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Journal of Aerospace Science and Technology، جلد ۱۶، شماره ۲، صفحات ۳۸-۴۹
عنوان فارسی New Guidance method for high altitude target Based on Constrained Incremental Predictive Control
چکیده فارسی مقاله 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.
کلیدواژه‌های فارسی مقاله
عنوان انگلیسی New Guidance method for high altitude target Based on Constrained Incremental Predictive Control
چکیده انگلیسی مقاله 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.
کلیدواژه‌های انگلیسی مقاله guidance,Parallel navigation,constrained incremental predictive control,high speed and high altitude target
نویسندگان مقاله Mohammad Yavari |
Faculty of Aerospace Engineering , Malek Ashtar University of Technology, Tehran, Iran

Nemat Allah Ghahremani |
Faculty of Electrical & Computer engineering, Malek Ashtar University of technology, Iran

Reza Zardashtti |
Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

Jalal Karimi |
Faculty of Aerospace Engineering, Malek Ashtar University of Technology, Tehran, Iran

نشانی اینترنتی https://jast.ias.ir/article_172202_c03247d1cd1c9ef1cc8148b3796bf8fc.pdf
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