Use of New Developments of Attitude Control Sensors for the Micro-Satellite Flying Laptop

Paper number

IAC-06-B5.6.18

Author

Mr. Matthias Waidmann, University of Stuttgart, Germany

Coauthor

Mr. Georg Grillmayer, University of Stuttgart, Germany

Coauthor

Mr. Dominik Saile, University of Stuttgart, Germany

Coauthor

Mr. Christian Waidmann, University of Stuttgart, Germany

Coauthor

Mrs. Viola Wolter, Steinbeis Transferzentrum Raumfahrt, Germany

Year

2006

Abstract

Currently the Institute of Space Systems (IRS) at the University of Stuttgart is in the implementation phase of its first micro-satellite Flying Laptop. Within the scope of the small satellite program of the IRS the Flying Laptop is the first satellite in a consecutive series of small spacecraft. The Flying Laptop with it's primary mission objectives being technology demonstration is developed and built by faculty, PhD/master students and in cooperation with the industry.
This paper provides an outline of the used attitude control hardware sensors and actuators. Several new developments are conducted and will be flown for the first time. 

For the measurement of the satellite's rotational rates the commercial fiber optic rate sensor “C-FORS” is used. This upgraded, higher accurate version of a COTS fiber optic rate sensor is designed for terrestrial applications. For redundancy reasons four rate sensors are arranged in a tetrahedron configuration. Thus, the three-axis measurements of the satellite's rotational rates are not restricted by a failure of any of the four sensors. 
For the tetrahedron mounting of the four sensors a rate sensor system was design at IRS providing both the mounting platform for the sensors and the interface electronic unit. Besides the interface connectors to the power control and distribution unit (PCDU), the on-board computer (OBC) and the four rate sensors, the separate power supply for each sensor is available at the interface electronic unit. The voltages required for accurate sensor operation are generated from the voltage supplied by the PCDU. Another component of the interface electronic unit is the Integrated Bus for Intelligent Sensors (IBIS). The measurement data which is generated simultaneously in all sensors is transmitted to the OBC via this common bus. Furthermore the rate sensor system is equipped with additional shielding against cosmic radiation to extend the period until the maximum tolerable radiation dose is reached.
By combining the mounting platform for the rate sensors with the box housing the electronic unit for power supply and communication a compact rate sensor system for four fiber optic rate sensors in a tetrahedron configuration was designed.

Abstract document

IAC-06-B5.6.18.pdf

Manuscript document

IAC-06-B5.6.18.pdf (🔒 authorized access only).

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