Modern Homing Missile Guidance Theory and Techniques

JOHNS HOPKINS APL TECHNICAL DIGEST, VOLUME 29, NUMBER 1 (2010)42 Modern Homing Missile Guidance Theory and TechniquesNeil F. Palumbo, Ross A. Blauwkamp, and Justin M. LloydINTRODUCTIONC lassical Guidance laws, with proportional navigation (PN) being the most prominent example, had proven to be effective Homing Guidance strategies up through the 1960s and early 1970s. By the mid-1970s, however, the predicted capability of future airborne threats (highly maneuverable aircraft, supersonic cruise missiles, tacti-cal and strategic ballistic Missile reentry vehicles, etc.) indicated that PN-guided weapons might be ineffective against them. However, by that time, the application of optimal control Theory to Missile Guidance problems had sufficiently matured, offering new and potentially prom-ising alternative Guidance law 3 Around this time, the computer power required to mechanize such advanced algorithms also was sufficient to make their application Modern Guidance laws are derived using linear- quadratic (LQ) optimal control Theory to obtain analytic feedback , 4, 5 Many of the Modern lassically derived Homing Guidance laws, such as proportional navigation, can be highly effective when the Homing mis-sile has significantly more maneuver capability than the threat.

Here, we start by considering a general nonlinear dynamics model of the system to be controlled (i.e., the “plant”). This dynamics model can be expressed as x f$ ( )t t= ( (x u), ( )t t, ) . (1) In Eq. 1, x is the n-dimensional state vector of real elements ( )x u! !R Rn m, is the control vector, and

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