Investigations were performed to obtain experimental data on the structure, composition, contaminants and impingement of plumes particularly from bipropellant thrusters burning nitrogen tetroxide (NTO) and monomethyl hydrazine (MMH) propellants that would be useful in improving the determination of plume effects on spacecraft performance. The experiments were conducted with real engine firings in the thrust range between 5 and 66 Newton in the HAMBURG high vacuum test facility using different measurement techniques such as mass spectrometry, heat flux sensors, short time photography, optical scatter and surface resistivity measurement and others. Results and conclusions were presented concerning the nature of the contaminant depositon process on different surface materials and concerning the surface properties change particularly in connection with optical transmission and scatter effects. The experimental results are suitable as INPUT DATA for theoretical computer programs of CONTAM/SURFACE:
Exhaust plume effects of small thrusters on spacecraft surfaces
Einfluesse der Abgasfahne von kleinen Schubraketen auf die Oberflaechen von Raumfahrzeugen
AIAA-Papers ; Jun ; 1-11
1987
11 Seiten, 12 Quellen
Conference paper
English