Development Testing of a LOX/Methane Engine for In-Space Propulsion

Judd, D. C.; Buccella, S.; Alkema, M; Hewitt, R.; McLaughlin, B.; Hart, Glenn; Veith, Eric M.

doi:10.2514/6.2006-5079

Cited by 19 publications

(11 citation statements)

References 1 publication

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“…(Note: This situation can easily be alleviated in future tests by using smaller venturis or a larger throat at the exit of the igniter.) An investigation into the cause of the difference in the experimental MRs from the target MRs focused on the inlet conditions to the venturis given in table 4 and the mass flow calculation given by equation (1). The inlet temperature to the venturi affected mass flow in both the inlet density, ρ l , and the vapor pressure, p v whereas, the controlling tank pressure only affects p i in equation (1).…”

Section: Test Resultsmentioning

confidence: 99%

“…An investigation into the cause of the difference in the experimental MRs from the target MRs focused on the inlet conditions to the venturis given in table 4 and the mass flow calculation given by equation (1). The inlet temperature to the venturi affected mass flow in both the inlet density, ρ l , and the vapor pressure, p v whereas, the controlling tank pressure only affects p i in equation (1). For example, the target density for the LOX was 1146 kg/m 3 and for the methane, it was 424 kg/m 3 .…”

Section: Test Resultsmentioning

confidence: 99%

See 1 more Smart Citation

Design, Fabrication, and Test of a LOX/LCH4 RCS Igniter at NASA

Schneider

John²,

Zoeckler³

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: Test Resultsmentioning

confidence: 99%

Section: Test Resultsmentioning

confidence: 99%

Design, Fabrication, and Test of a LOX/LCH4 RCS Igniter at NASA

Schneider

John²,

Zoeckler³

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Cleaner propellant combinations relative to usual storable propellants (MMH, UDMH, NTO), commonly designated as "green propellants" could come to fruition, provided early demonstration at low thrust level are satisfactory [8,16,21,42].…”

Section: Trend For Next and Future Launchersmentioning

confidence: 99%

A liquid propulsion panorama

Caisso¹,

Souchier²,

Rothmund³

et al. 2009

Acta Astronautica

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“…Here, T g is expected to be much lower than the effective gas temperature in the core flow (T ad ), which is calculated using Equation (2), where T ad is the adiabatic combustion temperature, and g is the energy release efficiency of the LRE.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on thermochemical phenomena in SiFRP

Hirai¹,

Matsuura²,

Kinefuchi

et al. 2012

Advanced Composite Materials

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This study focuses on understanding and modeling the physical phenomena that occur in degraded zones of silica-phenolic (SiFRP) materials under exposure to high-temperature gasses when applied to a liquid rocket engine (LRE) combustor. Although understanding and modeling these phenomena is considered essential in designing an LRE combustor, few studies on these fields can be found in the available literature. Basically, it is well known that when ablators are heated, a pyrolysis reaction proceeds in them, forming three distinct zones: a charred, a decomposed, and a virgin zone. The obtainable information for the thermal response of SiFRP in ground-firing tests is classified in two categories. The first category involves the equilibrium state characteristics after a long time has elapsed following burnout. This refers to the degraded thickness distribution, which reflects 3D information (the combustor's inner surface x the thickness direction) regarding the heat load distribution over the entire combustor's inner surface, owing to the highly insulating nature of SiFRP. The second category involves the transient characteristics of the propagation of the degraded zones in SiFRP, which can be detected using an ultrasonic testing (UT) method. In this paper, the progress of in-depth phenomena of SiFRP and their physical variations were intentionally studied. Our aim was to clarify and specify the quantitative threshold values of the interface points that characterize each degraded zone and the UT reflection point, and then express these values in terms of physical quantities that could appear in a numerical analysis.

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Development Testing of a LOX/Methane Engine for In-Space Propulsion

Cited by 19 publications

References 1 publication

Design, Fabrication, and Test of a LOX/LCH4 RCS Igniter at NASA

Design, Fabrication, and Test of a LOX/LCH4 RCS Igniter at NASA

A liquid propulsion panorama

Experimental investigation on thermochemical phenomena in SiFRP

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