S

Sebastien Reichstadt

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Co-Founder & Head of Propulsion
Mérignac, Nouvelle-Aquitaine, France

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Jobs verified_user 0% verified
  • The Exploration Company
    Co-Founder & Head Of Propulsion
    The Exploration Company
    Apr 2026 - Current (7 months)
  • The Exploration Company
    Co-Founder & Propulsion Senior Technical Advisor
    The Exploration Company
    Dec 2024 - Apr 2026 (1 year 5 months)
  • The Exploration Company
    Co-Founder & Lead Propulsion System
    The Exploration Company
    Sep 2021 - Dec 2024 (3 years 4 months)
  • Reaction Engines
    Rocket SME & Technology Coordinator
    Reaction Engines
    Dec 2019 - Aug 2021 (1 year 9 months)
  • ArianeGroup
    Liquid Propulsion System Technological Coordinator
    ArianeGroup
    Jan 2018 - Nov 2019 (1 year 11 months)
    - Insure consistency between launcher needs and liquid propulsion systems development
    - Support subsystems technology orientation in consistency with liquid propulsion systems needs
    - Propose technology policy by identifying key differentiating technologies to be mastered by the company
    - Follow the performance of R&T projects to measure progress of technology maturation
  • ArianeGroup
    Propulsive System Expert
    ArianeGroup
    Jul 2016 - Nov 2019 (3 years 5 months)
    - Ensure the support to the built and the validation of the technical deliveries of the department.
    - Animate and develop our expert network, to reinforce the knowledge management of our department specialties
    - Reinforce our technical mastering as System in developing the transverse view jobs/products in-house of the department and with our interfaces
  • ArianeGroup
    Vulcain 2.1 Propulsion System Functional Manager
    ArianeGroup
    Jul 2016 - Oct 2017 (1 year 4 months)
    Conduct the development of the Lower Liquid Propulsion System (LLPS) for the next European Launcher Ariane 6 in the field of functional design :
    - Ensure consistency between engine, propulsive system and launcher development logic
    - Refine project scope and sequencing in consistency with higher level planning
    - Organize the planning of functional activities
    - Monitor the progress of activities (technical maturity, planning and costs)

    Coordinate Ariane 6 activities within the Propulsive System Department such as :
    - Engine and propulsive system functional design
    - System functional models development
    - Functional tests analyses
    - Firing tests preparation and analyses
  • Safran
    Engine System Expert
    Safran
    Sep 2015 - Jun 2016 (10 months)
  • Snecma
    Vulcain 2.1 Propulsion System Functional Manager
    Snecma
    Apr 2015 - Jun 2016 (1 year 3 months)
    Conduct the development of the Lower Liquid Propulsion System (LLPS) for the next European Launcher Ariane 6 in the field of functional design :
    - Ensure consistency between engine, propulsive system and launcher development logic
    - Refine project scope and sequencing in consistency with higher level planning
    - Organize the planning of functional activities
    - Monitor the progress of activities (technical maturity, planning and costs)

    Coordinate Ariane 6 activities within the Propulsive System Department such as :
    - Engine and propulsive system functional design
    - System functional models development
    - Functional tests analyses
    - Firing tests preparation and analyses
  • Snecma
    Upper Stage Engine Design Engineer
    Snecma
    Dec 2012 - May 2015 (2 years 6 months)
    - Justify engine functional design wrt to upper-level performance requirements and design rules (Preparation of engine CDR - held in November 2014)
    - Define steady-state objectives for development and qualification engine campaigns
    - Break down functional requirements to subsystems
    - Carry out impact studies wrt engine or subsystems design evolution
    - Identify and manage engine critical items

    Snecma expert on functional design
    - Review member on engine or subsystem designs
    - Definition of new methodologies to be introduced in design justification loop
  • Snecma
    Health Monitoring System (HMS) Delivery Manager
    Snecma
    Nov 2011 - Dec 2012 (1 year 2 months)
    - Coordinate foreign contractors activities
    - Manage budget and planning in coherence with project milestones
    - Rally internal actors around the project
  • F
    First Stage Engine Design Engineer
    Mar 2011 - Dec 2012 (1 year 10 months)
    Technical missions :
    - Justify engine functional design with respect to upper-level performance requirements and design rules (Preparation of engine PDR - held in October 2012)
    - Establish engine functional development logic
    - Define demonstration objectives for engine firing tests campaign
    - Break down functional requirements to subsystems
    - Carry out impact studies wrt engine or subsystems design evolution
    - Identify and manage engine critical items

