Please use this identifier to cite or link to this item: https://doi.org/10.2514/1.6893
Title: Performance prediction of a novel solid-propellant microthruster
Authors: Zhang, K.L.
Chou, S.K. 
Ang, S.S.
Issue Date: Jan-2006
Citation: Zhang, K.L., Chou, S.K., Ang, S.S. (2006-01). Performance prediction of a novel solid-propellant microthruster. Journal of Propulsion and Power 22 (1) : 56-63. ScholarBank@NUS Repository. https://doi.org/10.2514/1.6893
Abstract: A novel microelectromechanical-systems-based solid-propellant microthruster is developed for stationkeeping, attitude control, drag compensation, and orbit adjust of microspacecraft. Key to the development of the solid-propellant microthruster is the generation of extremely accurate thrust levels and impulse bits. Modeling and simulation can predict the propellant combustion and gas expansion processes inside the microthruster and then derive the microthruster performance. A computational-fluid-dynamics-based model is proposed in this paper to optimize the design by computing the subsonic/supersonic micronozzle flow and calculating the microthruster performance. Wall heat loss and boundary-layer effects, which are especially important for microscale thrusters, are highlighted in the model. Different solid propellants, microthruster geometries, and operating conditions are also evaluated. The computational-fluid-dynamics modeling results are compared with the one-dimensional thermodynamic modeling results and experimental testing data. Copyright © 2004 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
Source Title: Journal of Propulsion and Power
URI: http://scholarbank.nus.edu.sg/handle/10635/61082
ISSN: 07484658
DOI: 10.2514/1.6893
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