AN OPTIMIZED HYBRID ROCKET MOTOR FOR THE SARA PLATFORM REENTRY SYSTEM DOI 10.5028/jatm.2012.04032312
Journal of Aerospace Technology and Management, 2012 This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the
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Performance of a circular body earth-to-orbit winged transport with various strap-on boosters [PDF]
Various types of twin strap-on boosters were evaluated by applying them to a core vehicle. The core vehicle has a clipped delta wing and a simple circular body, and is equipped with five Space Shuttle main engines.
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Influence of Adding Carbonaceous Fuels to Ionic Liquids on Propellant Properties. [PDF]
ACS Omega, 2022 Gao X, Gao Z, Tan Y, Chen P, Du Z, Li Y.
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Combustor design and analysis using the Rocket Combustor Interactive Design (ROCCID) methodology [PDF]
The ROCket Combustor Interactive Design (ROCCID) Methodology is a newly developed, interactive computer code for the design and analysis of a liquid propellant rocket combustion chamber.
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Analysis of carbon nano particle variant as the propellant fuel to increase specific impulses of rockets. [PDF]
F1000Res, 2023 Navalino R, Muda N, Hafizah M, Ruyat Y.
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Evaluation of on-board hydrogen storage methods for hypersonic vehicles [PDF]
Hydrogen is the foremost candidate as a fuel for use in high speed transport. Since any aircraft moving at hypersonic speeds must have a very slender body, means of decreasing the storage volume requirements below that for liquid hydrogen are needed. The
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Particle-Filter-Based Fault Diagnosis for the Startup Process of an Open-Cycle Liquid-Propellant Rocket Engine. [PDF]
Sensors (Basel)Cha J, Ko S, Park SY.
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Effect of Correlation on Multi-Engine Rocket Propulsion Systems [PDF]
A matter of great concern in the design and operation of multi-engine rocket propulsion systems is the effect of the premature shutdown of one engine on the vehicle.
Baker, J. R., Breneman, J. E.
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Tripropellant combustion process [PDF]
The addition of small amounts of hydrogen to the combustion of LOX/hydrocarbon propellants in large rocket booster engines has the potential to enhance the system stability.
Carroll, R. G., Kmiec, T. D.
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Nano-Iron as a Catalyst in Isocyanate-Free Rocket Propellants. [PDF]
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