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Analytical
Engineering
Background
Rocket Propulsion
Satellite Propulsion
Fluid Dynamics
Thermodynamics
Structure Mechanics
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Space Propulsion Thermodynamic Engineering
and Analysis.
Rocket engine and space propulsion engineering and analysis performed
by Astrium thermodynamics team at Ottobrunn, Germany.
Programme Experience
The thermodynamics team have extensive
experience and achievements associated with the analysis and engineering
of numerous international programmes, including:
Rocket Engines & Satellite Thrusters:
 VINCI
(Ariane 5 upper stage).
Aestus
II/RS72
(Ariane 5 upper stage/upper stage Delta class).
Aestus (Ariane 5 upper stage).
Vulcain
2 (Ariane 5 core stage).
Vulcain (Ariane 5 core stage) Elite, ANE (Vulcain technology programmes).
Bipropellant
thrusters (10N, 400N, 22N, MSG) (satellite attitude control).
Hydrazine
thrusters.
Ion thrusters
(Artemis IPP).
Satellites:
IntelSat (antennas, solar generator).
InSat (satellite, antennas).
SinoSat (satellite, antennas).
Astra 2B (antennas).
Huygens (research capsule for landing on Jupiter's satellite Titan
in 2004).
MIPAS (satellite, antennas).
ISO (Cryostat, research satellite).
Meteosat, Meteosat II (satellite, antennas, propulsion system, attitude
control).
ARPK, RVSE (docking system, test on Space Shuttle flight STS84).
Seviri (satellite, antennas).
RTOF (measurement of particles in a comet's tail).
Solar Generators:
Eutelsat II.
Spacebus 3000.
Eurostar 3000.
Orion 2.
Reusable and Manned Space Flight:
Hermes (space shuttle for use on Ariane 5).
Saenger (two-stage space transport system, reusable).
CRV/CTV (high technology re-entry capsule system).
Festip (technology programme for reusable space transport vehicles).
MSTP (technology programme for manned space transport).
Tools
A variety of well proven tools are used in support of computations into
heat transfer, radiation exchange, geometric modelling, finite element
modelling, etc, include the following:
| ESATAN
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| A nodal programme for stationary/transient
heat transfer including thermal conduction and radiation, no geometry
modelling (lumped parameters). Applied in all satellite and solar generator
projects. Also applied to rocket engines, in particular as a reduced
model for complex configurations, e.g. at integrated stage / engine level. |
| THERMICA
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| A radiation exchange programme: delivers
radiation flows/view factors for ESATAN models. Calculated by means of
a Monte Carlo simulation. Applied in all computations using ESATAN node
models where radiation is important, in particular satellites and solar
generators. |
| I-DEAS
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| Geometric modelling with CAD properties and
partial interfaces to NASTRAN and CATIA, via Gtran/GRad to THERMICA.
Used for 3-D or axial symmetric finite element modelling of engine components,
detailed models of satellites and solar generators. |
| I-DEAS
/ TMG |
| THERMAL-MODEL-GENERATOR
Integrated definition, computation and post-processing of an FE model
generated by I-DEAS. Simplified radiation (Gebhard factors). 3-D as well
as axial symmetric models are possible (incl. radiation). Used for all
thermal applications with FE modelling |
| I-DEAS
/ ESC |
| ELECTRONIC-SYSTEM-COOLING
Structure/flow coupling for FE model thermal calculations having very
low flow speeds. Used for thermal analysis of electronic components with
convection cooling. |
| Gtran
/GRad |
| Interface programme for data exchange between
I-DEAS and THERMICA, for the generation of model geometry and thermal
properties in I-DEAS and the computation of radiation with THERMICA.
Used in all thermal calculations using I-DEAS geometry models in order
to use radiation flows in ESATAN by means of THERMICA, i.e. all satellite
and solar generator projects |
Contact for Further Information
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If
you require more detailed information on any of our products or services,
then please contact
us, indicating your particular areas of interest or intended application.
Your enquiry will receive our best attention.
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