سال انتشار: ۱۳۸۹

محل انتشار: دهمین همایش انجمن هوافضای ایران

تعداد صفحات: ۴

نویسنده(ها):

Mohammad Samani – Science & Research Brance, Islamic Azad university(IAU)
Habib Ganbarpoue Asl – Aerospace Engineering Department,Sharif University of Technology,Tehran,Iran
Seid Hossin Pourtakdust – Center for Researchand Developmentin SpaceS cienceand Technology,Aerospace Engineering Department, Sharif UniversityofTechnology,Tehran,Iran

چکیده:

The goal of this paper is to estimate attitude and position of a air vehicle in space. The air vehicle navigation system includes IMU/GPS/Magnetometer/Altimeter sensors. First of all, the dynamic modeling of the fly is presented and then by solving differential equations of flight using forth order Runge-Kutta, the ideal path is generated. Consequently, regarding to the fly path, sensors output can be found. After adding errors to Inertia and navigation sensors, the sensors outputs are simulated. Finally, with using Extended Filter Kalman (EKF) algorithms, sensors data will be merged and thus attitude and position of the air vehicle are determined and then the estimation errors will be calculated