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

Session

Shock Tubes

13 Sept 2022, 14:30

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

74. Comparison of Equilibrium Radiation Between Shock Tube and Plasma Torch Spectroscopy for Atmospheric Pressure Air

Alex Glenn (University of Oxford)

13/09/2022, 14:30

Experimental Facilities

As a vehicle re-enters the Earth’s atmosphere, it will be travelling at hypersonic speeds through the quiescent atmospheric gas for the majority of its journey. Consequently, a bow shock forms ahead of the vehicle, creating a sudden temperature and pressure increase. The post-shock temperatures are high enough to excite internal energy modes of the gas particles and promote dissociation and...

83. Measurement of Aeroheating of Satellite Components at True Flight Total Enthalpies

James Leader (University of Oxford)

13/09/2022, 14:55

At end-of-life, satellites must be de-orbited to comply with guidelines laid out by the Inter-Agency Space Debris Coordination Committee (IADC). Disposal by direct re-entry into Earth’s atmosphere is preferred. The IADC guidelines also state that undue ground risk to people and property must be avoided, and environmental pollution should be minimised. These guidelines are intended to prevent...

79. Experimental Simulation of a Galileo Sub-Scale Model at Ice Giant Entry Conditions in the T6 Free-Piston Driven Wind Tunnel

Mr Joseph Steer (University of Oxford)

13/09/2022, 15:20

Uranus and Neptune, known collectively as the Ice Giants, are the only two planets in the solar system that are yet to be explored with a dedicated mission. Planetary entry probe missions to the Ice Giants were proposed in 2010 by NASA and ESA which prompted a resurgence of interest in experimental simulation of the aeroheating environment that would be encountered by such a spacecraft. The...

91. Numerical Model for Non-Equilibrium Shock Tube Flow

Justin Clarke (University of Oxford)

16/09/2022, 09:00

Background of the Study

Non-equilibrium phenomena can significantly change the heat transfer and aerodynamic characteristics of hypersonic vehicles. Consequently, the design of vehicles entering planetary atmospheres relies heavily on numerical calculations, and in turn these require accurate estimates of physical quantities such as rate constants and intra-molecular interaction...

112. Qualification of the European Shock-Tube for High Enthalpy Research

Mario Lino da Silva (Instituto de Plasmas e Fusão Nuclear - Instituto Superior Tecnico)

16/09/2022, 09:25

ESTHER is a two stage shock-tube. It comprises a 1.6\metre\ length and 200\milli\metre\ diameter combustion driver where He/\ce{H2}/\ce{O2} and \ce{N2}/\ce{H2}/\ce{O2} mixtures are injected by an automated gas filling system at initial pressures up to 100 bars. These mixtures are ignited through a Nd:Yag laser shooting on the back plate through a thick sapphire window, reaching final pressures...

114. HIGH-PRESSURE COMBUSTION AND QUALIFICATION OF ESTHER SHOCK-TUBE DRIVER

Ricardo Ferreira

16/09/2022, 09:50

The ESTHER shock tube is a new state-of-the-art facility at Instituto Superior Técnico to support future ESA planetary exploration missions. A high-pressure combustion chamber using a mixture of He:H2:O2 ignited by a high-power Nd:YAG laser acts as the driver. A qualification campaign was carried out with 99 shots and evaluating the effects of air:fuel ratio, filling pressure, inert gas...

93. Fast-response measurements of shock layer radiation in the High Enthalpy Shock Tunnel Göttingen (HEG)

Divek Surujhlal (DLR German Aerospace Center)

16/09/2022, 10:15

Background of the study

The development of reentry aerodynamic configurations requires examination of surface heat flux. Reentry-relevant freestream conditions are suitably generated by shock tunnels such as the High Enthalpy Shock Tunnel G{\"o}ttingen (HEG). Surface heating due to radiation at high-enthalpy stagnation conditions has been shown to comprise a significant portion of the total...