Nonlinear hoc robust guidance law for homing missiles

Hsin Yuan Chen, Ciann-Dong Yang

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

This paper proposes an H∞ robust guidance law for homing missiles with nonlinear kinematics in the homing phase. Unlike the conventional approaches where the trajectory of the target is often assumed to be known or needs to be estimated in real time, the proposed robust guidance law can achieve performance robustness in the absence of target's information and under the variations of the initial conditions of engagement. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is the solution of the associated Hamilton-Jacobi Partial differential inequality (HJPDI). In this paper we show that the HJPDI of the missile guidance problem can be solved analytically with simple manipulations. The numerical simulations show that the H∞ robust guidance law exhibits strong robustness properties against the disturbances from target's maneuvers and the variations in initial engagement conditions.

Original languageEnglish
Title of host publicationGuidance, Navigation, and Control Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Pages554-562
Number of pages9
Publication statusPublished - 1998
EventGuidance, Navigation, and Control Conference and Exhibit, 1998 - Boston, United States
Duration: 1998 Aug 101998 Aug 12

Other

OtherGuidance, Navigation, and Control Conference and Exhibit, 1998
CountryUnited States
CityBoston
Period98-08-1098-08-12

Fingerprint

Electronic guidance systems
Missiles
Control theory
Kinematics
Trajectories
Computer simulation

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Chen, H. Y., & Yang, C-D. (1998). Nonlinear hoc robust guidance law for homing missiles. In Guidance, Navigation, and Control Conference and Exhibit (pp. 554-562). American Institute of Aeronautics and Astronautics Inc, AIAA.
Chen, Hsin Yuan ; Yang, Ciann-Dong. / Nonlinear hoc robust guidance law for homing missiles. Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998. pp. 554-562
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Chen, HY & Yang, C-D 1998, Nonlinear hoc robust guidance law for homing missiles. in Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, pp. 554-562, Guidance, Navigation, and Control Conference and Exhibit, 1998, Boston, United States, 98-08-10.

Nonlinear hoc robust guidance law for homing missiles. / Chen, Hsin Yuan; Yang, Ciann-Dong.

Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998. p. 554-562.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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AB - This paper proposes an H∞ robust guidance law for homing missiles with nonlinear kinematics in the homing phase. Unlike the conventional approaches where the trajectory of the target is often assumed to be known or needs to be estimated in real time, the proposed robust guidance law can achieve performance robustness in the absence of target's information and under the variations of the initial conditions of engagement. The most difficult and challenging task involved in applying the nonlinear H∞ control theory is the solution of the associated Hamilton-Jacobi Partial differential inequality (HJPDI). In this paper we show that the HJPDI of the missile guidance problem can be solved analytically with simple manipulations. The numerical simulations show that the H∞ robust guidance law exhibits strong robustness properties against the disturbances from target's maneuvers and the variations in initial engagement conditions.

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Chen HY, Yang C-D. Nonlinear hoc robust guidance law for homing missiles. In Guidance, Navigation, and Control Conference and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA. 1998. p. 554-562