An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Sy-Hieu Nguyen; Dinh-Dung Nguyen

doi:doi:10.11648/j.ajae.20200702.11

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An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance

Sy-Hieu Nguyen, Dinh-Dung Nguyen

Published in American Journal of Aerospace Engineering (Volume 7, Issue 2)

Received: 22 March 2020 Accepted: 8 April 2020 Published: 31 December 2020

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Abstract

The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile’s acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.

Published in	American Journal of Aerospace Engineering (Volume 7, Issue 2)
DOI	10.11648/j.ajae.20200702.11
Page(s)	6-15
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2024. Published by Science Publishing Group

Keywords

Optimal Control, Optimal Guidance Law, Midcourse Phase, Wind Disturbance

References

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APA Style

Sy-Hieu Nguyen, Dinh-Dung Nguyen. (2020). An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance. American Journal of Aerospace Engineering, 7(2), 6-15. https://doi.org/10.11648/j.ajae.20200702.11

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ACS Style

Sy-Hieu Nguyen; Dinh-Dung Nguyen. An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance. Am. J. Aerosp. Eng. 2020, 7(2), 6-15. doi: 10.11648/j.ajae.20200702.11

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AMA Style

Sy-Hieu Nguyen, Dinh-Dung Nguyen. An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance. Am J Aerosp Eng. 2020;7(2):6-15. doi: 10.11648/j.ajae.20200702.11

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@article{10.11648/j.ajae.20200702.11,
  author = {Sy-Hieu Nguyen and Dinh-Dung Nguyen},
  title = {An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance},
  journal = {American Journal of Aerospace Engineering},
  volume = {7},
  number = {2},
  pages = {6-15},
  doi = {10.11648/j.ajae.20200702.11},
  url = {https://doi.org/10.11648/j.ajae.20200702.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20200702.11},
  abstract = {The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile’s acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.},
 year = {2020}
}

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TY  - JOUR
T1  - An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance
AU  - Sy-Hieu Nguyen
AU  - Dinh-Dung Nguyen
Y1  - 2020/12/31
PY  - 2020
N1  - https://doi.org/10.11648/j.ajae.20200702.11
DO  - 10.11648/j.ajae.20200702.11
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 6
EP  - 15
PB  - Science Publishing Group
SN  - 2376-4821
UR  - https://doi.org/10.11648/j.ajae.20200702.11
AB  - The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile’s acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.
VL  - 7
IS  - 2
ER  -

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Author Information

Sy-Hieu Nguyen

Department of Missile, Faculty of Control Engineering, Le Quy Don Technical University, Hanoi, Vietnam
Dinh-Dung Nguyen

Department of Aircraft System Design, Faculty of Aerospace Engineering, Le Quy Don Technical University, Hanoi, Vietnam

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Plain Text BibTeX RIS

APA Style

Sy-Hieu Nguyen, Dinh-Dung Nguyen. (2020). An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance. American Journal of Aerospace Engineering, 7(2), 6-15. https://doi.org/10.11648/j.ajae.20200702.11

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ACS Style

Sy-Hieu Nguyen; Dinh-Dung Nguyen. An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance. Am. J. Aerosp. Eng. 2020, 7(2), 6-15. doi: 10.11648/j.ajae.20200702.11

Copy | Download

AMA Style

Sy-Hieu Nguyen, Dinh-Dung Nguyen. An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance. Am J Aerosp Eng. 2020;7(2):6-15. doi: 10.11648/j.ajae.20200702.11

Copy | Download

@article{10.11648/j.ajae.20200702.11,
  author = {Sy-Hieu Nguyen and Dinh-Dung Nguyen},
  title = {An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance},
  journal = {American Journal of Aerospace Engineering},
  volume = {7},
  number = {2},
  pages = {6-15},
  doi = {10.11648/j.ajae.20200702.11},
  url = {https://doi.org/10.11648/j.ajae.20200702.11},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20200702.11},
  abstract = {The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile’s acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.},
 year = {2020}
}

Copy | Download

TY  - JOUR
T1  - An Optimal Algorithm for Midcourse Guidance Law Under Wind Disturbance
AU  - Sy-Hieu Nguyen
AU  - Dinh-Dung Nguyen
Y1  - 2020/12/31
PY  - 2020
N1  - https://doi.org/10.11648/j.ajae.20200702.11
DO  - 10.11648/j.ajae.20200702.11
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 6
EP  - 15
PB  - Science Publishing Group
SN  - 2376-4821
UR  - https://doi.org/10.11648/j.ajae.20200702.11
AB  - The guidance laws are commonly designed to yield as small a miss distance as possible, harmonious with the missile’s acceleration capability. In recent decades, the concept of optimized guidance law is well understood in applications where information concerning the target range and line-of-sight angle is available. Researchers' efforts have been continually made to apply modern control theory to conventional and adaptive autopilot designs, even though the classical theory is still applicable to autopilots. It can be noted that it is desirable to perform a detailed computer-aided feasibility study within the context of a realistic missile-target engagement model. Development and evaluation of guidance and control laws for simplified missile-target engagement scenarios are extended and adapted to the air-to-air missile situation and implemented in a complete three-dimensional engagement model. Thus, this study proposed a computational method for constructing an optimal midcourse guidance law, which is based on the optimal control theory and initial boundary conditions. This proposed guidance law is derived from an optimal control theory with the boundary conditions such as allowed relative distance between missile and target at the final time, low line-of-sight rate. A numerical simulation verifies the performance of this guidance law with the impact of harmonic wind. The simulation results demonstrate that the quality of effectiveness as well as the applicability of this proposed algorithm.
VL  - 7
IS  - 2
ER  -

Copy | Download