کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
1714590 1519950 2014 14 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Magnetometer-only attitude and angular velocity filtering estimation for attitude changing spacecraft
ترجمه فارسی عنوان
برآورد فیلتر نگرش سرعت زاویه ای و مغناطیس فقط برای تغییر نگرش فضاپیمای
کلمات کلیدی
برآورد نگرش و سرعت زاویه ای، فقط مغناطیس سنج بهبود فیلتر متوالی در زمان واقعی قابل مشاهده بودن،
موضوعات مرتبط
مهندسی و علوم پایه سایر رشته های مهندسی مهندسی هوافضا
چکیده انگلیسی
This paper presents an improved real-time sequential filter (IRTSF) for magnetometer-only attitude and angular velocity estimation of spacecraft during its attitude changing (including fast and large angular attitude maneuver, rapidly spinning or uncontrolled tumble). In this new magnetometer-only attitude determination technique, both attitude dynamics equation and first time derivative of measured magnetic field vector are directly leaded into filtering equations based on the traditional single vector attitude determination method of gyroless and real-time sequential filter (RTSF) of magnetometer-only attitude estimation. The process noise model of IRTSF includes attitude kinematics and dynamics equations, and its measurement model consists of magnetic field vector and its first time derivative. The observability of IRTSF for small or large angular velocity changing spacecraft is evaluated by an improved Lie-Differentiation, and the degrees of observability of IRTSF for different initial estimation errors are analyzed by the condition number and a solved covariance matrix. Numerical simulation results indicate that: (1) the attitude and angular velocity of spacecraft can be estimated with sufficient accuracy using IRTSF from magnetometer-only data; (2) compared with that of RTSF, the estimation accuracies and observability degrees of attitude and angular velocity using IRTSF from magnetometer-only data are both improved; and (3) universality: the IRTSF of magnetometer-only attitude and angular velocity estimation is observable for any different initial state estimation error vector.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Acta Astronautica - Volume 102, September–October 2014, Pages 89-102
نویسندگان
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