    Project missions :
    - Track and schedule engine functional and HMS (Health Monitoring System) studies
    - Manage budget and schedule
    - Participate in weekly internal project meeting and quaterly meeting with ESA client
    - Ensure internal
  • Snecma
    Propulsion System Engineer
    Snecma
    Sep 2008 - Mar 2011 (2 years 7 months)
    - Improve engine steady-state model for HM7b engine through update of subsystems characteristics and model tuning methodology
    - Support validation of PROOSIS simulation platform for VINCI steady-state engine model and tools
    - Develop next generation methods to characterize VINCI engine and subsystems operating domains during test campaigns and flights
    - Ensure technology watch on performance identification methods
    - Support VINCI engine development campaigns on steady-state engine performance aspects (forecast simulations, post-test analyses, risk analysis studies, test profile definitions...)
  • ONERA The French Aerospace Lab
    Research Engineer on dual-mode ramjet
    ONERA The French Aerospace Lab
    Nov 2007 - Aug 2008 (10 months)
    - Forecast combustion chamber performances on the engine operating domain through 3D reactive computations
    - Validate engine performances with respect to functional requirements
    - Contribute to ground-to-flight transposition methodology in preparation of engine firing tests
  • ONERA
    PHD Student
    ONERA
    Nov 2003 - Oct 2007 (4 years)
    Research subject : Study of mixing and combustion processes inside a research ramjet combustor

    PhD Supervisor : Pascal BRUEL (LMA - Université de Pau et des Pays de l'Adour)

    ONERA Management : Nicolas BERTIER & Arnaud RISTORI (DEFA)

    - Characterize non-reactive flow inside an atmospheric pressure model rig through intruse measurement
    - Characterize reactive flow (velocity and fluctuation) through PIV assembly
    - Implement and evaluate micro-mixing combustion models
    - Evaluate the ability of Large Eddy Simulations (LES) to forecast flow characteristics in non-reactive and reactive configuration (global performances and comparisons with available measurements)

    -
  • SNECMA Moteurs
    Engineering Student
    SNECMA Moteurs
    Sep 2001 - Aug 2002 (1 year)
    - Identify most representative turbulence and combustion models for injector reactive computations (comparisons with tests measurements or FLUENT simulations)
    - Validate CFD code N3S-Natur on combustion and injection processes
    - Develop a CFD computation methodology to characterize performances of new generation injectors (design optimization support). Main constraints : CFD novice users and results to be provided within a day
    - Forecast gas generator behaviour in nominal and deviated (leaks) conditions
Education verified_user 0% verified
  • U
    Doctor of Philosophy (PhD, Energetics, Fluid Mechanics
    Université de Pau et des Pays de lAdour
    Jan 2004 - Dec 2007 (4 years)
  • Pierre and Marie Curie University
    Master of Advanced Studies, Combustion, Fluid Mechanics, Thermodynamics, Acoustics
    Pierre and Marie Curie University
    Jan 2002 - Dec 2003 (2 years)
  • Ecole supérieure des Techniques aéronautiques et de Construction automobile
    Master of Science (MSc, Aeronautics, Propulsion, Fluid Mechanics
    Ecole supérieure des Techniques aéronautiques et de Construction automobile
    Jan 1997 - Dec 2003 (7 years)
    Six-month internship at ONERA
    Subject : Comparison Between Numerical Computations and Experiments for a Research Ramjet Combustor

