Ignition and Burn in a Hybrid Nuclear Fuel for a Pulsed Rocket Engine
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作者:
Taylor, B.
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NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA
Univ Alabama, Prop Res Ctr, 301 Sparkman Dr, Huntsville, AL 35899 USANASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA
Taylor, B.
[1
,2
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Cassibry, J.
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Univ Alabama, Prop Res Ctr, 301 Sparkman Dr, Huntsville, AL 35899 USANASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA
Cassibry, J.
[2
]
Adams, R.
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NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USANASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA
Adams, R.
[1
]
机构:
[1] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA
[2] Univ Alabama, Prop Res Ctr, 301 Sparkman Dr, Huntsville, AL 35899 USA
This work explores the parameter space of a cylindrical hybrid nuclear fuel in support of a z-pinch driven pulsed fission-fusion (PuFF) engine. 0D power balance and 1D burn wave calculations have been performed to explore the parameter space of hybrid cylindrical nuclear fuels. The boundary of minimal initial conditions needed to reach breakeven are found within the context of the model. The effects of initial conditions upon the yield at the end of burn wave expansion are also determined. The model is used to examine the minimum initial energies predicted to result in yields of a few MJ. The goal of this work is to guide fuel design, inform future models and experiments as well as look for the most efficient parameter space for ignition in a z-pinch driven hybrid nuclear reaction. The impact of initial parameters upon ignition, burn, and gain are discussed. It is found that a hybrid cylindrical target may breakeven with initial energy near the axis of approximately 4-6 MJ in lithium deuteride/uranium 235 fuel. It is also found that magnetic field can lower the threshold further of which the magnitude changes across the parameter space. The dual fusion/fission reactions are found to boost each other leading to lower initial driving energies needed to reach breakeven in the hybrid cylindrical nuclear fuel.
机构:
Department of Aerospace Engineering, Lovely Professional University, Punjab, PhagwaraDepartment of Aerospace Engineering, Lovely Professional University, Punjab, Phagwara
Srivastava S.
Thakur A.K.
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Department of Aerospace Engineering, Lovely Professional University, Punjab, PhagwaraDepartment of Aerospace Engineering, Lovely Professional University, Punjab, Phagwara
Thakur A.K.
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Gupta L.R.
Gehlot A.
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机构:
Uttaranchal Institute of Technology, Uttaranchal University, Uttarakhand, DehradunDepartment of Aerospace Engineering, Lovely Professional University, Punjab, Phagwara
机构:
Dept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai
Seralathan S.
Sandeep K.
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Dept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai
Sandeep K.
Ejaz Z.H.
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Dept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai
Ejaz Z.H.
Sufiyan S.
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机构:
Dept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai
Sufiyan S.
Hariram V.
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机构:
Dept. of Mech. Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai
Hariram V.
Paul R.C.
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Dept. of Automobile Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai
Paul R.C.
Nadanakumar V.
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Dept. of Automobile Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, ChennaiDept. of Aeronautical Engg., Hindustan Inst. of Tech. and Sci., Padur, Tamil Nadu, Chennai