Accession Number:

ADA558199

Title:

Methane Dual Expander Aerospike Nozzle Rocket Engine

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

Report Date:

2012-03-22

Pagination or Media Count:

131.0

Abstract:

The Air Force Institute of Technology AFIT, working to meet requirements set by the Air Force Research Laboratorys Next Generation Engine NGE initiative, is developing upper stage rocket models. The current path of investigation focuses on combining a dual expander cycle with an aerospike nozzle, or the Dual Expander Aerospike Nozzle DEAN using methane fuel. The design process will rely heavily on AFITs previous work, which focused on the development of tools for and the optimization of a hydrogenoxygen DEAN engine. The work outlined in this paper expands the existing research by substituting methane for hydrogen. The targets derived from the NGE program include a vacuum specific impulse of 383 seconds, 25,000 lbf of thrust, and a thrust to weight ratio of 108. NASAs Numerical Propulsion System Simulation was used in conjunction with Phoenix Integrations ModelCenter to optimize over several parameters to include OF ratio, thrust, and engine geometry. After thousands of iterations over the design space, the selected MDEAN engine concept has 349 s of Isp and a thrust to weight ratio of 120. The MDEAN was compared to liquid hydrogen technology, existing methane technology, and the NGE goals.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE