48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit 2012
DOI: 10.2514/6.2012-3935
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Design and Development of a LOX/LCH4 Technology Demonstrator

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Cited by 9 publications
(8 citation statements)
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“…The calculations are performed to second order accuracy with the criteria for convergence being a stabilised integral of total surface heat flux along the chamber wall. (1) as 1031 kgm -3 . The corresponding temperature is calculated at the injector upstream pressure of 10.93 MPa for this LOX density as 118K using NIST 11 tables.…”
Section: Figure 2 Grid 1 44792 Cellsmentioning
confidence: 99%
“…The calculations are performed to second order accuracy with the criteria for convergence being a stabilised integral of total surface heat flux along the chamber wall. (1) as 1031 kgm -3 . The corresponding temperature is calculated at the injector upstream pressure of 10.93 MPa for this LOX density as 118K using NIST 11 tables.…”
Section: Figure 2 Grid 1 44792 Cellsmentioning
confidence: 99%
“…3 The main objective is to improve the National system and technology capabilities on liquid rocket engines for future space applications, with specific regard to LOX/LCH 4 technology. The final aim of the program is building a rocket engine demonstrator whose high-level requirements can be summarized as follows: thrust class of 30 kN; relevant to future applications of space propulsion; pressurefed testing; regenerative cooling with liquid methane; ability to reproduce an expander cycle engine.…”
Section: Introductionmentioning
confidence: 99%
“…In this paper performance and stability analyses are conducted on the Penn State LOX/CH4 uni-element rocket, the details of which are described by Locke, Pal and Woodward 2 with performance and stability assessments by Hulka and Jones 3 as well as on the sub scale breadboard (SSBB) experimental rocket engine under development at CIRA 4 Of particular interest are the chamber pressures around 800 psia (5.5MPa), see Table 1 since these correspond to the nominal chamber pressures associated with the CIRA engine, and which are not fully documented by Hulka and Jones. These cases will be addressed in this paper and will be presented as an alternative step towards evaluating the performance of the CIRA SSBB.…”
Section: Introductionmentioning
confidence: 99%