Lyapunov-based impact time control guidance laws against stationary targets

Nonlinear guidance laws that consider impact time constraints are proposed. Two-dimensional and three-dimensional impact time control guidance laws are derived using Lyapunov stability theory. Under the consideration of the nonlinear kinematics, it is shown that the missile states converge to the desired equilibrium point by the Lyapunov stability theory. The singularity issue of the proposed guidance laws is also analyzed. Numerical simulations are performed to verify the performance of the proposed guidance laws.

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

[2]  Min-Jea Tahk,et al.  Optimal Guidance Laws with Terminal Impact Angle Constraint , 2005 .

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

[4]  Radhakant Padhi,et al.  Impact-Angle-Constrained Suboptimal Model Predictive Static Programming Guidance of Air-to-Ground Missiles , 2012 .

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

[6]  Jang Gyu Lee,et al.  Biased PNG law for impact with angular constraint , 1998 .

[7]  Camille Alain Rabbath,et al.  Lyapunov-Based Nonlinear Missile Guidance , 2004 .

[8]  Ji Jun,et al.  Three-dimensional guidance law with terminal impact angle constraint , 2009, 2009 International Conference on Mechatronics and Automation.

[9]  Zhang Youan,et al.  Lyapunov stability based three-dimensional guidance for missiles against maneuvering targets , 2002, Proceedings of the 4th World Congress on Intelligent Control and Automation (Cat. No.02EX527).

[10]  Nathan Harl,et al.  Impact Time and Angle Guidance with Sliding Mode Control , 2009 .

[11]  Youdan Kim,et al.  Design of generalized conceptual guidance law using aim angle , 2004 .

[12]  Joseph Z. Ben-Asher,et al.  Near-Optimal Spatial Midcourse Guidance Law with an Angular Constraint , 2014 .

[13]  Chang-Hun Lee,et al.  Biased PNG Law for Impact-Time Control , 2013 .

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

[15]  Jinzhi Wang,et al.  Partial Integrated Guidance and Control for Missiles with Three-Dimensional Impact Angle Constraints , 2014 .

[16]  Min-Jea Tahk,et al.  Impact-time-control guidance law for anti-ship missiles , 2006, IEEE Trans. Control. Syst. Technol..

[17]  Tae Soo No,et al.  Bank-to-Turn Guidance Law Using Lyapunov Function and Nonzero Effort Miss , 2001 .

[18]  Min-Jea Tahk,et al.  Guidance law to control impact time and angle , 2005, 2005 International Conference on Control and Automation.

[19]  Min-Jea Tahk,et al.  Homing Guidance Law for Cooperative Attack of Multiple Missiles , 2010 .

[20]  Youdan Kim,et al.  Guidance Laws for Anti-Ship Missiles Using Impact Angle and Impact Time , 2006 .

[21]  Chang-Hun Lee,et al.  Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints , 2013, IEEE Transactions on Aerospace and Electronic Systems.

[22]  Taek Lyul Song,et al.  Impact angle control for planar engagements , 1999 .

[23]  Warren Boord,et al.  Lyapunov approach to guidance laws design , 2005 .

[24]  Min-Jea Tahk,et al.  Time-to-go weighted optimal guidance with impact angle constraints , 2006, IEEE Transactions on Control Systems Technology.

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

[26]  Jae-Hyuk Oh,et al.  Capturability of the 3-dimensional pure PNG law , 1999 .

[27]  K-S Kim,et al.  Practical guidance law controlling impact angle , 2007 .