    One-year internship at SNECMA Moteurs Vernon
    Subject : Computational simulations of a new generation gaz-generator for a rocket motor.
Projects (professional or personal) verified_user 0% verified
  • A
    Ariane 6
    Oct 2013 - Current (13 years 1 month)
  • A
    Ariane 5 ME (Mid-life Evolution)
    Dec 2012 - Dec 2014 (2 years 1 month)
  • F
    Future Launcher Preparatory Program - SCORE-D
    Mar 2011 - Dec 2012 (1 year 10 months)
  • A
    Ariane Consolidation and Evolution Preparation
    Sep 2008 - Dec 2009 (1 year 4 months)
Publications verified_user 0% verified
  • t
    Fault Detection and Isolation for a Rocket Engine Valve
    th IFAC Symposium on Automatic Control in Aerospace
    Jan 2013
    A fault detection and isolation scheme based on Hinf. theory is presented for an engine actuator valve. The simulation model of the engine corresponds to a staged combustion rocket engine used to study the applicability and capabilities of FDI techniques towards real-time validation in an engine test-bench. The obtained FDI design is capable of detecting and estimating (biases, ramps and including oscillatory) fault for the selected valve in a robust manner. The design methodology allows reuse of the design process for other valves with minor modifications and tuning.
  • A
    System engineering presentation of the European staged combustion demonstrator SCORE-D
    AAAF ESA CNES Space Propulsion
    May 2012
    Authors : I. Jeaugey, J. Montheillet, S. Reichstadt, A. Ghouali, G. Dantu The intent of this publication is to provide an overview of the system engineering of the European staged combustion demonstrator SCORE-D designed in the frame of the ESA Future Launchers Preparatory Programme (FLPP). The primary goal is to master a staged combustion engine system. In addition to testing a staged combustion demonstrator, a strong focus is placed on improving the maturity level of technologies which will become increasingly important for space propulsion such as health monitoring and the all-electric engine control. Throughout the design and testing of SCORE-D, introducing new technologies and monitoring the progress of their maturity is a prime object
  • C
    Comparison of numerical methods and combustion models for LES of a ramjet
    CR Mécanique
    Jan 2009
    Authors : A. Roux, S. Reichstadt, N. Bertier, L. Gicquel, F. Vuillot and T. Poinsot Ramjets are very sensitive to instabilities and their numerical predictions can only be addressed adequately by Large Eddy Simulation (LES). With this technique, solvers can be implicit or explicit and handle structured, unstructured or hybrid meshes... Turbulence and combustion models are other sources of differences. The impact of these options is here investigated for the ONERA ramjet burner. To do so, two LES codes developed by ONERA and CERFACS compute one stable operating condition. Preliminary LES results of the two codes underline the overall robustness of LES. Mean flow features at the various critical sections are reasonably well predicted by both co
  • t
    PIV and gas sampling analysis measurements for fuel-to-air mixing study inside a research ramjet combustor
    th International Symposium on Flow Visualization
    Jul 2008
    Authors : A. Ristori, S. Reichstadt, C. Brossard, G. Heid An ongoing research ramjet program initiated at ONERA under support of DGA (French ministry of Defence) aims to improve methodology for ramjet combustion chamber design and tuning by using validated CFD codes. A transparent model rig was used for aerodynamic tests with air flows at atmospheric pressure and room temperature. Among the various mechanisms that are controlling the development of the combustion processes inside the combustor, the mixing is certainly one of the most crucial as far as stability or efficiency are concerned. The work presented in this paper is addressing the characterization, in absence of combustion, of the turbulent flow velocity and scalar fields associate
  • t
    Towards LES of mixing processes inside a research ramjet combustor
    th International Symposium on Airbreathing Engines
    Sep 2007
    Authors : S. Reichstadt, N. Bertier, A. Ristori, P. Bruel In 1995, ONERA initiated a research program on ramjet developments with the support of the DGA, Ministry of Defense. The targeted objective of this program is to improve the ramjet combustion chamber design by using both experiments and validated CFD codes. The present study is mainly devoted to the analysis of the fuel-to-air mixing properties in the combustion chamber of a generic research ramjet combustor. Accordingly, the first objective of this work was to characterize, in absence of combustion, the turbulent flow velocity and scalar fields associated to the mixing between the fuel and air. Thus, particle image velocimetry (PIV) and gas sampling analysis are the two techniques t
  • t
    Detailed characterization of the reacting one-phase and two-phase flow inside a research ramjet
    th International Symposium on Airbreathing Engines
    Sep 2005
    Authors : A. Ristori, G. Heid, C. Brossard, S. Reichstadt A research ramjet program has been initiated at ONERA with the support of DGA with the aim of improving methodology for ramjet combustion chamber design and tuning by using validated CFD codes. The approach used was to design and manufacture a specific ramjet model in order to setup an experimental database for nonreacting and reacting flows; the final aim is to validate models and CFD codes in order to have an accurate numerical tool able to predict steady performances of ramjet combustors. Two three-dimensional ramjet research combustors have been specifically designed to experimentally simulate flows inside real solid-propellant Ducted Rockets (SDR) or Liquid Fueled Ramjet (LFRJ)
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