu, X., Yan, R., & Lin, D. (2019). Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint. In X. Zhang (Ed.), The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 (pp. 2310-2330). (Lecture Notes in Electrical Engineering; Vol. 459). Springer Verlag. https://doi.org/10.1007/978-981-13-3305-7_187

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title = "Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint",

abstract = "In this paper, a new optimal linear-quadratic guidance law with terminal acceleration constraints is proposed for intercepting maneuvering target. Because the angle of attack is approximately proportional to the normal acceleration for aerodynamic control missile, not only miss distance, but also terminal acceleration is required to converge to zero for increasing effectiveness of the warhead for destroying armored target in the proposed guidance law. The gain characteristic of proposed guidance law is studied by comparing with traditional optimal guidance law with considering autopilot dynamics lags. Numerical simulations are performed to examine performance of the proposed optimal guidance law, and its robustness with respect to the time constant of autopilot dynamic lags is also studied by considering time constant typical errors.",

keywords = "Autopilot dynamics lags, Optimal guidance law, Robustness with time constant, Terminal acceleration constraint, Terminal zero angle of attack",

author = "Duo Zheng and Xinghua Xu and Ruyi Yan and Defu Lin",

note = "Publisher Copyright: {\textcopyright} Springer Nature Singapore Pte Ltd. 2019.; Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 ; Conference date: 16-10-2018 Through 18-10-2018",

year = "2019",

doi = "10.1007/978-981-13-3305-7_187",

language = "English",

isbn = "9789811333040",

series = "Lecture Notes in Electrical Engineering",

publisher = "Springer Verlag",

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address = "Germany",

}

Zheng, D, Xu, X, Yan, R & Lin, D 2019, Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint. in X Zhang (ed.), The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. Lecture Notes in Electrical Engineering, vol. 459, Springer Verlag, pp. 2310-2330, Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018, Chengdu, China, 16/10/18. https://doi.org/10.1007/978-981-13-3305-7_187

Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint. / Zheng, Duo; Xu, Xinghua; Yan, Ruyi et al.
The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. ed. / Xinguo Zhang. Springer Verlag, 2019. p. 2310-2330 (Lecture Notes in Electrical Engineering; Vol. 459).

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

TY - GEN

T1 - Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint

AU - Zheng, Duo

AU - Xu, Xinghua

AU - Yan, Ruyi

AU - Lin, Defu

N1 - Publisher Copyright: © Springer Nature Singapore Pte Ltd. 2019.

PY - 2019

Y1 - 2019

N2 - In this paper, a new optimal linear-quadratic guidance law with terminal acceleration constraints is proposed for intercepting maneuvering target. Because the angle of attack is approximately proportional to the normal acceleration for aerodynamic control missile, not only miss distance, but also terminal acceleration is required to converge to zero for increasing effectiveness of the warhead for destroying armored target in the proposed guidance law. The gain characteristic of proposed guidance law is studied by comparing with traditional optimal guidance law with considering autopilot dynamics lags. Numerical simulations are performed to examine performance of the proposed optimal guidance law, and its robustness with respect to the time constant of autopilot dynamic lags is also studied by considering time constant typical errors.

AB - In this paper, a new optimal linear-quadratic guidance law with terminal acceleration constraints is proposed for intercepting maneuvering target. Because the angle of attack is approximately proportional to the normal acceleration for aerodynamic control missile, not only miss distance, but also terminal acceleration is required to converge to zero for increasing effectiveness of the warhead for destroying armored target in the proposed guidance law. The gain characteristic of proposed guidance law is studied by comparing with traditional optimal guidance law with considering autopilot dynamics lags. Numerical simulations are performed to examine performance of the proposed optimal guidance law, and its robustness with respect to the time constant of autopilot dynamic lags is also studied by considering time constant typical errors.

KW - Autopilot dynamics lags

KW - Optimal guidance law

KW - Robustness with time constant

KW - Terminal acceleration constraint

KW - Terminal zero angle of attack

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SN - 9789811333040

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BT - The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018

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Zheng D, Xu X, Yan R, Lin D. Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint. In Zhang X, editor, The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. Springer Verlag. 2019. p. 2310-2330. (Lecture Notes in Electrical Engineering). doi: 10.1007/978-981-13-3305-7_187

Optimal linear-quadratic guidance law considering autopilot first-order lag with terminal acceleration constraint

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