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
Pedro Luiz Kaled Da Cás +3 more
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Advanced research and technology programs for advanced high-pressure oxygen-hydrogen rocket propulsion [PDF]
A research and technology program for advanced high pressure, oxygen-hydrogen rocket propulsion technology is presently being pursued by the National Aeronautics and Space Administration (NASA) to establish the basic discipline technologies, develop the ...
Marsik, S. J., Morea, S. F.
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Neural Network-Based Optimization of Hybrid Rocket Design for Modular Multistage Launch Vehicle
AerospaceIn this paper, an integrated optimization is carried out to find the optimal hybrid rocket engine design for a modular multistage launch vehicle targeting a 500 km polar circular orbit. A single hybrid rocket engine unit is reused across the whole launch
Paolo Maria Zolla +3 more
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, 1985 A dual structure aerospace vehicle is described which has an aeroshell structure and an internally disposed separable and reusable integral tank/thrust structure.
Jackson, L. R., Taylor, A. H.
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Space Transportation Materials and Structures Technology Workshop. Volume 1: Executive summary [PDF]
The workshop was held to provide a forum for communication within the space materials and structures technology developer and user communities. Workshop participants were organized into a Vehicle Technology Requirements session and three working panels ...
Cazier, F. W., Jr., Gardner, J. E.
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Study of low acceleration space transportation systems. Volume I - Summary Phase II STUDY report [PDF]
Technical feasibility of electric-nuclear propulsion system for manned Mars ...
Brown, H., Coates, G. L.
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Final design report of a personnel launch system and a family of heavy lift launch vehicles [PDF]
The objective was to design both a Personnel Launch System (PLS) and a family of Heavy Lift Launch Vehicles (FHLLVs) that provide low cost and efficient operation in missions not suited for the Shuttle.
Burton, Lee +7 more
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Using Hydrogen Peroxide for Rocket Fuel Tank Pressurization: Innovations, Advantages, and Challenges
Challenges and Issues of Modern ScienceThis paper explores the innovative use of hydrogen peroxide (H₂O₂) as a pressurizing agent for rocket fuel tanks, highlighting its potential to enhance efficiency and performance in rocket propulsion systems.
Mykhailo Vorobei, Mykola Bondarenko
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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.
europepmc +1 more source
Nuclear thermal/nuclear electric hybrids [PDF]
A description is given of the nuclear thermal and nuclear electric hybrid. The specifications are described along with its mission performance.
Reid, B. D.
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