Education, Science, Technology, Innovation and Life
Open Access
Sign In

Research on an extended composite proportional navigation law based on error adaptation and error anti saturation

Download as PDF

DOI: 10.23977/jeis.2022.070401 | Downloads: 16 | Views: 601

Author(s)

Jing Yu 1, Junwei Lei 1, Hong Wang 1, Lingling Wang 1

Affiliation(s)

1 College of Coast Defence, Naval Aviation University, Yantai, 264001, China

Corresponding Author

Junwei Lei

ABSTRACT

According to the two-dimensional spatial relationship model of relative motion between missile and target, a constant value proportional navigation law based on error anti saturation is proposed on the basis of conventional proportional navigation and extended proportional navigation; Thirdly, the adaptive estimation design of guidance parameters is carried out from the angle error of longitudinal plane and lateral plane, angle coupling error, monocular distance, reciprocal of monocular distance and other aspects, and finally a composite three-dimensional proportional guidance method with error adaptation and error anti saturation is formed. The case digital simulation results also show the correctness and effectiveness of the proposed method.

KEYWORDS

Proportional guidance, Extended proportional navigation, Adaptive, Anti saturation, Miss distance

CITE THIS PAPER

Jing Yu, Junwei Lei, Hong Wang, Lingling Wang, Research on an extended composite proportional navigation law based on error adaptation and error anti saturation. Journal of Electronics and Information Science (2022) Vol. 7: 1-8. DOI: http://dx.doi.org/10.23977/jeis.2022.070401.

REFERENCES

[1] C.-F. Lin, Modern Navigation, Guidance, and Control Processing. Englewood Cliffs, NJ:Prentice –Hall, 1991:360-371.
[2] G.M. Anderson, Comparisons of optimal control and differential game intercept missile guidance laws [J]. J. Guid., Conf. Dyn . 1981, 14(2):1056-1058,.
[3] E. Kreindler , Optimality of proportional navigation , AIAA.[J] 1973, 11(6):878-880.
[4] P.Gurfil , M.jodorkovsky , and M.Guelman, Design of nonsaturating guidance systems, J.Guid ,Contr .Dyn., 2000, 23(4):693-700.
[5] H.K. Khalil, Nonlinear System ,3rd ed. Englewood Cliffs ,NJ:Prentice-Hall,2002.
[6] M.J. Tahk , C.K.Ryoo, and H.Cho, Recursive time-to-go estimation for homing guidance missiles. IEEE Trans Aerosp . Electron. Syst . 2002, 38(1):13-24.
[7] P. Zarchan Tactical and Strategic Missile Guidance, 2nd ed. Washington, DC: AIAA, 1994,45-66.
[8] R. Manchester, A.V. Savkin .Cireular Navigation Guidanee Lawfor Preeision Missile/target Engagements [C]// proceedings of the 41st IEEE Conferenceon. Deeision and Control, 2002.
[9] I. Rusnak, L. Meirt. Modern Guidance Law for High-order Autopilot[J].Journal of  Guidance ,Control ,and Dynamics ,1991.14(5):1056-1058.
[10] I.Rusbank. Almost Analytic Reprentation for the Solution of the Differential Matrix Riccati Equation[J]. IEEE Transactions on Automatic Control , 1988.33(2):191-193.
[11] Xu H J ,Mirmirani M. Adaptive sliding mode control design for a hypersonic flight vehicle. Journal of guidance, control and dynamics, 2004,27(5):829-838.
[12] Junchun Yang, Jun Hu, Xiaole Lv. Design of Sliding Mode Tracking Control for Hypersonic Reentry Vehicles [C].Proceedings of the 26th Chinese Control Conference, Zhangjiajie, Hunan, China, 2007:1-4.
[13] Buschek H, Calise A J. Uncertainty modeling and fixed-order controller design for a hypersonic vehicle model. Journal of Guidance, Control and Dynamics, 1997,20(1):42-48.

Downloads: 5999
Visits: 242872

Sponsors, Associates, and Links


All published work is licensed under a Creative Commons Attribution 4.0 International License.

Copyright © 2016 - 2031 Clausius Scientific Press Inc. All Rights Reserved.