Missile guidance with constrained intercept body angle
A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.
Time-optimal impact angle control for vertical plane engagements
As a part of trajectory modulation to increase terminal effectiveness, impact angle control is required in the terminal phase of tactical missile systems. Moreover, the missile systems are allowed to have only low altitude and minimum flight time to reduce the probability of detection by sensors of missile defence systems and thus to increase survivability. In this paper, a simple numerical solution for a time-optimal control law is suggested in the case of constrained missile maneuverability and impact angle for a first-order-lag autopilot. The numerical solution utilizes an analytic solution of a simplified problem with a zero-lag autopilot assumption to determine optimal switching instants. Performance of the proposed control law is tested by a simulation study.
A spreader acceleration guidance scheme for command guided surface-to-air missiles
A novel guidance law for command-guided surface-to-air missiles is presented which attempts to reduce the integral control effort while at the same time taking into account the maneuvers of the target. In the process, the proposed law achieves some improvements in interception times and miss distances. A Monte Carlo simulation of a missile-target engagement in an inclined plane is carried out to check the performance of the proposed guidance law in comparison with existing laws in terms of integral control effort, interception time, and miss distance. The proposed method suffers from the obvious drawback of having to estimate the target acceleration, unlike the PN (proportional navigation) guidance law. It also needs somewhat higher time for computations (unlike PN). This is the reason for proposing this guidance law in a command guidance mode, since powerful ground based computers will be available to carry out the iterations.<<ETX>>