Use of USB Interface in Space Programs
- Paper number
IAC-07-B4.7.05
- Author
Mr. Giorgio Magistrati, Carlo Gavazzi Space S.p.A., Italy
- Coauthor
Dr. Massimiliano Pastena, Carlo Gavazzi Space S.p.A., Italy
- Year
2007
- Abstract
Carlo Gavazzi Space (CGS) is currently involved in the analysis of the suitability of the USB 2.0 interface in a space environment. The USB 2.0 has several characteristics that make it advantageous and gainful: 1)Master-slave architecture that foresees a single host controller ( that could be the Spacecraft Computer) and several slave devices ( connected into a daisy chain): up to 127 devices may be connected to a single host controller 2)Hot swapping that allows the connection and disconnection of slave devices without powering down or rebooting the computer/single host controller 3)High Data Rate up to 480 Mbits/sec in the USB2.0 version (USB 2.0 Hi-Speed, that seems ideal for Mass Memory Unit, CCD Cameras…) but also the so called Full Speed of 12Mbit/sec reachable with the previous USB version 1.1 seems attractive for certain space applications ( wheel, …) 4)Reduced number of needed pins: the USB 2.0 due to is serial transmission characteristics requires only four signal pins that is carried by the connector shell itself, this means a reduction in the satellite harness weight and complexity. 5)The USB physical layer foresees that the slave devices can sink up to 500 mA from the host controller : this feature seems attractive in scenarios where for example the wheel power electronics is supplied directly by the satellite power bus and the wheel control electronics could be directly powered by the USB I/F avoiding the use of internal DC/DC converters. 6)The large diffusion of USB devices will dramatically simplify the activity of manufacturing simulation/emulation HW tools for debugging or qualification test sessions. The usage of a plug and play and smart electrical I/F as the USB seems ideal for a space application for two different reasons: a)Redundancies at satellite S/s equipment level: the hot swapping capability will allow the implementation of hot/cold redundancies with a very limited increase of complexity in terms of weight or H/W I/Fs b)Possibility to upgrade some S/s equipment in a Satellite family without changes in the satellite electrical interfaces The CGS roadmap for the usage of the USB 2.0 I/F in space application foresees the analysis of potential candidates for the connector type to be used as space harness and the implementation study of a USB 2.0 IP core inside a FPGA (available also in space qualified version) . Also the scenario of a first possible space application of the USB will be described.
- Abstract document
- Manuscript document
IAC-07-B4.7.05.pdf (🔒 authorized access only).
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