سال انتشار: ۱۳۸۹

محل انتشار: دهمین همایش انجمن هوافضای ایران

تعداد صفحات: ۷

نویسنده(ها):

S. H. Jalali-Naini – Faculty of Engineering, Tarbiat Modares University, IRAN

چکیده:

In this paper, a modified guidance law is presented based on zero-effort errors or velocities-to-be-gained for explicit or implicit implementation. First, a closedloop guidance scheme is introduced for the ascending phase of flight. Second, a first-order nonlinear differential equation of the sensitivity matrix is obtained in terms of gravity gradient, partial derivatives of sensitivity matrices, and velocity-to-be-gained. This differential equation may be solved simultaneously with the implicit guidance equation onboard obtaining the velocity-to-be-gained. Third, an algorithm to calculate the thrust direction is presented in terms of zero-effort errors or velocities-to-be-gained