Time-to-go Polynomial Guidance with Trajectory Modulation for Observability Enhancement

A new impact angle control guidance law is introduced for a homing missile system equipped with a passive seeker against a stationary or slowly moving target. The proposed guidance law provides sufficient trajectory modulations, such as oscillatory trajectories, to enhance target observability from angle-only measurements. The derivation of the guidance command is based on the time-to-go polynomial guidance (TPG) law, which is one of the impact angle control laws. Closed-form solutions of the proposed law and their characteristics are investigated. The results inspired the proposed practical time-to-go calculation method and the maximum bounds of guidance gains, which are important for the practical implementation of the guidance law. Linear and nonlinear simulations with a target tracking filter are performed to investigate the performance of the proposed law.

[1]  Taek Lyul Song,et al.  Practical guidance for homing missiles with bearings-only measurements , 1996 .

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

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

[4]  Jin-Ik Lee,et al.  Inverse Optimal Problem for Homing Guidance with Angular Constraint , 2007 .

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

[6]  Branko Ristic,et al.  Beyond the Kalman Filter: Particle Filters for Tracking Applications , 2004 .

[7]  Min-Jea Tahk,et al.  Practical dual-control guidance using adaptive intermittent maneuver strategy , 2001 .

[8]  T. Song,et al.  Suboptimal filter design with pseudomeasurements for target tracking , 1988 .

[9]  Min-Jea Tahk,et al.  Guidance Law for Vision-Based Automatic Landing of UAV , 2007 .

[10]  Min-Jea Tahk,et al.  Observability characteristics of angle-only measurement under proportional navigation , 1995, SICE '95. Proceedings of the 34th SICE Annual Conference. International Session Papers.

[11]  Min-Jea Tahk,et al.  Use of Intermittent Maneuvers for Miss Distance Reduction in Exoatmospheric Engagements , 1989 .

[12]  Richard James Casler.  Dual-Control Guidance Strategy for Homing Interceptors Taking Angle-Only Measurements , 1978 .

[13]  D. Hull,et al.  Linear-quadratic guidance law for dual control of homing missiles , 1990 .

[14]  A. Jameson,et al.  Inverse Problem of Linear Optimal Control , 1973 .

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

[16]  Jason L. Speyer,et al.  Maximum-information guidance for homing missiles , 1984 .

[17]  Debasish Ghose,et al.  Impact Angle Constrained Interception of Stationary Targets , 2008 .

[18]  Jason L. Speyer,et al.  Estimation Enhancement by Trajectory Modulation for Homing Missiles , 1982, 1982 American Control Conference.

[19]  Chang-Kyung Ryoo,et al.  Optimal Guidance with Constraints on Impact Angle and Terminal Acceleration , 2003 .

[20]  M. Kim,et al.  Terminal Guidance for Impact Attitude Angle Constrained Flight Trajectories , 1973, IEEE Transactions on Aerospace and Electronic Systems.

[21]  E. Kreyszig,et al.  Advanced Engineering Mathematics. , 1974 .

[22]  Yaakov Bar-Shalom,et al.  Dual control guidance for simultaneous identification and interception , 1983, The 22nd IEEE Conference on Decision and Control.