This paper describes the approach and presents some highlights obtained from a study undertaken to define scaling criteria, predicted performance, and operating parameters for electrically augmented hydrazine thrusters in the 0.5 to 5.0 newton (0.1 to 1.0 lbf) thrust range. Thruster configurations based on three distinct approaches to augmentation heat exchanger design were considered. This selection was made from the many augmented thruster designs conceived, proposed, or tested based on those design approaches that have achieved qualification/flight status or sufficient maturity to have evolved into a comprehensive advanced development program. The approach taken consisted of constructing parametric thermal models of each of the thruster configurations in order to define performance, efficiency, size, and operating parameters as a function of thrust. The models were correlated with experimental data for each of the design types in the range where such data was available. These models also permitted optimization of the configuration at selected thrust levels; this optimization was supported by design layouts in order to verify the practicality of the computer-generated sizing and dimensional data. Practical considerations concerning the integration of electrically augmented hydrazine thrusters into geosynchronous communications satellites were also addressed. These include power requirements and conditioning, thruster control, test/checkout, and instrumentation/monitoring.
Design, performance, and operational scaling criteria for electrically augmented hydrazine thrusters
Konstruktion, Leistung und Kriterien fuer die Betriebsabstufung fuer elektrisch unterstuetzte Hydrazin-Triebwerke
AIAA-Papers ; 1-5
1984
5 Seiten, 7 Bilder, 8 Quellen
Conference paper
English
Application of power augmented hydrazine thrusters
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