subject:(NTR Nuclear Thermal Rocket)

Colorado School of Mines

1. Labib, Satira I. Design analysis and risk assessment for a single stage to orbit nuclear thermal rocket.

Degree: MS(M.S.), Metallurgical and Materials Engineering, 2014, Colorado School of Mines

► Recent advances in high power density fuel materials have renewed interest in nuclear thermal rockets (NTRs) as a viable propulsion technology for future space exploration.… (more)

▼ Recent advances in high power density fuel materials have renewed interest in nuclear thermal rockets (NTRs) as a viable propulsion technology for future space exploration. This thesis describes the design of three NTR reactor engines designed for the single stage to orbit launch of payloads from 1-15 metric tons. Thermal hydraulic and rocket engine analyses indicate that the proposed rocket engines are able to reach specific impulses in excess of 700 seconds. Neutronics analyses performed using MCNP5 demonstrate that the hot excess reactivity, shutdown margin, and submersion criticality requirements are satisfied for each NTR reactor. The reactors each consist of a 40 cm diameter core packed with hexagonal tungsten cermet fuel elements. The core is surrounded by radial and axial beryllium reflectors and eight boron carbide control drums. At the same power level, the 40 cm reactor results in the lowest radiation dose rate of the three reactors. Radiation dose rates decrease to background levels ~3.5 km from the launch site. After a one-year decay time, all of the activated materials produced by an NTR launch would be classified as Class A low-level waste. The activation of air produces significant amounts of argon-41 and nitrogen-16 within 100 m of the launch. The derived air concentration, DAC, from the activation products decays to less than unity within two days, with only argon-41 remaining. After 10 minutes of full power operation the 120 cm core corresponding to a 15 MT payload contains 2.5 x 10[superscript 13], 1.4 x 10[superscript 12], 1.5 x 10[superscript 12], and 7.8 x 10[superscript 7] Bq of [superscript 131]I, [superscript 137]Cs, [superscript 90]Sr, and [superscript 239]Pu respectively. The decay heat after shutdown increases with increasing reactor power with a maximum decay heat of 108 kW immediately after shutdown for the 15 MT payload. Advisors/Committee Members: King, Jeffrey C. (advisor), Howe, Steven D. (committee member), Braley, Jenifer C. (committee member).

Subjects/Keywords: NTR; space exploration; nuclear thermal rocket; nuclear propulsion; nuclear; Nuclear rockets; Nuclear rockets – Risk assessment; Nuclear rockets – Design; Nuclear propulsion; Propellants; Nuclear reactors

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APA (6^th Edition):

Labib, S. I. (2014). Design analysis and risk assessment for a single stage to orbit nuclear thermal rocket. (Masters Thesis). Colorado School of Mines. Retrieved from http://hdl.handle.net/11124/80818

Chicago Manual of Style (16^th Edition):

Labib, Satira I. “Design analysis and risk assessment for a single stage to orbit nuclear thermal rocket.” 2014. Masters Thesis, Colorado School of Mines. Accessed March 04, 2021. http://hdl.handle.net/11124/80818.

MLA Handbook (7^th Edition):

Labib, Satira I. “Design analysis and risk assessment for a single stage to orbit nuclear thermal rocket.” 2014. Web. 04 Mar 2021.

Vancouver:

Labib SI. Design analysis and risk assessment for a single stage to orbit nuclear thermal rocket. [Internet] [Masters thesis]. Colorado School of Mines; 2014. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/11124/80818.

Council of Science Editors:

Labib SI. Design analysis and risk assessment for a single stage to orbit nuclear thermal rocket. [Masters Thesis]. Colorado School of Mines; 2014. Available from: http://hdl.handle.net/11124/80818

University of Maryland

2. Clough, Joshua. Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets.

Degree: Aerospace Engineering, 2007, University of Maryland

URL: http://hdl.handle.net/1903/7604

► Bimodal nuclear thermal rocket (BNTR) engines have been shown to reduce the weight of space vehicles to the Moon, Mars, and beyond by utilizing a… (more)

▼ Bimodal nuclear thermal rocket (BNTR) engines have been shown to reduce the weight of space vehicles to the Moon, Mars, and beyond by utilizing a common reactor for propulsion and power generation. These savings lead to reduced launch vehicle costs and/or increased mission safety and capability. Experimental work of the Rover/NERVA program demonstrated the feasibility of NTR systems for trajectories to Mars. Numerous recent studies have demonstrated the economic and performance benefits of BNTR operation. Relatively little, however, is known about the reactor-level operation of a BNTR engine. The objective of this dissertation is to develop a numerical BNTR engine model in order to study the feasibility and component-level impact of utilizing a NERVA-derived reactor as a heat source for both propulsion and power. The primary contribution is to provide the first-of-its-kind model and analysis of a NERVA-derived BNTR engine. Numerical component models have been modified and created for the NERVA reactor fuel elements and tie tubes, including 1-D coolant thermodynamics and radial thermal conduction with heat generation. A BNTR engine system model has been created in order to design and analyze an engine employing an expander-cycle nuclear rocket and Brayton cycle power generator using the same reactor. Design point results show that a 316 MWt reactor produces a thrust and specific impulse of 66.6 kN and 917 s, respectively. The same reactor can be run at 73.8 kWt to produce the necessary 16.7 kW electric power with a Brayton cycle generator. This demonstrates the feasibility of BNTR operation with a NERVA-derived reactor but also indicates that the reactor control system must be able to operate with precision across a wide power range, and that the transient analysis of reactor decay heat merits future investigation. Results also identify a significant reactor pressure-drop limitation during propulsion and power-generation operation that is caused by poor tie tube thermal conductivity. This leads to the conclusion that, while BNTR operation is possible with a NERVA-derived reactor, doing so requires careful consideration of the Brayton cycle design point and fuel element survivability. Advisors/Committee Members: Lewis, Mark J (advisor).

Subjects/Keywords: Engineering, Aerospace; Engineering, Nuclear; bimodal nuclear thermal rocket; bntr; ntr; nuclear propulsion and power generation; NERVA-derived; Brayton cycle

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APA (6^th Edition):

Clough, J. (2007). Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/7604

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Clough, Joshua. “Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets.” 2007. Thesis, University of Maryland. Accessed March 04, 2021. http://hdl.handle.net/1903/7604.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Clough, Joshua. “Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets.” 2007. Web. 04 Mar 2021.

