Variable mixture ratio performance through nitrogen augmentation [PDF]
High/variable mixture ratio O2/H2 candidate engine cycles are examined for earth-to-orbit vehicle application. Engine performance and power balance information are presented for the candidate cycles relative to chamber pressure, bulk density, and mixture
Bair, E. K., Beichel, R., Obrien, C. J.
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Development of a high power microwave thruster, with a magnetic nozzle, for space applications [PDF]
This paper describes the current development of a high-power microwave electrothermal thruster (MET) concept at the NASA Lewis Research Center. Such a thruster would be employed in space for applications such as orbit raining, orbit maneuvering, station ...
Chapman, Randall A., Power, John L.
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Optimization of Bypass Flow Introduction Angle in Dual-Throat Nozzle
Journal of Electrical SystemsThis research paper investigates the optimal angle for introducing a bypass jet in rocket engines for thrust vectoring. Numerical simulations using a finite-volume method were performed to test a range of bypass jet angles and their effect on flow performance.
openaire +1 more source
Acoustic tests of duct-burning turbofan jet noise simulation: Comprehensive data report. Volume 2: Model design and aerodynamic test results [PDF]
The selection procedure is described which was used to arrive at the configurations tested, and the performance characteristics of the test nozzles are ...
Brausch, J. F. +5 more
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Liquid oxygen/liquid hydrogen auxiliary power system thruster investigation [PDF]
The design, fabrication, and demonstration of a 111 newton (25 lb) thrust, integrated auxiliary propulsion system (IAPS) thruster for use with LH2/LO2 propellants is described.
Eberle, E. E., Kusak, L.
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Tripropellant engine study [PDF]
The potential for converting the space shuttle main engine (SSME) to a dual-fuel, dual-mode engine using LOX/hydrocarbon propellants in mode 1 and LOX/H2 in mode 2 was examined.
Kirby, F. M., Wheeler, D. B.
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Advanced engine study program [PDF]
A design and analysis study was conducted to provide advanced engine descriptions and parametric data for space transfer vehicles. The study was based on an advanced oxygen/hydrogen engine in the 7,500 to 50,000 lbf thrust range.
Black, J. R. +7 more
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Efficient solutions to the Euler equations for supersonic flow with embedded subsonic regions [PDF]
A line Gauss-Seidel (LGS) relaxation algorithm in conjunction with a one-parameter family of upwind discretizations of the Euler equations in two dimensions is described.
Dwoyer, Douglas L., Walters, Robert W.
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Computer code for single-point thermodynamic analysis of hydrogen/oxygen expander-cycle rocket engines [PDF]
This analysis and this computer code apply to full, split, and dual expander cycles. Heat regeneration from the turbine exhaust to the pump exhaust is allowed.
Glassman, Arthur J., Jones, Scott M.
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Advanced rocket propulsion [PDF]
Existing NASA research contracts are supporting development of advanced reinforced polymer and metal matrix composites for use in liquid rocket engines of the future.
Obrien, Charles J.
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