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- Deutsches Zentrum für Luft- und Raumfahrt (DLR), Institut für Raumfahrtsysteme (2) (remove)
Time-triggered communication is widely used throughout several industry do-
mains, primarily for reliable and real-time capable data transfers. However,
existing time-triggered technologies are designed for terrestrial usage and not
directly applicable to space applications due to the harsh environment. In-
stead, specific hardware must be developed to deal with thermal, mechanical,
and especially radiation effects.
SpaceWire, as an event-triggered communication technology, has been used
for years in a large number of space missions. Its moderate complexity, her-
itage, and transmission rates up to 400 MBits/s are one of the main ad-
vantages and often without alternatives for on-board computing systems of
spacecraft. At present, real-time data transfers are either achieved by prior-
itization inside SpaceWire routers or by applying a simplified time-triggered
approach. These solutions either imply problems if they are used inside dis-
tributed on-board computing systems or in case of networks with more than
a single router are required.
This work provides a solution for the real-time problem by developing
a novel clock synchronization approach. This approach is focused on being
compatible with distributed system structures and allows time-triggered data
transfers. A significant difference to existing technologies is the remote clock
estimation by the use of pulses. They are transferred over the network and
remove the need for latency accumulation, which allows the incorporation of
standardized SpaceWire equipment. Additionally, local clocks are controlled
decentralized and provide different correction capabilities in order to handle
oscillator induced uncertainties. All these functionalities are provided by a developed Network Controller (NC), able to isolate the attached network and
to control accesses.
Within this thesis a new philosophy in monitoring spacecrafts is presented: the
unification of the various kinds of monitoring techniques used during the
different lifecylce phases of a spacecraft.
The challenging requirements being set for this monitoring framework are:
- "separation of concerns" as a design principle (dividing the steps of logging
from registered sources, sending to connected sinks and displaying of
information),
- usage during all mission phases,
- usage by all actors (EGSE engineers, groundstation operators, etc.),
- configurable at runtime, especially regarding the level of detail of logging
information, and
- very low resource consumption.
First a prototype of the monitoring framework was developed as a support library
for the real-time operating system
RODOS. This prototype was tested on dedicated hardware platforms relevant for
space, and also on a satellite demonstrator used for educational purposes.
As a second step, the results and lessons learned from the development and usage
of this prototype were transfered to a real space mission: the first satellite
of the DLR compact satellite series - a space based platform for DLR's own
research activities. Within this project, the software of the avionic subsystem
was supplemented by a powerful logging component, which enhances the traditional
housekeeping capabilities and offers extensive filtering and debugging
techniques for monitoring and FDIR needs. This logging component is the major
part of the flight version of the monitoring framework. It is completed by
counterparts running on the development computers and as well as the EGSE
hardware in the integration room, making it most valuable already in the
earliest stages of traditional spacecraft development.
Future plans in terms of adding support from the groundstation as well will lead
to a seamless integration of the monitoring framework not only into to the
spacecraft itself, but into the whole space system.