Vancouver:

Clough J. Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets. [Internet] [Thesis]. University of Maryland; 2007. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1903/7604.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Clough J. Integrated Propulsion and Power Modeling for Bimodal Nuclear Thermal Rockets. [Thesis]. University of Maryland; 2007. Available from: http://hdl.handle.net/1903/7604

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Texas A&M University

3. Appel, Bradley. Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket.

Degree: MS, Nuclear Engineering, 2012, Texas A&M University

URL: http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649

► The goal of this research is to apply modern methods of analysis to the design of a tungsten-cermet Nuclear Thermal Rocket (NTR) core. An NTR… (more)

▼ The goal of this research is to apply modern methods of analysis to the design of a tungsten-cermet Nuclear Thermal Rocket (NTR) core. An NTR is one of the most viable propulsion options for enabling piloted deep-space exploration. Concerns over fuel safety have sparked interest in an NTR core based on tungsten-cermet fuel. This work investigates the capability of modern CFD and neutronics codes to design a cermet NTR, and makes specific recommendations for the configuration of channels in the core. First, the best CFD practices available from the commercial package Star-CCM+ are determined by comparing different modeling options with a hot-hydrogen flow experiment. Next, through grid convergence and sensitivity studies, numerical uncertainty is shown to be a small contributor to overall uncertainty; while fuel thermal conductivity, hydrogen specific heat, and fission energy deposition are found to have a large impact on simulation uncertainty. The model-form error is then estimated by simulation of a NERVA fuel element from an NRX-A6 engine test, where the peak temperature matches measured data to within 2.2%. Using a combination of Star-CCM+ and MCNP for neutronics, typical uncertainties are estimated at 3% for predicting fuel temperature, 2% for hydrogen temperature, and 5% for pressure. The second part uses the aforementioned analysis methods in a parametric study to determine what coolant channel size and distribution is optimum for a 10 klbf-thrust cermet NTR core. By varying the channel diameter and pitch-to-diameter ratio (p/d), it is found that a diameter of 0.12 cm with a p/d of 1.8 results in the lightest core with a peak temperature of 2850 K. The study also shows that element-by-element mass flow rate zoning is the best method for handling radial power peaking. In addition, a detailed simulation of a cermet design developed at the Argonne National Laboratory shows that modifications to the historical fuel element design are required to avoid overheating. The final part investigates the ability of Star-CCM+ to model fuel element failure modes. Through a combination of uncertainty quantification and a parametric analysis, this thesis ultimately lays a groundwork for future detailed design of cermet NTR fuel elements. Advisors/Committee Members: Vierow, Karen (advisor), Bragg-Sitton, Shannon (advisor), Cizmas, Paul (committee member).

Subjects/Keywords: nuclear; rocket; CFD; propulsion

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APA (6^th Edition):

Appel, B. (2012). Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649

Chicago Manual of Style (16^th Edition):

Appel, Bradley. “Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket.” 2012. Masters Thesis, Texas A&M University. Accessed March 04, 2021. http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649.

MLA Handbook (7^th Edition):

Appel, Bradley. “Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket.” 2012. Web. 04 Mar 2021.

Vancouver:

Appel B. Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. [Internet] [Masters thesis]. Texas A&M University; 2012. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649.

Council of Science Editors:

Appel B. Multiphysics Design and Simulation of a Tungsten-Cermet Nuclear Thermal Rocket. [Masters Thesis]. Texas A&M University; 2012. Available from: http://hdl.handle.net/1969.1/ETD-TAMU-2012-08-11649

University of Waterloo

4. Christopher, Nicholas. Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate.

Degree: 2020, University of Waterloo

URL: http://hdl.handle.net/10012/15463

► Transpiration cooling is a promising thermal protection system for gas turbines, atmospheric re-entry heat shields, and rocket engine combustion chambers. Design of transpiration cooling systems… (more)

▼ Transpiration cooling is a promising thermal protection system for gas turbines, atmospheric re-entry heat shields, and rocket engine combustion chambers. Design of transpiration cooling systems must rely on numerical simulation in order to reduce costs. The purpose of this work it to better understand the physical phenomena which effect turbulence and heat transfer in a turbulent boundary layer with transpiration cooling, in order to inform models of the system. Towards this goal, direct numerical simulations (DNS) of transpiration cooling in a turbulent flat-plate boundary layer at a freestream mach number of 0.3 have been performed. The coolant and the hot gas are both air, and isothermal walls and coolant at a temperature ratio of Tw/T∞ = 0.5 have been prescribed. The blowing ratio (which is the mass flux ratio between the coolant and the freestream gas), and the coolant injection boundary conditions have been varied to investigate their effects on the flow. It is found that by increasing the blowing ratio, the peak turbulent kinetic energy moves away from the wall to a region of shear between the low-momentum coolant and high-momentum hot gas. As the blowing ratio is increased, there is also a reduction in heat transfer to the porous wall. This reduction of wall heat transfer is caused by the combined effects of heat advection due to the non-zero wall-normal velocity at the wall, and the reduction of the average boundary-layer temperature due to the accumulation of coolant. A new model for the latter effect is proposed which is physically realistic in the limit cases. The proposed combined model accounts for both heat advection and film accumulation and shows good agreement with the DNS data. An increase in turbulent transport of heat with increasing blowing rate is caused by the production of vortices between the coolant and hot gas. This causes a reduction in the cooling effectiveness, and can be seen near the leading edge of the transpiration region. Log law scaling of the velocity profile with blowing walls is analyzed, and found to only be applicable for modest blowing rates. Reasons for the failure of scaling laws at high blowing rates are proposed based on the x-momentum balance of the Navier-Stokes equations. In order to investigate wall modelling effects, simulations with uniform coolant injection have been compared to simulations with injection via many small slits. It is observed that as the slits get smaller (at fixed total mass flow rate and fixed wall porosity), the results trend towards the uniform injection case. Therefore, it is hypothesized that for small pore sizes, neglecting the effects of the individual pores in the wall boundary condition is physically justifiable.

Subjects/Keywords: rocket; thermal protection system; transpiration cooling; direct numerical simulation

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Christopher, N. (2020). Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate. (Thesis). University of Waterloo. Retrieved from http://hdl.handle.net/10012/15463

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Christopher, Nicholas. “Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate.” 2020. Thesis, University of Waterloo. Accessed March 04, 2021. http://hdl.handle.net/10012/15463.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Christopher, Nicholas. “Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate.” 2020. Web. 04 Mar 2021.

