In this paper, several attitude estimation designs are developed for the Tropical Rainfall Measurement Mission (TRMM) spacecraft. A contingency attitude determination mode is required in the event of a primary sensor failure. The final design utilizes a full sixth-order Kalman filter. However, due to initial software concerns, the need to investigate simpler designs was required. The algorithms...

In this study Fault Detection and Isolation (FDI) in the attitude determination and control system of Low Earth Orbit (LEO) satellite is investigated. Attitude determination system uses algebraic method. This method is based on computing any two analytical vectors in the reference frame and measuring these vectors in the body coordinate system (Barishev & Krilov, 1968; Wertz, 1988). As measurin...

Satellite Laser Ranging (SLR) systems successfully measure attitude and spin period of Envisat. During the International Laser Ranging Service (ILRS) campaign the SLR stations observed the satellite and provided measurements that allow determination of the attitude and the spin period of Envisat during year 2013. The spin parameters of the spacecraft are stable within a coordinate system fixed ...

This paper presents the overall mathematical model and results from pseudo linear recursive estimators of attitude and rate for a spinning spacecraft. The measurements considered are vector measurements obtained by sun-sensors, fixed head star trackers, horizon sensors, and three axis magnetometers. Two filters are proposed for estimating the attitude as well as the angular rate vector. One fil...

Extended Kalman filter (EKF) has been widely used for attitude determination in various satellite missions. However, it 1 requires an extensive computational power which is not suitable for nano-satellite application. This paper proposes a gain-scheduled 2 EKF (GSEKF) to reduce the computational requirement in nano-satellite attitude determination process. The proposed GSEKF 3 eliminates the on...

This guideline provides a procedure which specifies and documents consistent, useful, and welldefined coordinate system (or frame) definitions for spacecraft attitude control design and analysis. Several example coordinate frames and transformations are presented to show how these definitions are used to address various Attitude Control System (ACS) design issues. Past experience has shown the ...

Low-cost GNSS receivers with patch antennas track the carrier phases of the GNSS signals with millimeterto centimeter-level accuracy. However, code multipath of several tens of metres, frequent half cycle slips, and receiver clock offsets in the order of milliseconds make reliable kinematic integer ambiguity resolution still challenging. Low-cost inertial sensors are robust against GNSS signal ...

In this paper, a new and efficient algorithm is developed for attitude determination from Global Positioning System signals. The new algorithm is derived from a generalized nonlinear predictive filter for nonlinear systems. This uses a one time-step ahead approach to propagate a simple kinematics model for attitude determination. The advantages of the new algorithm over previously developed met...

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star identification is one of the most important stages in attitude determination with star trackers. this can be performed using matching algorithms between observed stars and a master star catalogue. the main challenge in this approach is to provide a fast and reliable identification algorithm that is sufficiently robust in different pointing views of the star tracker optical system in the sp...