Satellite propulsion modeling with ecosimpro: comparison between simulation and ground tests

This paper documents the work performed for the implementation and validation of a satellite propulsion subsystem modeling library ESPSSv2.0 (European Space Propulsion System Simulation) within the existing tool EcosimPro® and using test cases relevant for space applications. EcosimPro® is a physical simulation modeling tool that is an object-oriented visual simulation tool capable of solving various kinds of dynamic systems represented by writing equations and discrete events. It can be used to study both steady states and transients. The object oriented tool, with the propulsion library allows, for example, the user to draw (and to design at the same time) the propulsion system with components of that specific library with tanks, lines, orifices, thrusters, and tees. The user enhances the design with components from the thermal library (heaters, thermal conductance, and radiators), from the control library (analogue/digital devices), from the electric library, etc

A Satellite Platform Modelling with EcosimPro : Simulation and Ground Tests Comparison

edition: 2status: publishe

Dust Particle Erosion during Mars Entry

The ablator Norcoat Liege is baselined as thermal protection material for the European probe EXOMARS planned to land on Mars in 2016. During some Martian years, for unknown reasons, local dust storms may grow to global encircling storms in only a few days. Accordingly, any probe entering directly from a hyperbolic approach has to cope with the risk of flying in a severely dust loaded atmosphere. In the frame of two studies in contract to ESTEC and CNES, particle erosion of Norcoat Liege has been investigated. A systematic arc-jet test program supported by trajectory and flow field simulations has been performed. In this paper the results of these investigations are summarized and the influence on heat shield design is assessed

Space debris reentry prediction and ground risk estimation using a probabilistic breakup model

International audienceWhile the number of artificial space object re-enter the Earth atmosphere daily, predicting the reentry of a space debris remains an open problem. The reentry prediction is a multi-physics problem involving aerodynamics computations in rarefied and continuum flow, heat transfer calculations and structiral breakup predictions. Additionally, numerous uncertainties coming from unknown initial flight conditions, material properties or uncalibrated model parameters affect oru ability to make acurate predictions. In this wrk, we propose an original reentry prediction framework that associates deterministic physical solvers with a stochastic breakup model and uncertainty quantification tools to make robust reentry predictions and a statistical estimate of the impact location. Our method is able to predic breakup distributions and ground impact locations efficiently using simplified but robust models at reasonable computational cost. This framework is used to predict the reenty of Upper Stage deorbited from a GTO orbit