Vancouver:

Christopher N. Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate. [Internet] [Thesis]. University of Waterloo; 2020. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/10012/15463.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Christopher N. Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate. [Thesis]. University of Waterloo; 2020. Available from: http://hdl.handle.net/10012/15463

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

KTH

5. Westerlund, Simon. Design of Ablative Insulator for Solid Rocket Booster.

Degree: Energy Technology, 2015, KTH

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-179031

► The objective of this master thesis was to investigate an ablative liner for the T-Minus DART booster that will accelerate a dart to Mach… (more)

Subjects/Keywords: Solid rocket propulsion ablation thermal liner oxyacetylene torch

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APA (6^th Edition):

Westerlund, S. (2015). Design of Ablative Insulator for Solid Rocket Booster. (Thesis). KTH. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-179031

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Westerlund, Simon. “Design of Ablative Insulator for Solid Rocket Booster.” 2015. Thesis, KTH. Accessed March 04, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-179031.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Westerlund, Simon. “Design of Ablative Insulator for Solid Rocket Booster.” 2015. Web. 04 Mar 2021.

Vancouver:

Westerlund S. Design of Ablative Insulator for Solid Rocket Booster. [Internet] [Thesis]. KTH; 2015. [cited 2021 Mar 04]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-179031.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Westerlund S. Design of Ablative Insulator for Solid Rocket Booster. [Thesis]. KTH; 2015. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-179031

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Luleå University of Technology

6. Martinez, Lisandro. Space radiation analysis : radiation effects and particle interaction outside Earth Magnetosphere using GRAS and GEANT4.

Degree: 2009, Luleå University of Technology

URL: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-48735

►

Detailed analyses of galactic cosmic rays (GCR), solar proton events (SPE), and solar fluence effects have been conducted using SPENVIS and CREME96 data files… (more)

Subjects/Keywords: Technology; Space Science; technology; radiation; space radiation; space; physics; cancer; GEANT4; GRAS; ICRU sphere; AG: Antigravity; ALARA: As Low As Reasonably Achievable; ASTAR: stopping power and range tables for helium ions; BERT: Bertini Cascade Model; BNTR: Bimodal Nuclear Thermal Rocket; CERN: European Organization for Nuclear Research; CHIPS: Chiral Invariant Phase Space; CPU: Central Processing Unit; CREME96: Cosmic Ray Effects on Micro Electronics; DOSTEL: DOSimetry TELescopes; ESA: European Space Agency; GCR: Galactic Cosmic Rays; GDML: Geometry Description Markup Language; GEANT4: toolkit for the simulation of the passage of; particles through matter; GNC: Guidance Navigation and Control; GRAS: Geant4 Radiation Analysis for Space; HEP: High Energy Parameterized; ICRU: International Commission on Radiation Units and; Measurements; IMF: Interplanetary Magnetic Field; IMLEO: Initial Mass in Low Earth Orbit; INFI: Instituto Natzionale di Fisica Nuclear); ISP: Specific Impulse; ISS: International Space Station; JPL: Jet Propulsion Laboratory; LEO: Low Earth Orbit; LEP: Low Energy Parameterized; MPD: Magneto Plasma Dynamics; MULASSIS: MUlti‐:LAyered Shielding Simulation Software; NASA: National Aeronautics and Space Administration; NCRP: National Council of Radiation Protection; NEP: Nuclear Electric Propulsion; NERVA: Nuclear Engine Rocket Vehicle Application; NIST: National Institute of Standards and Technology; NTR: Nuclear Thermal Rocket; PSTAR: stopping power and range tables for protons; QGS: Quark Gluon String; S/C: Spacecraft; SPE: Solar Proton Events; SEP: Solar Electric Propulsion; SPENVIS: Space Environment Information System; TEPC: Tissue Equivalent Proportional Counter; TMI: Trans Mars Insertion; TPS: Thermal Protection System; Teknik

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Martinez, L. (2009). Space radiation analysis : radiation effects and particle interaction outside Earth Magnetosphere using GRAS and GEANT4. (Thesis). Luleå University of Technology. Retrieved from http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-48735

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Martinez, Lisandro. “Space radiation analysis : radiation effects and particle interaction outside Earth Magnetosphere using GRAS and GEANT4.” 2009. Thesis, Luleå University of Technology. Accessed March 04, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-48735.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Martinez, Lisandro. “Space radiation analysis : radiation effects and particle interaction outside Earth Magnetosphere using GRAS and GEANT4.” 2009. Web. 04 Mar 2021.

Vancouver:

Martinez L. Space radiation analysis : radiation effects and particle interaction outside Earth Magnetosphere using GRAS and GEANT4. [Internet] [Thesis]. Luleå University of Technology; 2009. [cited 2021 Mar 04]. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-48735.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Martinez L. Space radiation analysis : radiation effects and particle interaction outside Earth Magnetosphere using GRAS and GEANT4. [Thesis]. Luleå University of Technology; 2009. Available from: http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-48735

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Texas A&M University

7. Rodriguez, Oscar. RELAP5-3D Thermal Hydraulics Computer Program Analysis Coupled with DAKOTA and STAR-CCM+ Codes.

Degree: MS, Mechanical Engineering, 2012, Texas A&M University

URL: http://hdl.handle.net/1969.1/148410

► RELAP5-3D has been coupled with both DAKOTA and STAR-CCM+ in order to expand the capability of the thermal-hydraulic code and facilitate complex studies of desired… (more)

▼ RELAP5-3D has been coupled with both DAKOTA and STAR-CCM+ in order to expand the capability of the thermal-hydraulic code and facilitate complex studies of desired systems. In the first study, RELAP5-3D was coupled with DAKOTA to perform a sensitivity study of the South Texas Project (STP) power plant during steady-state and transient scenarios. The coupled software was validated by analyzing the simulation results with respect of the physical expectations and behavior of the power plant, and thermal-hydraulic parameters which caused greatest sensitivity where identified: inlet core temperature and reactor thermal power. These variables, along with break size and discharge coefficients, were used for further investigation of the sensitivity of the RELAP5-3D LOCA transient simulation under three difference cases: two inch break, six inch break, and guillotine break. Reactor thermal power, core inlet temperature, and break size were identified as producing the greatest sensitivity; therefore, future research would include uncertainty quantification for these parameters. In the second study, a small scale experimental facility, designed to study the thermal hydraulic phenomena of the Reactor Cavity Cooling System (RCCS) for a Very High Temperature Reactor (VHTR), was used as a model to test the capabilities of coupling Star-CCM+ and RELAP5-3D. This chapter discusses the capabilities and limitations of the STAR-CCM+/RELAP5-3D coupling, and a simulation, on the RCCS facility, was performed using STAR-CCM+ to study the flow patterns where expected complex flow phenomena occur and RELAP5-3D for the complete system. The code showed inability to perform flow coupling simulations and it is unable, at this time, to handle closed loop systems. The thermal coupling simulation was successful and showed congruent qualitative results to physical expectations. The locations of large fluid vortices were located specifically in the pipes closest to the inlet of the bottom manifold. In conclusion, simulations using coupled codes were presented which greatly improved the capabilities of RELAP5-3D stand-alone and computational time required to perform complex thermal-hydraulic studies. These improvements show greatly benefit for industrial applications in order to perform large scale thermal-hydraulic systems studies with greater accuracy while minimizing simulation time. Advisors/Committee Members: Hassan, Yassin A (advisor), Marlow, William H (advisor), Jacobs, Timothy J (committee member).

