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New Guidance method for high altitude target Based on Constrained Incremental Predictive Control

Document Type : Original Article

Authors

1 Faculty of Aerospace Engineering , Malek Ashtar University of Technology, Tehran, Iran

2 Faculty of Electrical & Computer engineering, Malek Ashtar University of technology, Iran

3 Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

10.22034/jast.2023.383679.1143

Abstract

In this paper a new mid-course guidance algorithm for intercepting high altitude target is proposed. A part of target flight path is outside the atmosphere. The maximum acceleration command is designed as a variable constraint that varies with altitude. This physical limitation is happened for the aerodynamically control interceptors at high altitudes because of decreasing air density. Based on generalized incremental predictive control approach, a new formulation for parallel navigation guidance law is proposed. Using the nonlinear kinematic equations of target-interceptor, the commands of the new guidance method are computed by optimization of a cost function involved the velocity perpendicular to the line of sight errors and guidance commands. An important feature of the proposed method is the minimization of the line- of - sight angular rate in a finite period of time. The various simulation results of the proposed guidance law shows the higher effectiveness of the designed guidance law in comparison with proportional navigation and sliding mode guidance.

Keywords

Main Subjects

Article Title [Persian]

New Guidance method for high altitude target Based on Constrained Incremental Predictive Control

Authors [Persian]

  • Mohammad Yavari 1
  • Nemat Allah Ghahremani 2
  • Reza Zardashtti 3
  • Jalal Karimi 3

1 Faculty of Aerospace Engineering , Malek Ashtar University of Technology, Tehran, Iran

2 Faculty of Electrical & Computer engineering, Malek Ashtar University of technology, Iran

3 Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

Abstract [Persian]

In this paper a new mid-course guidance algorithm for intercepting high altitude target is proposed. A part of target flight path is outside the atmosphere. The maximum acceleration command is designed as a variable constraint that varies with altitude. This physical limitation is happened for the aerodynamically control interceptors at high altitudes because of decreasing air density. Based on generalized incremental predictive control approach, a new formulation for parallel navigation guidance law is proposed. Using the nonlinear kinematic equations of target-interceptor, the commands of the new guidance method are computed by optimization of a cost function involved the velocity perpendicular to the line of sight errors and guidance commands. An important feature of the proposed method is the minimization of the line- of - sight angular rate in a finite period of time. The various simulation results of the proposed guidance law shows the higher effectiveness of the designed guidance law in comparison with proportional navigation and sliding mode guidance.

Keywords [Persian]

  • guidance
  • parallel navigation
  • constrained incremental predictive control
  • high speed and high altitude target
References
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Journal of Aerospace Science and Technology

Articles in Press, Accepted Manuscript
Available Online from 06 June 2023
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