Guidance laws based on H∞ observer considering measurement noises

Since in practice the line-of-sight (LOS) rate is difficult for a pursuer to measure accurately, the robust nonlinear H∞ observer is applied to estimate it using LOS azimuths without any priori information of target maneuvers or its estimate in the presence of measurement noise. A threedimensional guidance law is implemented by replacing the LOS rate with their estimates using only relative range, speed, and LOS azimuths. The stability analyses and performed simulations results show that the presented approach is effective.

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

[2]  M. Fu,et al.  Robust Nonlinear 3fm Filtering , 1996 .

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

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

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

[6]  Chi-Ching Yang,et al.  Optimal pure proportional navigation for maneuvering targets , 1996, Proceedings of 35th IEEE Conference on Decision and Control.

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

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

[9]  Stephen P. Boyd,et al.  Convex Optimization , 2004, Algorithms and Theory of Computation Handbook.

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

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

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

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

[14]  Jie Huang,et al.  A modified CLOS guidance law via right inversion , 1994, Proceedings of 1994 American Control Conference - ACC '94.

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

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

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

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

[19]  J. Shinar,et al.  Optimal guidance law in the plane , 1984 .

[20]  Yuri B. Shtessel,et al.  Integrated Higher-Order Sliding Mode Guidance and Autopilot for Dual Control Missiles , 2009 .

[21]  Xianghua Wang,et al.  Partial Integrated Guidance and Control with Impact Angle Constraints , 2015 .

[22]  Lei Chen,et al.  Ideal proportional navigation for exoatmospheric interception , 2013 .

[23]  Youan Zhang,et al.  Guidance law with impact time and impact angle constraints , 2013 .

[24]  Sheng Sun,et al.  A guidance law with finite time convergence accounting for autopilot lag , 2013 .

[25]  Pini Gurfil.  Zero-miss-distance guidance law based on line-of-sight rate measurement only , 2001 .

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

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

[28]  K. Teo,et al.  Guidance Laws with Finite Time Convergence , 2009 .

[29]  Stephen A. Murtaugh,et al.  Fundamentals of Proportional Navigation and Its Application to an Antisatellite Interceptor , 1966, IEEE Transactions on Aerospace and Electronic Systems.