Subjects/Keywords: Nuclear CFD; thermal hydraulics

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Rodriguez, O. (2012). RELAP5-3D Thermal Hydraulics Computer Program Analysis Coupled with DAKOTA and STAR-CCM+ Codes. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/148410

Chicago Manual of Style (16^th Edition):

Rodriguez, Oscar. “RELAP5-3D Thermal Hydraulics Computer Program Analysis Coupled with DAKOTA and STAR-CCM+ Codes.” 2012. Masters Thesis, Texas A&M University. Accessed March 04, 2021. http://hdl.handle.net/1969.1/148410.

MLA Handbook (7^th Edition):

Rodriguez, Oscar. “RELAP5-3D Thermal Hydraulics Computer Program Analysis Coupled with DAKOTA and STAR-CCM+ Codes.” 2012. Web. 04 Mar 2021.

Vancouver:

Rodriguez O. RELAP5-3D Thermal Hydraulics Computer Program Analysis Coupled with DAKOTA and STAR-CCM+ Codes. [Internet] [Masters thesis]. Texas A&M University; 2012. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1969.1/148410.

Council of Science Editors:

Rodriguez O. RELAP5-3D Thermal Hydraulics Computer Program Analysis Coupled with DAKOTA and STAR-CCM+ Codes. [Masters Thesis]. Texas A&M University; 2012. Available from: http://hdl.handle.net/1969.1/148410

Penn State University

8. Martin, Heath Thomas. Assessment of the Performance of Ablative Insulators under Realistic Solid Rocket Motor Operating Conditions.

Degree: 2013, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/17518

► Ablative insulators are used in the interior surfaces of solid rocket motors to prevent the mechanical structure of the rocket from failing due to intense… (more)

Subjects/Keywords: solid rocket motor; ablation; ablative; heat flux measurement; thermal radiation; radiometer; x-ray radiography

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Martin, H. T. (2013). Assessment of the Performance of Ablative Insulators under Realistic Solid Rocket Motor Operating Conditions. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/17518

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Martin, Heath Thomas. “Assessment of the Performance of Ablative Insulators under Realistic Solid Rocket Motor Operating Conditions.” 2013. Thesis, Penn State University. Accessed March 04, 2021. https://submit-etda.libraries.psu.edu/catalog/17518.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Martin, Heath Thomas. “Assessment of the Performance of Ablative Insulators under Realistic Solid Rocket Motor Operating Conditions.” 2013. Web. 04 Mar 2021.

Vancouver:

Martin HT. Assessment of the Performance of Ablative Insulators under Realistic Solid Rocket Motor Operating Conditions. [Internet] [Thesis]. Penn State University; 2013. [cited 2021 Mar 04]. Available from: https://submit-etda.libraries.psu.edu/catalog/17518.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Martin HT. Assessment of the Performance of Ablative Insulators under Realistic Solid Rocket Motor Operating Conditions. [Thesis]. Penn State University; 2013. Available from: https://submit-etda.libraries.psu.edu/catalog/17518

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

The Ohio State University

9. Eades, Michael J., Eades. ¹³⁵Xe in LEU Cermet Nuclear Thermal Propulsion Systems.

Degree: PhD, Nuclear Engineering, 2016, The Ohio State University

URL: http://rave.ohiolink.edu/etdc/view?acc_num=osu1468426881

► Nuclear Thermal Propulsion (NTP) is currently a topic of research for NASA. NASA has the goal of sending humans to Mars and Nuclear Thermal Propulsion… (more)

▼ Nuclear Thermal Propulsion (NTP) is currently a topic of research for NASA. NASA has the goal of sending humans to Mars and Nuclear Thermal Propulsion (NTP) is an appealing technology to aid in this endeavor. In the simplest terms, an NTP system is a nuclear reactor that utilizes hydrogen that is expanded through a convergent-divergent nozzle and ejected for propulsion. NTP can shorten the travel time to Mars and reduce the mass that must be lifted into low earth orbit. Furthermore, strategies to use low enriched uranium (LEU) in NTP systems have been identified which could make NTP significantly more affordable to develop than for past NTP development efforts. Beyond a human Mars mission, NTP has the potential to assist in other human and robotic missions beyond low earth orbit. The overarching goal of this work is to better understand NTP technology so that it may one day help with a human Mars mission. This work focuses on a subset of NTP systems that use a combination of LEU and tungsten cermet fuel and addresses the issues related to ¹³⁵Xe in these systems. LEU cermet NTP systems have a unique operational regime where ¹³⁵Xe has a profound impact on performance and controllability. LEU cermet NTP have extremely high power densities, operate with a thermal neutron spectrum, and the reference human mission to Mars requires restarting the reactor 4 to 8 hour after full power operation. In this work, two LEU cermet NTP point designs are presented and used as reference systems for the study of ¹³⁵Xe in LEU cermet NTP systems. These point designs were produced with a thorough search of the rocket performance design space.Using infinite lattice burnup calculations, it was found that MCNP 6.1.1 Beta and Serpent 2 produced very similar results and that burnup cells across the fuel element were not needed to capture spatial self shielding effects. The infinite lattice results were used to inform the approach undertaken for the full core burnup calculations. Full core burnup calculations indicate that the reactivity loss during operation of a LEU cermet NTP system has a maximum value of 210 pcm during a 25 minute burn and the maximum reactivity loss after operation peaks at approximately 3500 pcm. The possible effect of ^135mXe on xenon worth in LEU cermet NTP systems was found by using the model based TENDL-2014 nuclear data library and Serpent 2. Model based TENDL cross sections were used because no experimentally determined cross sections are available for ^135mXe. A relationship to estimate the performance (in terms of Isp loss) as a function of control drum angle is derived and presented. Mitigation strategies are identified that show promise for counteracting the effects of ¹³⁵Xe and maximizing the performance of LEU cermet NTP systems. It is recommended for future work that an integrated reactor systems code be developed to examine ¹³⁵Xe in LEU cermet NTP more thoroughly. In addition, this work has identified a need for basic nuclear data… Advisors/Committee Members: Thomas, Blue (Advisor).

