Ingénierie et Systèmes Avancés

Transcription

1 Ingénierie et Systèmes Avancés Technical Capabilities Bât Cheminnov, Site ENSCPB, 16 Avenue Pey Berland Pessac - France Ph. Reynier - 5 Nov

2 ISA Ingénierie et Systèmes Avancés (ISA) is a limited company founded in April 2006 through a partnership between: - Ph. Reynier, managing director, and majority shareholder, with a strong R&D background started in the academic and re-inforced by 8 years of international experience at DLR (Germany) and ESA-ESTEC (European Space Agency, The Netherlands); - Fluid Gravity Engineering Ltd (UK), software support and minority shareholder. The company is located in the technical support centre of the ENSCPB in the campus of the University of Bordeaux. Ph. Reynier - 5 Nov

3 Activities The activities of the company are oriented as follows: - Atmospheric entry of spacecraft; - Cryogenics; - Physical modeling and computational fluid dynamics. The in-house software allow the investigation of the main phenomena associates to re-entry. The capabilities of the available tools cover the following domains: - Fluid Mechanics; - Thermal engineering (ablation, cryogenics); - Electromagnetism; - Plasma radiation. Ph. Reynier - 5 Nov

4 Applications A significant experience is already available in the following areas: - Trajectory analysis; - Transition to turbulence; - Blackout; - Radiation; - Ablation; - CFD; - Debris assessment; - Passivation of launcher propellant tanks; - Cryogenics; - Propulsion. Ph. Reynier - 5 Nov

5 Ablation Most of the thermal protection systems are made of ablative material. Ablation has a strong impact on heat-flux and the prediction of material recession is necessary for sizing the TPS. The prediction on heat-flux accounting for ablation can be achieved using a blowing condition at the surface. TPS recession calculations are available based on 1D approaches. Fig. : Mass fraction of C2 (from the material pyrolysis) during an high-speed Earth entry at 14 km/s. Ph. Reynier - 5 Nov

6 Aerodynamics HFK (DLR study): Development of an actuator disc in TAU code for missiles equipped with grid fins. Prediction of the missile aerodynamic behaviour. Cm-B-CFD Cm-B-Exp Cm-M-CFD Cm-M-Exp Cm alpha Ph. Reynier - 5 Nov

7 CFD A long experience in CFD acquired in several European research institutes (DLR, ESTEC, IMFT) is available. For re-entry, tools like TAU (DLR code) and TINA have been extensively used for the analysis of test facilities (SCIROCCO) and the prediction of heat-flux (EURORETURN, INTERMARSNET, IRDT, PARES). Vorticity field over IRDT cone at peak heatflux conditions. Surface pressure distribution de during IRDT re-entry. Ph. Reynier - 5 Nov

8 Cryogenics/Multiphase Experience was gained in the frame of different studies: Ariane 5 SCA tank passivation for assessing the clogging risk of vent line, and cryogenics studies for slush hydrogen production in the frame of FLPP. 20 Pressure upstream ejection ONERA EXP ESTEC CFD Tank pressure Ejection pressure at the end of a vent line for hydrazine venting into space Temperature distribution in a slush hydrogen production container. Ph. Reynier - 5 Nov

9 Debris assessment Investigation on the explosion potential of ATV during its re-entry in presence of propellant leakage. CFD is of interest for the analysis of destructive re-entry beside the use of software dedicated to debris prediction (DAS). Pressure distribution inside and outside ATV at 75 km of altitude. Pressures from trajectory analysis and CFD and chemical reaction auto-ignition limits. Ph. Reynier - 5 Nov

10 Entry A significant experience has been acquired at ESTEC on trajectories, heat-flux prediction, thermochemical non-equilibrium, catalysis, transition to turbulence, radiation, black-out and ablation for several studies and projects such as: ATV, EURORETURN, INTERMARSNET, SCIROCCO, IRDT, PARES, EXOMARS, AURORA and JEP. Fig.: Pressure distribution (left) and heat-flux (right) predicted for the entry of INTERMARSNET. Ph. Reynier - 5 Nov

11 Propulsion VULCAIN (IMFT - Fluid Mechanics Institute of Toulouse): Modelling and simulation of coaxial jets for ARIANE 5 rocket engine. Single-phase approach of spray atomisation. Turbulence modelling (standard and non linear k-ε models, RSM model). Left: Unsteady flow-field of oxygen mass fraction. Right: Average velocity flow-field. Ph. Reynier - 5 Nov

12 Radiation Radiation is investigated using the code PARADE to compute plasma emission. A weak coupling with CFD codes is available allowing the prediction of radiative heat-flux and flow-field. Fig. 4: Emitted radiative power along the stagnation line using two thermo-chemistry models. The difference is due to a slightly larger and hotter shock-layer predicted using the model already available with TINA. Ph. Reynier - 5 Nov