Part of #ANALYSIS OF THE PREDICTED ERRORS IN GUIDANCE LAWS# :
Publishing year : 2005
Conference : 13th Annual Conference of Mechanical Engineering
Number of pages : 8
Abstract: In this paper, the equations predicted errors for the final position and velocity vectors are derived by adding a model for the vehicle's thrust / drag approximation in the presence of gravity and autopilot dynamics. The guidance / control system in assumed as an arbitrary-order linear time-variant. The presented equations are applicable to both endoatmospheric and exoatmospheric missions and are developed for two classes of system. First, for systems in which acceleration commands are truncated at a specified time. Second, for systems in which corrective maneuvers are cut off at a specified time, regardless of acceleration commands. The gravitational acceleration is modeled as a given vectorial function of time. Further. The method is modified for an endoatmospheric / exoatmospheric interceptor having a cut off capability to compensate for a cut-off delay.