Subjects/Keywords: Nuclear Engineering; Xenon-135, Space Nuclear, Nuclear Thermal Propulsion, Xe-135m

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APA (6^th Edition):

Eades, Michael J., E. (2016). ¹³⁵Xe in LEU Cermet Nuclear Thermal Propulsion Systems. (Doctoral Dissertation). The Ohio State University. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=osu1468426881

Chicago Manual of Style (16^th Edition):

Eades, Michael J., Eades. “¹³⁵Xe in LEU Cermet Nuclear Thermal Propulsion Systems.” 2016. Doctoral Dissertation, The Ohio State University. Accessed March 04, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1468426881.

MLA Handbook (7^th Edition):

Eades, Michael J., Eades. “¹³⁵Xe in LEU Cermet Nuclear Thermal Propulsion Systems.” 2016. Web. 04 Mar 2021.

Vancouver:

Eades, Michael J. E. ¹³⁵Xe in LEU Cermet Nuclear Thermal Propulsion Systems. [Internet] [Doctoral dissertation]. The Ohio State University; 2016. [cited 2021 Mar 04]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1468426881.

Council of Science Editors:

Eades, Michael J. E. ¹³⁵Xe in LEU Cermet Nuclear Thermal Propulsion Systems. [Doctoral Dissertation]. The Ohio State University; 2016. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=osu1468426881

Texas A&M University

10. Coles, Taylor Marie. Computational Nuclear Forensics Analysis of Weapons-grade Plutonium Separated from Fuel Irradiated in a Thermal Reactor.

Degree: MS, Nuclear Engineering, 2014, Texas A&M University

URL: http://hdl.handle.net/1969.1/152706

► The objective of this thesis work is to utilize computational models to reliably predict the intrinsic signature of the weapons-grade plutonium separated from a Pressurized… (more)

▼ The objective of this thesis work is to utilize computational models to reliably predict the intrinsic signature of the weapons-grade plutonium separated from a Pressurized Heavy Water Reactor (PHWR), specifically an Indian 220 MWe PHWR. The PHWR produced weapons-grade plutonium due to the low-burnup seen by the fuel in the computational model. The computational modeling for this project was completed using MCNPX-2.7 radiation transport code. MCNPX-2.7 was used to perform burnup calculations for the PHWR in able to determine the resulting isotopic makeup of actinides and trace elements found in the discharged fuel. The discharged fuel of interest was a single bundle of natural uranium fuel which had undergone a burnup of about 1 GWd/tU. During the PHWR core burnup simulation, certain fuel channels were reshuffled and replaced with a number of new or "fresh" fuel bundles to simulate the process of refueling the reactor; however, it was later determined that utilizing a computational model of a single bundle with reflective boundary conditions on all sides was sufficient in producing the necessary data. That single bundle was burnt to the desired burnup and the final fuel composition of that bundle was used in the isotopic analysis. The specific fission products and actinides selected for this analysis were chosen based upon five parameters; the amount of production, half-life, activity, probability of detection, and the Plutonium Uranium Extraction Process (PUREX) decontamination factor. An uncertainty analysis associated with Monte Carlo methodology was completed using the computational model to predict the mean and standard deviation of the amount of production from the PHWR. Ratios of the selected isotopes concentrations and activities per 1 Kg of total plutonium with a decontamination factor of 106 were calculated for the PHWR. The intrinsic signature of the PHWR was also compared to that from a Fast Breeder Reactor (FBR), and a ratio of the PHWR results to the FBR results was completed to determine if noticeable differences could be seen between the two reactor types, hence, proving the existence of identifyable intrinsic physical signatures in separated weapons-grade plutonium produced by differing reactor types. Ultimately, if smuggled weapons-grade plutonium is intercepted, an analysis of isotopic signatures would be able to attribute the material back to a source reactor. The future work would include experimental data collected after single fuel pellets of natural uranium fuel have been irradiated to the desired burnup in the Oak Ridge National Laboratory- High Flux Isotope Reactor (ORNL-HFIR), and then separated using the PUREX process to experimentally determine the intrinsic signature of the fuel. The experimental data is not yet available. Advisors/Committee Members: Chirayath, Sunil S (advisor), Bangerth, Wolfgang (committee member), Charlton, William S (committee member).

Subjects/Keywords: Nuclear; forensics; thermal; plutonium; weapons-grade

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APA (6^th Edition):

Coles, T. M. (2014). Computational Nuclear Forensics Analysis of Weapons-grade Plutonium Separated from Fuel Irradiated in a Thermal Reactor. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/152706

Chicago Manual of Style (16^th Edition):

Coles, Taylor Marie. “Computational Nuclear Forensics Analysis of Weapons-grade Plutonium Separated from Fuel Irradiated in a Thermal Reactor.” 2014. Masters Thesis, Texas A&M University. Accessed March 04, 2021. http://hdl.handle.net/1969.1/152706.

MLA Handbook (7^th Edition):

Coles, Taylor Marie. “Computational Nuclear Forensics Analysis of Weapons-grade Plutonium Separated from Fuel Irradiated in a Thermal Reactor.” 2014. Web. 04 Mar 2021.

Vancouver:

Coles TM. Computational Nuclear Forensics Analysis of Weapons-grade Plutonium Separated from Fuel Irradiated in a Thermal Reactor. [Internet] [Masters thesis]. Texas A&M University; 2014. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1969.1/152706.

