Historical Evolution of the Space Shuttle Primary and Vernier Reaction Control Rocket Engine Designs

Stechman, Carl; Lawson, C G

doi:10.2514/6.2006-4892

Cited by 4 publications

(4 citation statements)

References 10 publications

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“…Therefore, it can be concluded that L2 with a high silicon content was composed of metal disilicides. Some studies have shown that the silicide of the transition layer was M 5 Si 3 [25][26][27][28][29][30]34]. In this work, the atomic ratio of metals to silicon in the L1 layer was basically the same as that of M 5 Si 3 , indicating that the silicide in the L1 layer was M 5 Si 3 .…”

Section: Oxidation Behavior Of the Silicide Coatingsupporting

confidence: 50%

“…The Si-20Cr-20Fe coating had very stable performance in a combustion atmosphere at 1360 • C and could withstand hundreds of thermal shocks. It has been successfully used as a high-temperature protective coating for niobium alloy nozzles of F100 rocket engines [29]. Sankar et al analyzed the microstructure and composition evolution of the Si-20Cr-20Fe coating on C103 alloy during oxidation and explained the formation and oxidation resistance mechanisms of the silicide coating [30].…”

Section: Introductionmentioning

confidence: 99%

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Microstructure and Composition Evolution of a Fused Slurry Silicide Coating on MoNbTaTiW Refractory High-Entropy Alloy in High-Temperature Oxidation Environment

Han

Zhang

et al. 2020

Materials

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In this paper, the Si-20Cr-20Fe coating was prepared on MoNbTaTiW RHEA by a fused slurry method. The microstructural evolution and compositions of the silicide coating under high-temperature oxidation environment were studied. The results show that the silicide coating could effectively prevent the oxidation of the MoNbTaTiW RHEA. The initial silicide coating had a double-layer structure: a high silicon content layer mainly composed of MSi2 as the outer layer and a low silicon content layer mainly contained M5Si3 as the inner layer. Under high-temperature oxidation conditions, the silicon element diffused from the silicide coating to the RHEA substrate while the oxidation of the coating occurred. After oxidation, the coating was composed of an outer oxide layer and an inner silicide layer. The silicide layer moved toward the inside of the substrate, led to the increase of its thickness. Compared with the initial silicified layer, its structure did not change significantly. The structure and compositions of the oxide layer on the outer surface strongly depended on the oxidation temperature. This paper provides a strategy for protecting RHEAs from oxidation at high-temperature environments.

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Section: Oxidation Behavior Of the Silicide Coatingsupporting

confidence: 50%

Section: Introductionmentioning

confidence: 99%

Microstructure and Composition Evolution of a Fused Slurry Silicide Coating on MoNbTaTiW Refractory High-Entropy Alloy in High-Temperature Oxidation Environment

Han

Zhang

et al. 2020

Materials

View full text Add to dashboard Cite

show abstract

“…Therefore, it can be concluded that L2 with a high silicon content was composed of metal disilicides. Some studies have shown that the silicide of the transition layer was M5Si3 [25][26][27][28][29][30]34]. In this work, the atomic ratio of metals to silicon in the L1 layer was basically the same as that of M5Si3, indicating that the silicide in the L1 layer was M5Si3.…”

Section: Oxidation Behavior Of the Silicide Coatingsupporting

confidence: 48%

Microstructure and Composition Evolution of a Fused Slurry Silicide Coating on MoNbTaTiW Refractory High-entropy Alloy in High-temperature Oxidation Environment

Han¹,

Su²,

Zhang³

et al. 2020

Preprint

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The poor oxidation resistance of refractory high-entropy alloys (RHEAs) is a major obstacle for their use in high-temperature engineering applications. Anti-oxidation coating technology is an effective method for improving the oxidation resistance. In this paper, the Si-20Cr-20Fe coating was prepared on MoNbTaTiW RHEA by a fused slurry method. The microstructural evolution and compositions of the silicide coating under high-temperature oxidation environment were studied. The results show that the silicide coating could effectively prevent the oxidation of the MoNbTaTiW RHEA. The initial silicide coating had a double-layer structure; a high silicon-content layer mainly composed of MSi2 as the outer layer and a low silicon-content layer mainly contained M5Si3 as the inner layer. Under high-temperature oxidation conditions, the silicon element diffused from the silicide coating to the RHEA substrate while the oxidation of the coating occurred. After oxidation, the coating was composed of an outer oxide layer and an inner silicide layer. The silicide layer moved toward the inside of the substrate, led to the increase of its thickness. Compared with the initial silicified layer, its structure did not change significantly. The structure and compositions of the oxide layer on the outer surface strongly depended on the oxidation temperature. This paper provides a strategy for protecting RHEAs from oxidation at high-temperature environments.

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“…This series of engines has been developed from R-4D-7 to R-4D-16. After more than 40 years of development, through continuous improvement, the engine structure design and material selection, as well as the selection of new propellants, the specific impulse performance of the engine have been improved by more than 10% [2][3][4]. EADS' Astrium division's 10N bipropellant thrusters S10-01, S10-02, S10-18, etc.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on the New 100N Bipropellant Space Rocket Engine

Huang¹,

Zhang²,

Wang³

et al. 2022

Proceedings of the International Conference of Fluid Power and Mechatronic Control Engineering (ICFPMCE 2022)

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This paper developed experimental research on the new 100N bipropellant space rocket engine. The bi-centrifugal swirl injector with high degree of technological maturity, high reliability and properties is used on this engine. The cold flow test, steady-state hot firing, pulse-mode firing, long life hot firing and deflection firing test are carried out. The results show that, the flow and spray characteristics of injector keep stable; during the steady-state hot firing, the structure of engine is intact; the impulse is good and the heat back temperature can up to 220.2 °C; during the different pulse-mode firing, the engine response time (t90) is lower than 38 ms; after the 45000 s long life firing, the structure temperate is not high which can fit the demand of long life; the heat back temperature of weld can up to 232.0 °C.

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Historical Evolution of the Space Shuttle Primary and Vernier Reaction Control Rocket Engine Designs

Cited by 4 publications

References 10 publications

Microstructure and Composition Evolution of a Fused Slurry Silicide Coating on MoNbTaTiW Refractory High-Entropy Alloy in High-Temperature Oxidation Environment

Microstructure and Composition Evolution of a Fused Slurry Silicide Coating on MoNbTaTiW Refractory High-Entropy Alloy in High-Temperature Oxidation Environment

Microstructure and Composition Evolution of a Fused Slurry Silicide Coating on MoNbTaTiW Refractory High-entropy Alloy in High-temperature Oxidation Environment

Experimental Investigation on the New 100N Bipropellant Space Rocket Engine

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