A novel three‐dimensional guidance law implementation using only line‐of‐sight azimuths

Summary A novel three-dimensional guidance law using only line-of-sight azimuths based on input-to-state stability and robust nonlinear observer is proposed for interception of maneuvering targets. The proposed guidance law does not need any prior information of unknown bounded target maneuvers and uncertainties. Since in practice the line-of-sight rate is difficult for a pursuer to measure accurately, a nonlinear robust observer is introduced to estimate it. A three-dimensional guidance law with bearing only measurement is obtained for interception of maneuvering targets. The presented algorithm is tested using computer simulations against a maneuvering target. Copyright © 2014 John Wiley & Sons, Ltd.

[1]  Sreenatha G. Anavatti,et al.  Observer-based adaptive guidance law considering target uncertainties and control loop dynamics , 2006, IEEE Transactions on Control Systems Technology.

[2]  Dongkyoung Chwa,et al.  Adaptive nonlinear guidance law considering control loop dynamics , 2003 .

[3]  Ciann-Dong Yang,et al.  Nonlinear H∞ Robust Guidance Law for Homing Missiles , 1998 .

[4]  M. Guelman.  The closed-form solution of true proportional navigation , 1976, IEEE Transactions on Aerospace and Electronic Systems.

[5]  Antonios Tsourdos,et al.  Optimal Impact Angle Control Guidance Law Based on Linearization About Collision Triangle , 2014 .

[6]  Masoud Abbaszadeh,et al.  A generalized framework for robust nonlinear Hinfinity filtering of Lipschitz descriptor systems with parametric and nonlinear uncertainties , 2012, Autom..

[7]  J. E. Cochran,et al.  Analytical solutions to a guidance problem , 1991 .

[8]  Fei Tao,et al.  Optimal guidance law design for impact with terminal angle of attack constraint , 2014 .

[9]  W. McEneaney.  Robust/ H ∞ filtering for nonlinear systems , 1998 .

[10]  Nathan Harl,et al.  Impact Time and Angle Guidance With Sliding Mode Control , 2009, IEEE Transactions on Control Systems Technology.

[11]  Stephen A. Murtaugh,et al.  Fundamentals of proportional navigation , 1966, IEEE Spectrum.

[12]  In-Joong Ha,et al.  A Lyapunov-like approach to performance analysis of 3-dimensional pure PNG laws , 1994 .

[13]  Bor-Sen Chen,et al.  Nonlinear fuzzy H∞ guidance law with saturation of actuators against maneuvering targets , 2002, IEEE Trans. Control. Syst. Technol..

[14]  Jie Huang,et al.  A modified CLOS guidance law via right inversion , 1995 .

[15]  Pini Gurfil.  Zero-miss-distance guidance law based on line-of-sight rate measurement only , 2003 .

[16]  Yu Yao,et al.  Guidance law implementation with performance recovery using an extended high-gain observer , 2013 .

[17]  Haibo Ji,et al.  Guidance Laws Based on Input-to-State Stability and High-Gain Observers , 2012, IEEE Transactions on Aerospace and Electronic Systems.

[18]  F. Adler.  Missile Guidance by Three‐Dimensional Proportional Navigation , 1956 .

[19]  Minyue Fu,et al.  Robust nonlinear H∞ filtering , 1996, Autom..

[20]  Chi-Ching Yang,et al.  Optimal pure proportional navigation for maneuvering targets , 1997 .

[21]  N. F. Palumbo,et al.  Basic Principles of Homing Guidance , 2010 .

[22]  Youdan Kim,et al.  Design of Missile Guidance Law via Variable Structure Control , 2000 .

[23]  Di Zhou,et al.  Adaptive Sliding-Mode Guidance of a Homing Missile , 1999 .

[24]  C.-s. Shieh.  Design of three-dimensional missile guidance law via tunable nonlinear H/sub /spl infin// control with saturation constraint , 2007 .

[25]  J. Chern,et al.  Ideal Proportional Navigation , 1992 .