System-on-chip for space applications is now a reality
- Paper number
IAC-08.B4.6.B2
- Author
Mr. Torbjörn Hult, Saab Space AB, Sweden
- Year
2008
- Abstract
The first generation of true system-on-chip (SoC) devices including a powerful CPU with many different on-chip I/O functions have been discussed for many years and are now available in radiation-hardened technology. The main advantage with a SoC device, compared to today’s typical processor boards, is a more compact solution providing several interfaces like serial links and serial data buses. Fast serial links opens up the opportunity of easily designing network topologies that can be used for improving the overall system processing performance as well as creating redundancy schemes that handle faults in various ways. An example of a modern SoC device is the COLE chip from Saab Space. COLE provides eight SpaceWire nodes that can be connected to links running up to 200 Mbps, two CAN bus controllers, three 1553 bus controllers and several other serial and parallel interfaces. The chip itself and how it is used in existing architectures have been presented in other conferences like DASIA. The proposed paper will show a new architecture for a spacecraft platform controller based on reusing the same SoC device in the following applications: * Generic processor executing the platform communication and control tasks * Mass memory controller supporting up to 64 Gbit of data storage * Star Tracker processor interfacing an external optical head * GPS receiver processor interfacing an external RF and antenna unit An additional TM/TC and supervisor module will make up a complete spacecraft controller. The Star Tracker and GPS receiver processors are new functions not earlier included in the spacecraft controller. The modules will be inter-connected using up to seven SpaceWire links from each module to connect five pairs of the listed functions in optimized redundancy without any power-consuming router devices. Although it is possible to use the modules in network redundancy, for instance to execute Star Tracker processing in the GPS receiver processor, this is not considered as baseline due to unnecessary complications of the software and the system validation process. The mass of the listed functionality including power supplies and box mechanics can be decreased, from a value of 10 – 15 kg to about 7 – 8 kg when using today’s packaging technology for a fully redundant spacecraft controller. A further improvement is possible when going to advanced packaging concepts using silicon or ceramic substrates, reducing the mass to less than 1 kg.
- Abstract document
- Manuscript document
IAC-08.B4.6.B2.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.