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Title: Development and testing of a nitrous-oxide/ethanol bi-propellant rocket engine

Conference · · AIAA Journal of Propulsion and Power
DOI:https://doi.org/10.2514/6.2016-5092· OSTI ID:1492388
 [1];  [1];  [2];  [2];  [1]
  1. New Mexico Institute of Mining and Technology, Socorro, NM (United States)
  2. Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
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Here, a liquid bi-propellant rocket engine and supporting infrastructure has been de-signed, constructed, and tested at New Mexico Institute of Mining and Technology ina cooperative effort with Sandia National Laboratories. The modular engine designconsists of a head-end fuel-oxidizer injector, gaseous H2/02 torch ignitor, combustionchamber, and nozzle modules. The robust modular design allows for rapid config-uration changes and component replacement if damaged in testing.

Research Organization:
Sandia National Lab. (SNL-NM), Albuquerque, NM (United States)
Sponsoring Organization:
USDOE National Nuclear Security Administration (NNSA)
DOE Contract Number:
AC04-94AL85000
OSTI ID:
1492388
Report Number(s):
SAND-2018-10844J; 668354
Journal Information:
AIAA Journal of Propulsion and Power, Conference: 52nd AIAA/SAE/ASEE Joint Propulsion Conference, AIAA Propulsion and Energy Forum, (AIAA 2016-5092) , Salt Lake City, UT, 25-27 July 2016
Country of Publication:
United States
Language:
English

References (6)

Seedless Velocimetry Measurements by Schlieren Image Velocimetry journal March 2011
Development of a Laboratory-Scale System for Hybrid Rocket Motor Testing journal January 2011
Fuel Options for Next-Generation Chemical Propulsion journal January 2012
Nitrous oxide as a rocket propellant journal March 2001
Effects of Injector Design on Combustion Stability in Hybrid Rockets Using Self-Pressurizing Oxidizers conference July 2014
Schlieren and Shadowgraph Techniques book January 2001

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