Solid Propellant Microthruster Design for Nanosatellite Applications

A solid propellant microthruster is investigated and is designed with conventional materials and processes with a future plan for microelectromechanical systems fabrication. The proposed solid propellant microthruster design will be demonstrated onboard the YUsend-1 satellite. The YUsend-1 prototype...

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Bibliographic Details
Published in:Journal of propulsion and power 2011-11, Vol.27 (6), p.1288-1294
Main Authors: Sathiyanathan, Kartheephan, Lee, Regina, Chesser, Hugh, Dubois, Charles, Stowe, Robert, Farinaccio, Rocco, Ringuette, Sophie
Format: Article
Language:English
Subjects:
Chambers
Design engineering
Nanosatellites
Pendulums
Solid propellants
Sonics
Supersonic nozzles
Thrust
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Summary:A solid propellant microthruster is investigated and is designed with conventional materials and processes with a future plan for microelectromechanical systems fabrication. The proposed solid propellant microthruster design will be demonstrated onboard the YUsend-1 satellite. The YUsend-1 prototype solid propellant microthruster consists of 36 individual Ministers with chambers 1.5 mm in diameter and approximately 3.6 nun in length. The propellant is a formulation of glycidyl azide polymer and ammonium perchlorate with decreased viscosity for easy chamber filling. Impulse and thrust values are determined using a ballistic pendulum for nozzleless, sonic, and supersonic nozzle configurations. Throat diameters are approximately 600-700 mm. In all three configurations, ignition is successful. For the sonic and supersonic nozzles, a concentrated plume is visible for a burn duration of 1.3-1.6 s, resulting in pendulum displacements of 1.4-1.9 mm. The observed thrust range is 0.18-0.29 inN, which is consistent with existing solid propellant microthruster designs.
ISSN:0748-4658
1533-3876
DOI:10.2514/1.B34109