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A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a second order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation w

A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a second order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with a missile acceleration feedback term and a navigation ratio to account for first order autopilot time lag. This configuration results in nearly optimal miss distance behavior, with sensitivity to unmodeled errors being substantially less than that in modern guidance systems. The system is particularly useful for high altitude, minimally maneuvering targets.

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A method for terminal guidance of a missile to intercept a target, said method being a second order scheme employing a predictive proportional navigation system including an autopilot, an intertial reference unit and a noise adaptive guidance computer, said system including noise and radome error co

A method for terminal guidance of a missile to intercept a target, said method being a second order scheme employing a predictive proportional navigation system including an autopilot, an intertial reference unit and a noise adaptive guidance computer, said system including noise and radome error compensation, said computer having an adaptive guidance filtering system, said proportional navigation system having input values for line of sight (LOS) angle seqqqtd and tc, where esM-qsM, an estimate of LOS angle ssM-ssM, said method comprising the steps of: applying the boresight error angle esM-ssM-ssssqsqsqsqsqsqesM-ssM-ss2Vc; combining said multiplied LOS rate with acceleration term YM at a third combining point to provide the term 2VcsM; multiplying the residual LOS angle by AVc to provide the value AVc(sM-sc(sM-s2VcsM at a fourth combining point to provide the value 2VcsM+AVc(sM-s2VcsM+AVc(sM-ssM-ssss2 and applying that product to a sixth combining point; multiplying the missile lateral acceleration term YM by a gain C4 which is a function of autopilot dynamics lM and Tgo, the value C4 YM being fed back to said sixth combining point; multiplying said sixth combining point output C4YM+C2sgo; and applying the immediately preceding term to said autopilot as command acceleration to modify the position of the missile control surfaces and to account for first order autopilot time lag, thereby providing nearly optimal miss distance and low sensitivity to radome error.