9th International Workshop on Radiation of High Temperature Gases for Space Missions

Session

Numerical Simulations

13 Sept 2022, 09:00

Auditório (Biblioteca Municipal - Santa Maria - Azores -Portugal)

Conveners

Numerical Simulations

• Christian Mundt
• Louis Walpot (ESA/TEC-MPA)

Numerical Simulations

• There are no conveners in this block

98. Simulation of radiating non-equilibrium flows during atmospheric entries using a gas kinetic simulation code

Julian Beyer (University of Stuttgart)

13/09/2022, 09:00

To protect space vehicles of the extreme heat loads during atmospheric entries, appropriate heat shields are necessary. For the higher entry speed class of missions, their design requires the characterization of the both the incident radiative heat flux and associated uncertainties, as well as the impact of radiative cooling in the flow field. An accurate prediction of these properties is also...

115. Assessment of CFD Capabilities of Various In-House Solvers for Modeling Argon Plasma MHD Experiments

Vatsalya Sharma

13/09/2022, 09:25

Atmospheric entry into a target planet is a critical phase for space missions as the spacecraft must face harsh conditions involving thermal loads in the order of Megawatts. During the entry, the atmospheric gas dissociates and (partly) ionizes. The resulting plasma sheath subjects the spacecraft to high heat fluxes and leads to communication blackout as well. Since both aspects can compromise...

78. Numerical investigation of hypersonic aerothermodynamics over a double-cone

Dr Davide Ninni (Politecnico di Bari)

13/09/2022, 09:50

Space exploration has become a stronghold in aerospace engineering. Understanding the dynamic behind hypersonic flows is crucial for the design of thermal protection systems of space vehicles. The extremely high flight velocities of such bodies while entering in the atmosphere induce the formation of strong shock waves in front of them: in the downstream region, non equilibrium takes place due...

87. Coupling of Radiation and Spallation of Carbon Ablators in a Plasma Wind Tunnel

Felix Grigat (Institute of Space Systems, HEFDiG)

14/09/2022, 11:00

Ablative thermal protection systems (TPS) reduce the heat flux on a spacecraft during atmospheric entry through a number of effects. Modern materials consist of a porous carbon preform which is infiltrated with phenolic resin. During reentry, the resin inside the material pyrolyses which leads to the outflow of cold pyrolysis gases towards the surface and ultimately into the boundary layer and...

100. Non-equilibrium modeling of inductively coupled plasma discharges

Mr Sanjeev Kumar (University of Illinois at Urbana-Champaign)

14/09/2022, 11:20

Background of the study : The windward side of a re-entry vehicle needs to be protected by a heat shield, made of advanced thermal protection materials (TPMs) to overcome the tremendous amount of heat loads during planetary entry. Because in-flight testing of new TPMs is prohibitively expensive, the extreme heat loads imposed on a thermal protection shield during hypersonic re-entry are...

102. Multi-Fidelity Modeling Framework for High-Temperature Gas Radiation

Sung Min Jo

14/09/2022, 11:40

Introduction
During atmospheric entry flights, a substantial amount of radiative heat transfer occurs around surface of spacecraft and this affects the success of designed mission. The radiative heat transfer roughly depends on the fourth power of governing temperature which implies the accurate representation of it is one of the crucial components to design a thermal protection system...

129. State to state dissociation rates of H2 by collision with H and He using the QCT method

Dr Joao Vargas (King Abdullah University of Science and Technology, Physical Science and Engineering Division Mechanical Engineering Programme, Clean Combustion Research Center)

14/09/2022, 12:00

The latest decadal planetary science survey recommended an orbiter and probe mission to Uranus [1]. Set to launch within the decade, now is an opportune moment to review kinetic data relevant for the design of this mission. The dissociation rates of molecular hydrogen are relevant for more accurate assessment of the convective heating experienced by an entry probe. Furthermore, in the last 20...

130. Modelling of hot plumes with particles for improved launcher applications

Yannick Hoarau (ICube, Université de Strasbourg)

14/09/2022, 12:20

Europe’s access to space today relies primarily on the Ariane 5 family of heavy lift launchers and the Vega launcher for small payloads. The successful development of these launchers depends on finding solutions in the critical and challenging areas of propulsion and aero-thermodynamics, which are the key elements of any launch vehicle. In the past, aerodynamic and aero-thermodynamic...