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Linear pyrometer for investigations of thermal protection systems

1993; American Institute of Aeronautics and Astronautics; Volume: 7; Issue: 1 Linguagem: Inglês

10.2514/3.11573

1533-6808

Otto Loesener, Monika Auweter‐Kurtz, M. Hartling, Ernst Messerschmid,

Spacecraft Design and Technology

Simulated re-entry tests of reusable thermal protection systems for spacecraft are being conducted in an arc-heated, high-enthalpy wind tunnel. The surface temperature is usually measured by remote pyrometers. Since the material is heated by the radiating plasma, signal disturbances are present when measuring through the plasma. Furthermore the normal spectral emittance is subject to changes, depending on plasma conditions. In order to avoid these drawbacks a new kind of pyrometer for the measurement of the rear side temperature was designed. This article describes the design and the application of the miniaturized pyrometer in the plasma wind tunnel