Council of Science Editors:

Coles TM. Computational Nuclear Forensics Analysis of Weapons-grade Plutonium Separated from Fuel Irradiated in a Thermal Reactor. [Masters Thesis]. Texas A&M University; 2014. Available from: http://hdl.handle.net/1969.1/152706

University of Saskatchewan

11. Oladimeji, Dotun J 1989-. Thermal Conductivity of Nuclear Fuel and its Degradation by Physical and Chemical Burnup.

Degree: 2017, University of Saskatchewan

URL: http://hdl.handle.net/10388/8024

► Nuclear fuel performance during reactor operation has been studied using both atomic scale simulation and experimental procedure in order to investigate how nuclear fission process… (more)

▼ Nuclear fuel performance during reactor operation has been studied using both atomic scale simulation and experimental procedure in order to investigate how nuclear fission process affects both the physical state and the chemistry of the fuel. Attention has been drawn to the consequences of nuclear exposure after Fukushima nuclear accident, as it relates to the impact of modern reactor design and nuclear fuel performance. With the recognition of the inherent risks associated with pure uranium oxide (UO2) fuel reactors, there is a need to study nuclear fuel with a view to highlighting their susceptibility to reactor accident, hence, developing an accident tolerant fuel. In this work, cerium oxide (CeO2) has been deployed as a surrogate material for UO2 fuel due to their uniquely similar physicochemical behaviors as fuel materials during operations of nuclear reactors. CeO2 is, however, non-radioactive. The nuclear reactor safety analysis revealed that thermal conductivity is an important property of nuclear fuel because it controls fuel operating temperature and therefore influences its safety. In line with this assertion, two key areas of focus have been identified in this investigation: i) degradation of thermal conductivity by structural and fission products in nuclear fuel and ii) the fuel microstructural evolution due to dissolved fission product. The former has been carried out using molecular dynamics (MD) simulations and analytical models over the full range of temperature of interest while the latter was carried out using both experimental procedure and MD simulations. MD simulations of the structural and thermal properties of CeO2 as a representative of UO2 fuel were carried out using Large-scale Atomic/Molecular Massively Parallel Simulator (LAMMPS) code. The thermal expansion, thermal conductivity, and oxygen ion diffusion were calculated using classical ionic potential models. During these processes, verification of methods was done to establish the best potential for CeO2. The many-body ionic potential in the Embedded Atom Method (EAM) and two-body force field potentials were used to predict lattice parameters and thermal conductivity. Nuclear fuel efficiency changes during reactor operation because of irradiation process. Fission products like fission gas bubble, pores, cracks, dissolved and precipitated fission product buildup in the fuel matrix. The effect of physical burnup such as porosity on the thermophysical properties of CeO2 was simulated using a large system with thousands of atoms. Pores were induced on the large CeO2 system by carefully removing an appropriate number of atoms in proper proportion to mimic porosity evolution. Lattice parameter and the thermal conductivity were calculated at a different percentage of porosity for CeO2. This calculation relates the degradation of thermal conductivity with a number of pores and increasing temperature. In irradiated oxide fuels (UO2 and PuO2), several fission products (FP) are produced and they take various chemical states depending on the… Advisors/Committee Members: Szpunar, Jerzy, Szpunar, Barbara, Powel, Rob, Koustov, Alexandre, Ghezelbash, Masoud, Boulfiza, Mohamed.

Subjects/Keywords: Nuclear Fuel; Molecular Dynamics; Thermal conductivity

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APA (6^th Edition):

Oladimeji, D. J. 1. (2017). Thermal Conductivity of Nuclear Fuel and its Degradation by Physical and Chemical Burnup. (Thesis). University of Saskatchewan. Retrieved from http://hdl.handle.net/10388/8024

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Oladimeji, Dotun J 1989-. “Thermal Conductivity of Nuclear Fuel and its Degradation by Physical and Chemical Burnup.” 2017. Thesis, University of Saskatchewan. Accessed March 04, 2021. http://hdl.handle.net/10388/8024.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Oladimeji, Dotun J 1989-. “Thermal Conductivity of Nuclear Fuel and its Degradation by Physical and Chemical Burnup.” 2017. Web. 04 Mar 2021.

Vancouver:

Oladimeji DJ1. Thermal Conductivity of Nuclear Fuel and its Degradation by Physical and Chemical Burnup. [Internet] [Thesis]. University of Saskatchewan; 2017. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/10388/8024.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Oladimeji DJ1. Thermal Conductivity of Nuclear Fuel and its Degradation by Physical and Chemical Burnup. [Thesis]. University of Saskatchewan; 2017. Available from: http://hdl.handle.net/10388/8024

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Georgia Tech

12. Huning, Alexander Jared. A novel core analysis method for prismatic high temperature gas reactors.

Degree: PhD, Mechanical Engineering, 2016, Georgia Tech

URL: http://hdl.handle.net/1853/58615

► A new transient thermal hydraulic method for simulating prismatic HTGRs during a loss-of-forced-circulation (LOFC) accident is presented. This expands upon the steady state thermal hydraulic… (more)

Subjects/Keywords: HTGR; Thermal hydraulics; Reactor analysis; Nuclear safety

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APA (6^th Edition):

Huning, A. J. (2016). A novel core analysis method for prismatic high temperature gas reactors. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/58615

Chicago Manual of Style (16^th Edition):

Huning, Alexander Jared. “A novel core analysis method for prismatic high temperature gas reactors.” 2016. Doctoral Dissertation, Georgia Tech. Accessed March 04, 2021. http://hdl.handle.net/1853/58615.

MLA Handbook (7^th Edition):

Huning, Alexander Jared. “A novel core analysis method for prismatic high temperature gas reactors.” 2016. Web. 04 Mar 2021.

Vancouver:

Huning AJ. A novel core analysis method for prismatic high temperature gas reactors. [Internet] [Doctoral dissertation]. Georgia Tech; 2016. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1853/58615.

Council of Science Editors:

Huning AJ. A novel core analysis method for prismatic high temperature gas reactors. [Doctoral Dissertation]. Georgia Tech; 2016. Available from: http://hdl.handle.net/1853/58615

University of South Carolina

13. Sentell, Jr., Dennis Shannon. Application of Computational Fluid Dynamics Methods to Improve Thermal Hydraulic Code Analysis.

Degree: PhD, Nuclear Engineering, 2013, University of South Carolina

URL: https://scholarcommons.sc.edu/etd/2369

► A computational fluid dynamics code is used to model the primary natural circulation loop of a proposed small modular reactor for comparison to experimental… (more)

Subjects/Keywords: Engineering; Nuclear Engineering; COMSOL; thermal-hydraulics; TRACE

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APA (6^th Edition):

Sentell, Jr., D. S. (2013). Application of Computational Fluid Dynamics Methods to Improve Thermal Hydraulic Code Analysis. (Doctoral Dissertation). University of South Carolina. Retrieved from https://scholarcommons.sc.edu/etd/2369

Chicago Manual of Style (16^th Edition):

Sentell, Jr., Dennis Shannon. “Application of Computational Fluid Dynamics Methods to Improve Thermal Hydraulic Code Analysis.” 2013. Doctoral Dissertation, University of South Carolina. Accessed March 04, 2021. https://scholarcommons.sc.edu/etd/2369.

MLA Handbook (7^th Edition):

Sentell, Jr., Dennis Shannon. “Application of Computational Fluid Dynamics Methods to Improve Thermal Hydraulic Code Analysis.” 2013. Web. 04 Mar 2021.

