Neoclassical Guidance for Homing Missiles

A new approach to guidance of homing missiles is considered. Like classical proportional navigation (PN), the new guidance law utilizes line-of-sight (LOS) rate measurement only. However, its performance is superior to PN, in the sense that zero-miss-distance (ZMD) is obtained against highly maneuvering targets. This merit is achieved withneithertheestimationoftargetmaneuvernortimetogo.Inthederivationofthenewguidancelaw,alinearized formulation of the PN interception kinemtics is used. Based on themethod ofadjoints, it is proved analytically that whentheoveralltransferfunctionofthemissileisbiproper,thatis, thedegreeofthenumeratorequalsthedegreeof thedenominator,ZMDisobtained.TheZMDpropertyholdsinthefollowingcases:deterministictargetmaneuvers, random target maneuvers, deterministic target maneuvers with random starting times, fading noise, and passiveand active-receiver noise. The realization of the new guidance law requires lead compensation. When LOS rate measurement is corrupted by noise, lead ‐lag compensation can be used instead. These design considerations are illustrated in simulations, which verify that negligiblemissdistanceagainst highly maneuvering targetsis obtained even when the LOS rate measurement is noisy.

[1]  K. Narendra,et al.  A Geometrical Criterion for the Stability of Certain Nonlinear Nonautonomous Systems , 1964 .

[2]  Ilan Rusnak,et al.  Optimal Guidance for High-Order and Acceleration Constrained Missile , 1991 .

[3]  Stephan A. R. Hepner,et al.  Adaptive two-time-scale tracking filter for target acceleration estimation , 1991 .

[4]  E. J. Holder,et al.  An analysis of modern versus classical homing guidance , 1990 .

[5]  M. Guelman.  The stability of proportional navigation systems , 1990 .

[6]  I. Sandberg.  A frequency-domain condition for the stability of feedback systems containing a single time-varying nonlinear element , 1964 .

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

[8]  Paul Zarchan.  Complete Statistical Analysis of Nonlinear Missile Guidance Systems - SLAM , 1979 .

[9]  W.-T. Chang,et al.  Incremental maneuver estimation model for target tracking , 1992 .

[10]  R. Moose.  An adaptive state estimation solution to the maneuvering target problem , 1975 .

[11]  Toshiyuki Tanaka,et al.  Hyperstable range in homing missiles , 1990 .

[12]  Weiping Li,et al.  Applied Nonlinear Control , 1991 .

[13]  Paul Zarchan,et al.  Proportional navigation and weaving targets , 1995 .

[14]  Pini Gurfil,et al.  Finite Time Stability Approach to Proportional Navigation Systems Analysis , 1998 .

[15]  N. A. Shneydor,et al.  Missile guidance and pursuit , 1998 .

[16]  I. Rusnak.  Advanced guidance laws for acceleration-constrained missile, randomly maneuvering target and noisy measurements , 1996, IEEE Transactions on Aerospace and Electronic Systems.

[17]  Josef Shinar,et al.  Stochastic Analysis of the Interception of Maneuvering Antisurface Missiles , 1997 .

[18]  Mauricio Guelman,et al.  A qualitative study of proportional navigation , 1971, IEEE Transactions on Aerospace and Electronic Systems.

[19]  Shaul Gutman.  On Optimal Guidance for Homing Missiles , 1979 .

[20]  R. G. Cottrell.  Optimal intercept guidance for short-range tactical missiles , 1971 .

[21]  Robert J. Fitzgerald.  Shaping Filters for Disturbances with Random Starting Times , 1979 .