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Enhanced Situation Awareness |
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The Advanced Concepts Team is assessing a novel approach to infer the health status of the spacecraft and its instrumentations from the readings of few, strategically placed thermal sensors [1]. As a starting point the thermal network model of a spacecraft is used. Different nodes with different temperatures define parts of the spacecraft, the interaction between the nodes (the links) is defined by the laws of thermodynamics. Heat transfer either can be convection or radiation. This defines a complex network and we have to decide which nodes should be chosen in order that the network becomes observable, which is equivalent to put thermal sensors onboard of the spacecraft. This choice is neither unique nor does there exist a closed formula to obtain an optimal choice.
The method proposed is particular attractive in those network whose state and parameters can be estimated by the filter using a minimal amount of readings. The relation between the network topology and this minimal number is therefore an issue strictly related to the observability of the system which is here approached using graph theory. |
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System and sensor uncertainties
are taken into account in the lumped parameter network (LPN) modeling of the thermal
system and a nonlinear dual filter is run on the resulting
stochastic model. In the dual filtering configuration
[2] the states and the parameters of
a dynamic system are estimated simultaneously in
an alternating optimization fashion. To cope with
the strong nonlinearities of the resulting thermal
network we propose to use the "unscented" extension
of the well known Kalman filter [3, 4]. The
main advantage of the dual filtering based method
applied to the thermal network is the possibility
of detecting variations in the thermal properties of
the spacecraft as a result of variations of its physical
properties together with a complete thermal
mapping of the system. Events such as faults can
be detected by the dual filter as well as new values
of system parameters (e.g. radiative couplings) that
result from a variation of the spacecraft geometry
(e.g. from the deployment of antennas, solar panels,
etc.). Finally, the system could be employed as a
virtual sensor able to identify anomalous behaviors
of a possible faulty physical sensor.
