Terminal Guidance Law for UAV Based on Receding Horizon Control Strategy

Terminal guidance law against the maneuvering target is always the focal point. Most of the literatures focus on estimating the acceleration of target and time to go in guidance law, which are difficult to acquire. This paper presents a terminal guidance law based on receding horizon control strategy. The proposed guidance law adopts the basic framework of receding horizon control, and the guidance process is divided into several finite time horizons. Then, optimal control theory and target motion prediction model are used to derive guidance law for minimum time index function with continuous renewal of original conditions at the initial time of each horizon. Finally, guidance law performs repeated iteration until intercepting the target. The guidance law is of subprime optimal type, requiring less guidance information, and does not need to estimate the acceleration of target and time to go. Numerical simulation has verified that the proposed guidance law is more effective than traditional methods on constant and sinusoidal target with bounded acceleration.

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

[2]  Gyorgy Hexner,et al.  Stochastic optimal control guidance law with bounded acceleration , 2007 .

[3]  Mario Sznaier,et al.  Receding Horizon Control Lyapunov Function Approach to Suboptimal Regulation of Nonlinear Systems , 2000 .

[4]  Sangkyung Sung,et al.  A Hybrid Guidance Law for a Strapdown Seeker to Maintain Lock-on Conditions against High Speed Targets , 2013 .

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

[6]  D. Ghose,et al.  Accurate Time-to-Go Estimation for Proportional Navigation Guidance , 2014 .

[7]  T. L. Vincent,et al.  Guidance against maneuvering targets using Lyapunov optimizing feedback control , 2002, Proceedings of the 2002 American Control Conference (IEEE Cat. No.CH37301).

[8]  Xin Jiang,et al.  Nonlinear receding horizon guidance for spacecraft formation reconfiguration on libration point orbits using a symplectic numerical method. , 2016, ISA transactions.

[9]  Jun Zhou,et al.  Impact-Time-Control Guidance Law for Missile with Time-Varying Velocity , 2016 .

[10]  Chun-Hsu Ko,et al.  Guidance and obstacle avoidance of passive robot walking helper based on receding horizon control , 2014, 2014 IEEE International Conference on Automation Science and Engineering (CASE).

[11]  Abolghasem Naghash,et al.  Optimal Guidance Based on Receding Horizon Control and Online Trajectory Optimization , 2013 .

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

[13]  Min-Jea Tahk,et al.  Recursive time-to-go estimation for homing guidance missiles , 2002 .

[14]  Jie Guo,et al.  Impact Time Guidance Law Considering Autopilot Dynamics Based on Variable Coefficients Strategy for Maneuvering Target , 2015 .

[15]  Paul Zarchan,et al.  Tactical and strategic missile guidance , 1990 .

[16]  Xiaodong Liu,et al.  Guidance law against maneuvering targets with intercept angle constraint. , 2014, ISA transactions.

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

[18]  Di Zhou,et al.  Design of three-dimensional nonlinear guidance law with bounded acceleration command , 2015 .

[19]  Jiang Wang,et al.  Continuous second-order sliding mode based impact angle guidance law , 2015 .

[20]  Richard J. Prazenica,et al.  Receding Horizon Control for MAVs with Vision-Based State and Obstacle Estimation , 2007 .

[21]  Harshal B. Oza,et al.  Generalized Model Predictive Static Programming and Angle-Constrained Guidance of Air-to-Ground Missiles , 2014 .

[22]  Toshiyuki Ohtsuka,et al.  Time-Variant Receding-Horizon Control of Nonlinear Systems , 1996 .

[23]  Eric Wahl,et al.  Non-linear receding horizon control based real-time guidance and control methodologies for launch vehicles , 2016, 2016 IEEE Aerospace Conference.

[24]  Bin Fu,et al.  Integrated Guidance and Control Method for the Interception of Maneuvering Hypersonic Vehicle Based on High Order Sliding Mode Approach , 2015 .