New generations of spacecraft data handling systems: Less Harness , More Reliability
- Paper number
IAC-06-D1.4.09
- Author
Mr. Rouzbeh Amini, Delft University of Technology, The Netherlands
- Coauthor
Mr. Gerard Aalbers, Technical University of Delft (TUDelft), The Netherlands
- Coauthor
Mr. Rob Hamann, Technical University of Delft (TUDelft), The Netherlands
- Coauthor
Dr. Wim Jongkind, Technical University of Delft (TUDelft), The Netherlands
- Coauthor
Mr. Pieter Beerthuizen, Dutch Space B.V., The Netherlands
- Year
2006
- Abstract
Over the last two decades the miniaturization and integration of electronics has revolutionized many systems in various areas as diverse as computing, communications, and household appliances. Smaller systems which use less power but are able to perform more functions with a higher speed, are ideally suited for space applications where mass and power are at a premium. Bus and data handling subsystems of spacecrafts, which provide the interfaces and data links between subsystems such as payload, telecommunication, on-board computer, etc., are also affected by technology advancements in the last decades.
As the systems grow smaller in both mass and volume, the mass and volume of wiring harnesses and connectors become the limiting factors in the miniaturization. Besides this, other important factors in space applications such as deterministic behavior, fault tolerance, and redundancy remain the primary criteria which should be fulfilled by the bus standard.
Next to traditional approaches, such as galvanic isolation of power and data lines, to increase the reliability of data handling system, various bus standards for space applications were introduced since the late eighties. Harness reduction and reliability issues have always been the key design factors. The OBDH and MACS bus standards were introduced by ESA and were the first bus types to be used. Mil-Std-1533 was the significant follower, which was widely used after OBDH and MACS. However, bus architectures have always been subject to improvement and development, due to various requirements of different systems and missions. The technology advancement in the direction of miniaturization, however, ensures more reliability and less harnessing next to realizing more functions. As a consequence, the CAN-bus has become more popular during the last few years. Also, many small satellites and CubeSats have converged to use this standard, as well as the I 2C bus standard.
In the last five to ten years, the need for high speed data buses for data handling purposes increased, usually in combination with Digital Signal Processors (DSP). Therefore, some studies have been performed on using FireWire (IEEE-1394). Currently the de facto standard is SpaceWire, which is being used by both NASA and ESA. Furthermore, studies are performed on the use of optical and electromagnetic wireless bus systems. These enable an additional reduction in harnessing and provide more flexibility, functionality, and even bus reconfiguration.
In this paper, we aim to survey the different major bus standards which are used in on-board data handling system of satellites and spacecrafts. The survey will focus on the fault tolerance and reliability of the different standards, but will also address harnessing. We will show that the miniaturization has improved the functionality and power efficiency of the buses, while maintaining the required reliability.
- Abstract document
- Manuscript document
IAC-06-D1.4.09.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.