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Analytical
Engineering
Background
Rocket Propulsion
Satellite Propulsion
Fluid Dynamics
Thermodynamics
Structure Mechanics
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Rocket Propulsion Engineering and Analysis.
Rocket engine design and engineering activities performed by the Astrium propulsion team at Ottobrunn, Germany.
The
Team
The expertise of Ottobrunn's rocket propulsion team is applied
to the engineering, design, analysis and performance prediction of liquid
propellant rocket engines and combustion chambers. This experience has
been gathered over a period exceeding 40 years and has supported the well
proven and successful design of rocket
engines, rocket thrust chambers and associated systems covering a range
of different propellants including monopropellants, earth storable hypergolic
propellants, cryogenic propellants and more recently, alternative 'green'
and hydrocarbon propellants.
Typical
Activities
Typical activities of the propulsion team include:
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Design
and optimisation of rocket engine combustion chamber profile and nozzle
cooling. Nozzle flow and performance analysis. Hydraulic characterisation
of cooling channels (flow checks). Combustion chamber simulation and associated
heat transfer analysis. Production monitoring and assessment of design
deviations. Upgrade development and evolution of analytical and prediction
models, software and tools. Characterisation of thrust chamber operating
behaviour. Development of multiphase flow codes within national and international
technology programmes under ESA/ESTEC contracts and R & D projects.
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Rocket
engine test analysis of injection head and ignition, combustion chamber
efficiency and cooling. Design of injection component set-up and configuration.
Hydraulic flowcheck characterisation of elements. Hydraulic design of
dome, distribution and manifolds. Design of ignition systems. Evaluation
and assessment of flow checks for injection elements and cooling channels.
Characterisation of thrust chamber operating behaviour. Definition of
test requirements. Rocket engine flight test analysis and evaluation.
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Service
life analyses. Improvement of service life model (database). Characterisation
and analysis of crack propagation. Thrust chamber operating characterisation
(Operating envelope programme).
Experience
HM7 engine, Vulcain engine, Vulcain II engine, Aestus engine, RS72
engine, Vinci engine, 22N thruster, 400N AOCS thruster, NTP, TEHORA, ASTRA,
Tekan, GSTP II, etc.
Tools
A number of tools have been developed
and are constantly being refined to support the design, analysis, modelling
and performance prediction of rocket engines. These include tools for rocket
engine combustion flow analysis, computation of thrust chamber flow phenomena,
determination of heat transfer processes in rocket engine thrust chambers,
characterisation of thrust chamber operational behaviour and the determination
of heat transfer processes in rocket engine thrust chambers. The
experienced use of these tools have repeatedly verified the accuracy of
their predictions from the actual test and service life of rocket engines.
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ROCFLAM
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ROCFLAM:
ROcket Combustion FLow Analysis Module.
A Multiphase Navier-Stokes code for the computation of flow phenomena
in thrust chambers using storable propellant combinations such as hydrazine/N2O4
and MMH/N2O4. Developed under ESA/ESTEC Contract for the simulation
of film-cooled engines.
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CryoRoc
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CryoROC:
Cryogenic ROcket Combustion. A multiphase Navier-Stokes
code for the computation of flow phenomena in thrust chambers using
cryogenic oxygen and hydrogen. A derivative of the ROCFLAM code, linked
with RFCS. The procedure allows the exact determination of heat transfer
in regeneratively cooled thrust chambers. The code also enables an assessment
of the impact of transpiration cooling and combustion chamber cracks
on the performance of rocket engines and the prediction of solid particle
acceleration in kinetically compacted cold gas injection nozzles as
used for the Vulcain 2 and VINCI developments.
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RCFS
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RCFS:
Regenerative Coolant Flow Simulation. A
programme for the determination of heat transfer processes in rocket
engine thrust chambers based on advanced Nusselt correlation's. Used
for hypergolic and cryogenic propellant combinations, the programme
is a partial module of CryoROC - for computation of heat transfer of
the cooling agent, and partial module of Envelope - for the determination
of heating-up. Used for Vulcain 2 and VINCI developments.
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Envelope
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| Envelope: A Programme for the characterisation
of the VINCI thrust chamber operational behaviour used for the VINCI
expander cycle. Development of pressure loss in the VINCI cooling
cycle. |
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Life
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Life:
Tool for the service life estimation of rocket combustion chambers,
considering low cycle fatigue and creeping damage; used for RS-72, Vulcain
2 and VINCI developments.
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ETES
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ETES: Programme
for the complete evaluation of engine tests. |
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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