IAA Space Exploration Conference
Planetary Robotic and Human Spaceflight Exploration
09 January 2014
A pre-Summit Conference of the
HEADS OF SPACE AGENCIES SUMMIT ON EXPLORATION
5) Space Exploration: The Imperative of Global Cooperation
Performance Evaluation of Attitude Determination Methods for InnoSAT
Nanosatellite Project
Md Azlin Md Said 1, Muhamad Fadly2, Adam Ain 2, Mohd Faizal Alaudin 3, Harijono
Djojodihardjo3, Radzuan Razali4
(1) School of Civil Engineering, Universiti Sains, Engineering Campus, 14300 Nibong Tebal Malaysia
(2) CEDEC, Universiti Sains Malaysia, Engineering Campus, 14300 Nibong Tebal Malaysia
(3) Dept of Aerospace Eng, Faculty of Engineering, University Putra Malaysia, Serdang, Selangor
(4) Dept Fundamental and Applied Science, Faculty of Science and Information Technology, Universiti
Teknologi Petronas, Bandar Seri Iskandar, 31750 Tronoh, Perak.
Keywords:
Attitude determination, Performance Evaluation, Deterministic and recursive methods, InnoSAT
(Sample text: 2 pages / 900 words maxi)
Abstract
The purpose of this paper is to develop and evaluate the accuracy and speed performance of
the five point base and one recursive approach to estimate the attitude and angular rates of
InnoSAT. The methods use optimal combination of sun sensors and magnetometers
measurement vector in the body and orbit frames. The similar source of vector was packed in a
matrix and fed to the methods according to the respective way. Due to the moments of inertia,
the attitude of each axis is mutually affected which impacted the accuracy of the estimated
attitude while using the EKF. The use of sun sensors introduced estimation problem as owing to
eclipse.
A practical strategy is proposed to tackle the problem while running the methods in the attitude
determination system (ADS) along its position in the orbit. The result of this paper is possible to
be used as a reference and benchmark for engineers to design and implement deterministic and
recursive attitude determination using the sun sensor and magnetometer and also to give some
information on how to handle eclipse problems. The study provides a practical solution to
choose the deterministic and recursive methods to be implemented in the embedded ADS. This
study also offers some brief evaluation of the use of numbers of measurement data which
originate from different sensors in determining the attitude of small satellite. Furthermore, it
provides improvement of the EKF algorithm flow to become more practical for implementation
and give practical solution for the eclipse problem to be overcome.
To develop and evaluate the accuracy and speed performance of the five point base and one
recursive approach to estimate the attitude and angular rates of InnoSAT. The methods use
optimal combination of sun sensors and magnetometers measurement vector in the body and
orbit frames. The similar source of vector was packed in a matrix and fed to the methods
according to the respective way. Due to the moments of inertia, the attitude of each axis is
mutually affected which impacted the accuracy of the estimated attitude while using the EKF.
The use of sun sensors introduced estimation problem as owing to eclipse. A practical strategy
is proposed to tackle the problem while running the methods in the attitude determination
system (ADS) along its position in the orbit. The result of this paper is possible to be used as a
reference and benchmark for engineers to design and implement deterministic and recursive
attitude determination using the sun sensor and magnetometer and also to give some
information on how to handle eclipse problems.
The study provides a practical solution to choose the deterministic and recursive methods to be
implemented in the embedded ADS. This study also offers some brief evaluation of the use of
numbers of measurement data which originate from different sensors in determining the attitude
of small satellite. Furthermore, it provides improvement of the EKF algorithm flow to become
more practical for implementation and give practical solution for the eclipse problem to be
overcome.
To develop and evaluate the accuracy and speed performance of the five point base and one
recursive approach to estimate the attitude and angular rates of InnoSAT. The methods use
optimal combination of sun sensors and magnetometers measurement vector in the body and
orbit frames. The similar source of vector was packed in a matrix and fed to the methods
according to the respective way. Due to the moments of inertia, the attitude of each axis is
mutually affected which impacted the accuracy of the estimated attitude while using the EKF.
The use of sun sensors introduced estimation problem as owing to eclipse. A practical strategy
is proposed to tackle the problem while running the methods in the attitude determination
system (ADS) along its position in the orbit. The result of this paper is possible to be used as a
reference and benchmark for engineers to design and implement deterministic and recursive
attitude determination using the sun sensor and magnetometer and also to give some
information on how to handle eclipse problems.
The study provides a practical solution to choose the deterministic and recursive methods to be
implemented in the embedded ADS. This study also offers some brief evaluation of the use of
numbers of measurement data which originate from different sensors in determining the attitude
of small satellite. Furthermore, it provides improvement of the EKF algorithm flow to become
more practical for implementation and give practical solution for the eclipse problem to be
overcome.
To develop and evaluate the accuracy and speed performance of the five point base and one
recursive approach to estimate the attitude and angular rates of InnoSAT. The methods use
optimal combination of sun sensors and magnetometers measurement vector orbit frames. The
similar source of vector was packed in a matrix and fed to the methods according to the
respective way. Due to the moments of inertia, the attitude of each axis is mutually affected
which impacted the accuracy of the estimated attitude while using the EKF. The use of sun
sensors introduced estimation problem as owing to eclipse. A practical strategy is proposed to
tackle the problem while running the methods in the attitude determination system (ADS). The
result is possible to be used as a reference and benchmark for engineers to design and
implement deterministic and recursive attitude determination using the sun sensor and
magnetometer and also to give some information on how to handle eclipse problems.