Vancouver:

Sentell, Jr. DS. Application of Computational Fluid Dynamics Methods to Improve Thermal Hydraulic Code Analysis. [Internet] [Doctoral dissertation]. University of South Carolina; 2013. [cited 2021 Mar 04]. Available from: https://scholarcommons.sc.edu/etd/2369.

Council of Science Editors:

Sentell, Jr. DS. Application of Computational Fluid Dynamics Methods to Improve Thermal Hydraulic Code Analysis. [Doctoral Dissertation]. University of South Carolina; 2013. Available from: https://scholarcommons.sc.edu/etd/2369

Penn State University

14. Ferreira F Sessim, Marina. MESOSCALE SIMULATIONS OF THERMAL TRANSPORT IN W-UO2 CERMET FUEL FOR NUCLEAR THERMAL PROPULSION.

Degree: 2017, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/14809mvf5410

► Nuclear thermal propulsion (NTP) provides constant power for long space missions, which is a tremendous benefit over chemical rockets. Therefore, a lot of effort in… (more)

Subjects/Keywords: Nuclear Thermal Propulsion; CERMET; Thermal Conductivity; Heat Conduction; Tungsten; Uranium Dioxide; W-UO2; Nuclear Fuel

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APA (6^th Edition):

Ferreira F Sessim, M. (2017). MESOSCALE SIMULATIONS OF THERMAL TRANSPORT IN W-UO2 CERMET FUEL FOR NUCLEAR THERMAL PROPULSION. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/14809mvf5410

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ferreira F Sessim, Marina. “MESOSCALE SIMULATIONS OF THERMAL TRANSPORT IN W-UO2 CERMET FUEL FOR NUCLEAR THERMAL PROPULSION.” 2017. Thesis, Penn State University. Accessed March 04, 2021. https://submit-etda.libraries.psu.edu/catalog/14809mvf5410.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ferreira F Sessim, Marina. “MESOSCALE SIMULATIONS OF THERMAL TRANSPORT IN W-UO2 CERMET FUEL FOR NUCLEAR THERMAL PROPULSION.” 2017. Web. 04 Mar 2021.

Vancouver:

Ferreira F Sessim M. MESOSCALE SIMULATIONS OF THERMAL TRANSPORT IN W-UO2 CERMET FUEL FOR NUCLEAR THERMAL PROPULSION. [Internet] [Thesis]. Penn State University; 2017. [cited 2021 Mar 04]. Available from: https://submit-etda.libraries.psu.edu/catalog/14809mvf5410.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ferreira F Sessim M. MESOSCALE SIMULATIONS OF THERMAL TRANSPORT IN W-UO2 CERMET FUEL FOR NUCLEAR THERMAL PROPULSION. [Thesis]. Penn State University; 2017. Available from: https://submit-etda.libraries.psu.edu/catalog/14809mvf5410

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Michigan

15. Poston, David Irvin. A computational model for an open-cycle gas core nuclear rocket.

Degree: PhD, Nuclear engineering, 1994, University of Michigan

URL: http://hdl.handle.net/2027.42/129380

► A computational model of an open-cycle Gas Core Nuclear Rocket (GCR) is developed. The model evaluates the rocket performance of an open-cycle GCR as a… (more)

▼ A computational model of an open-cycle Gas Core Nuclear Rocket (GCR) is developed. The model evaluates the rocket performance of an open-cycle GCR as a function of design and operational parameters. The primary output of the model is the specific impulse and thrust of the rocket. The solution is divided into two distinct areas – thermal-hydraulics and neutronics. To obtain the thermal-hydraulic solution, a computer code is written which solves the Navier-Stokes, energy, and species diffusion equations. A spatially implicit solution is obtained by a direct solver that is developed specifically for the code. The two-dimensional transport code TWODANT is used to obtain the neutronics solution. The important requirements of the neutronics model are the ability to handle neutron upscattering and a highly inhomogeneous mesh. The thermal-hydraulic and neutronic models are coupled, and the solution proceeds in an iterative manner until a consistent power density profile is obtained. Various open-cycle gas core nuclear rocket designs are evaluated. First, it is assumed that the fuel and propellant do not mix. In this ideal case, it is found that the limiting factor in determining thrust and specific impulse is the maximum allowable wall heat flux. Next, a neutronic study is performed on a simplified homogeneous open-cycle GCR design. The effect of changing the fuel/propellant densities and temperatures on the multiplication factor k-eff is studied, as is the use of alternate fuels and propellants. Following this simplified neutronic study, the results from a complete thermal-hydraulic/neutronic solution are presented. The thermodynamic and nuclear properties of the reactor are studied in detail, particularly density and neutron flux. These results provide insight into the underlying physics of an open-cycle GCR, as well demonstrate the capabilities of the model. Next, a parametric design study is conducted which examines the rocket performance of the open-cycle GCR as a function of various design and operational parameters. It is found that fuel containment is very adversely effected by high reactor power or rocket acceleration. Finally, some innovative concepts are discussed that could help improve fuel containment. Advisors/Committee Members: Kammash, Terry (advisor).

Subjects/Keywords: Computational; Core; Cycle; Gas; Model; Nuclear; Open; Rocket

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APA (6^th Edition):

Poston, D. I. (1994). A computational model for an open-cycle gas core nuclear rocket. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/129380

Chicago Manual of Style (16^th Edition):

Poston, David Irvin. “A computational model for an open-cycle gas core nuclear rocket.” 1994. Doctoral Dissertation, University of Michigan. Accessed March 04, 2021. http://hdl.handle.net/2027.42/129380.

MLA Handbook (7^th Edition):

Poston, David Irvin. “A computational model for an open-cycle gas core nuclear rocket.” 1994. Web. 04 Mar 2021.

Vancouver:

Poston DI. A computational model for an open-cycle gas core nuclear rocket. [Internet] [Doctoral dissertation]. University of Michigan; 1994. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/2027.42/129380.

