سال انتشار: ۱۳۸۴
محل انتشار: سیزدهمین کنفرانس سالانه مهندسی مکانیک
تعداد صفحات: ۸
Jalali-Naini – Department of Aerospace Engineering , Sharif Univercity of Technology , Tehran , Iran
Pourtakdoust – Department of Aerospace Engineering , Sharif Univercity of Technology , Tehran , Iran
In this paper, equations predicted errors for final position and velocity vectors are derived by adding a model for the vehicle thrust/ drag approximation in the presence of gravity and autopilot dynamics. The guidance / control system in assumed as a linear time-variant arbitrary- order. The presented equations are applicable to both endoatmospheric and exoatmospheric missions and are developed for two classes of system. First, for systems in which the acceleration commands is truncated at a specified time. Second , for systems in which the corrective maneuvers are cut off at a specified time, regardless of the acceleration commands. The gravitational acceleration is modeled as a given vectorial function of time. Furthermore . the method is modified for an endoatmospheric / exoatmospheric interceptor having cut-off capability to compensate cut-off delay.