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NASA NTRS · 20180002607

Project NEO Specific Impulse Testing Solutions

Baffa, Bill
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Abstract

The Neo test stand is currently configured to fire a horizontally mounted rocket motor with up to 6500 lbf thrust. Currently, the Neo test stand can measure flow of liquid propellant and oxidizer, pressures residing in the closed system up to the combustion chamber. The current configuration does not have the ability to provide all data needed to compute specific impulse. This presents three methods to outfit the NEO test fixture with instrumentation allowing for calculation of specific impulse.

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Baffa, Bill. 2018-04-18. Project NEO Specific Impulse Testing Solutions. https://ntrs.nasa.gov/citations/20180002607

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