Effect of autopilot structure on proportional navigation guidance

The dynamic characteristics of acceleration autopilot and attitude autopilot are discussed in detail. Also, a comparison study was made between these two different types of control schemes for guidance loop. By means of simulation, it is concluded that the guidance accuracy is mainly determined by the slowest subsystem among different system dynamics. For air-to-ground missiles, with limited terminal guidance time, the control scheme of acceleration autopilot combined with proportional navigation guidance (PNG) law is the better choice.