Abstract: A method for engaging a target uses sensors to generate target track(s). The tracks are projected forward in time and associated with a track quality measure. The maximum seeker look angle and beamwidth, acceleration, and net radar sensitivity characteristics are listed for each type of interceptor. A plurality of target intercept times are generated for each interceptor type. The probability that the interceptor can acquire the target is determined from the projected target tracks, the quality measure, and the characteristics. The probability of hitting the target is determined from the probability of acquisition and acceleration of the interceptor type. The probabilities of acquisition and of hitting the target are aggregated, and the type of interceptor to use is the type having (a) an extreme value of the aggregation or (b) the earliest intercept time from among the interceptors having an aggregation value above a threshold value.

Abstract: A guided missile or projectile and associated guidance control are provided to control a path to a point of intersection with a potentially moving target. A new path is repetitively recomputed and acceleration orthogonal to the path is applied to minimize heading error and thereby to converge on the target. The gain of the control function is partly proportional to heading error, but the gain is reduced approaching the point of convergence. In this way, the guidance control is more responsive to actual variance of the true heading error and is less responsive to random error in sensing the target heading, which random error would otherwise increase in its contribution to corrective guidance movements approaching the point of intersection.

Abstract: A guided missile or projectile and associated guidance control are provided to control a path to a point of intersection with a potentially moving target. A new path is repetitively recomputed and acceleration orthogonal to the path is applied to minimize heading error and thereby to converge on the target. The gain of the control function is partly proportional to heading error, but the gain is reduced approaching the point of convergence. In this way, the guidance control is more responsive to actual variance of the true heading error and is less responsive to random error in sensing the target heading, which random error would otherwise increase in its contribution to corrective guidance movements approaching the point of intersection.

Abstract: A method guides an interceptor missile toward an accelerating target. The method sets up a line-of-sight between the interceptor and the target, and monitors the acceleration of the angle of the line-of-sight. The acceleration is multiplied by a gain factor dependent upon the range between the target and the interceptor, to generate a driving acceleration. The acceleration of the interceptor in a direction perpendicular to the line-of-sight is added to the driving acceleration, to generate pre-weighted acceleration. The pre-weighted acceleration is multiplied by a navigation factor to produce commanded interceptor acceleration.