Council of Science Editors:

Poston DI. A computational model for an open-cycle gas core nuclear rocket. [Doctoral Dissertation]. University of Michigan; 1994. Available from: http://hdl.handle.net/2027.42/129380

University of Cambridge

16. Lowe, Steven. Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows.

Degree: PhD, 2018, University of Cambridge

URL: https://doi.org/10.17863/CAM.24670 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.744958

► This thesis is concerned with the development and application of laser induced thermal grating spectroscopy (LITGS) as a tool for thermometry in reacting and non-reacting… (more)

▼ This thesis is concerned with the development and application of laser induced thermal grating spectroscopy (LITGS) as a tool for thermometry in reacting and non-reacting flows. LITGS signals, which require resonant excitation of an absorbing species in the measurement region to produce a thermal grating, are acquired for systematic measurements of temperature in high pressure flames using OH and NO as target absorbing species in the burned gas. The signal obtained in LITGS measurements appears in the form of a time-based signal with a characteristic frequency proportional to the value or the sound speed of the local medium. With knowledge of the gas composition, the temperature can be derived from the speed of sound measurement. LITGS thermometry using resonant excitation of OH in the burned gas region of in oxygen enriched CH4/O2/N2 and CH4/air laminar flames was performed at elevated pressure (0.5 MPa) for a range of conditions. Measurements were acquired in oxygen enriched flames to provide an environment in which to demonstrate LITGS thermometry under high temperature conditions (up to 2900 K). The primary parameters that influence the quality of LITGS signal were also investigated. The signal contrast, which acts as a marker for the strength of the frequency oscillations, is shown to increase with an increase in the burnt gas density at the measurement point. LITGS employing resonant excitation of NO is also demonstrated for quantitative measurements of temperature in three environments – a static pressure cell at ambient temperature, a non-reacting heated jet at ambient pressure and a laminar premixed CH4/NH3/air flame operating at 0.5 MPa. Flame temperature measurements were acquired at various locations in the burned gas close to a water-cooled stagnation plate, demonstrating the capability of NO-LITGS thermometry for measuring the spatial distribution of temperature in combustion environments. In addition, the parameters that in influence the local temperature rise due to LITGS were also investigated in continuous vapour flows of acetone/air and toluene/air mixtures at atmospheric conditions. Acetone and toluene are commonly targeted species in previous LITGS measurements due to their favourable absorption characteristics. Results indicate that LITGS has the potential to produce accurate and precise measurements of temperature in non-reacting flows, but that the product of the pump intensity at the probe volume and the absorber concentration must remain relatively low to avoid significant localised heating of the measurement region.

Subjects/Keywords: 621.36; Combustion; Laser; LITGS; Thermal grating; nitric oxide; laser induced thermal grating; spectroscopy; flame; high pressure flames; NO; OH-LITGS; NO-LITGS; acetone; toluene; thermalization; thermalisation; temperature; temperature measurement; thermometry; LIEGS; oxygen enriched; oxygen enrichment; rocket combustion; flat flame; rocket motor; speed of sound; flame physics; laser physics; rocket; jet engine; temperature profile; applied physics; engineering; combustion science; combustion technology

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APA (6^th Edition):

Lowe, S. (2018). Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows. (Doctoral Dissertation). University of Cambridge. Retrieved from https://doi.org/10.17863/CAM.24670 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.744958

Chicago Manual of Style (16^th Edition):

Lowe, Steven. “Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows.” 2018. Doctoral Dissertation, University of Cambridge. Accessed March 04, 2021. https://doi.org/10.17863/CAM.24670 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.744958.

MLA Handbook (7^th Edition):

Lowe, Steven. “Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows.” 2018. Web. 04 Mar 2021.

Vancouver:

Lowe S. Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows. [Internet] [Doctoral dissertation]. University of Cambridge; 2018. [cited 2021 Mar 04]. Available from: https://doi.org/10.17863/CAM.24670 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.744958.

Council of Science Editors:

Lowe S. Quantitative measurements of temperature using laser-induced thermal grating spectroscopy in reacting and non-reacting flows. [Doctoral Dissertation]. University of Cambridge; 2018. Available from: https://doi.org/10.17863/CAM.24670 ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.744958

University of Adelaide

17. Ide, Kym Martin. Thermal and fracture behaviour of rocket motor materials / by Kim Martin Ide.

Degree: 1997, University of Adelaide

URL: http://hdl.handle.net/2440/18971

► This thesis analyses the way in which ageing, temperature and strain-rate affect the thermal and fracture properties of the polymeric components in the PICTOR rocket… (more)

Subjects/Keywords: Thermal stresses.; Rocket engines.; Polymeric composites Thermal properties.; Fracture mechanics.

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APA (6^th Edition):

Ide, K. M. (1997). Thermal and fracture behaviour of rocket motor materials / by Kim Martin Ide. (Thesis). University of Adelaide. Retrieved from http://hdl.handle.net/2440/18971

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Ide, Kym Martin. “Thermal and fracture behaviour of rocket motor materials / by Kim Martin Ide.” 1997. Thesis, University of Adelaide. Accessed March 04, 2021. http://hdl.handle.net/2440/18971.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Ide, Kym Martin. “Thermal and fracture behaviour of rocket motor materials / by Kim Martin Ide.” 1997. Web. 04 Mar 2021.

Vancouver:

Ide KM. Thermal and fracture behaviour of rocket motor materials / by Kim Martin Ide. [Internet] [Thesis]. University of Adelaide; 1997. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/2440/18971.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Ide KM. Thermal and fracture behaviour of rocket motor materials / by Kim Martin Ide. [Thesis]. University of Adelaide; 1997. Available from: http://hdl.handle.net/2440/18971

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Southern California

18. Gilpin, Matthew R. High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites.

Degree: PhD, Aerospace Engineering, 2015, University of Southern California

URL: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/600904/rec/3180

► Solar thermal propulsion (STP) offers an unique combination of thrust and efficiency, providing greater total ΔV capability than chemical propulsion systems without the order of… (more)

▼ Solar thermal propulsion (STP) offers an unique combination of thrust and efficiency, providing greater total ΔV capability than chemical propulsion systems without the order of magnitude increase in total mission duration associated with electric propulsion. Despite an over 50 year development history, no STP spacecraft has flown to‐date as both perceived and actual complexity have overshadowed the potential performance benefit in relation to conventional technologies. The trend in solar thermal research over the past two decades has been towards simplification and miniaturization to overcome this complexity barrier in an effort finally mount an in‐flight test. ❧ A review of micro‐propulsion technologies recently conducted by the Air Force Research Laboratory (AFRL) has identified solar thermal propulsion as a promising configuration for microsatellite missions requiring a substantial ΔV and recommended further study. A STP system provides performance which cannot be matched by conventional propulsion technologies in the context of the proposed microsatellite “inspector" requiring rapid delivery of greater than 1500 m/s ΔV. With this mission profile as the target, the development of an effective STP architecture goes beyond incremental improvements and enables a new class of microsatellite missions. ❧ Here, it is proposed that a bi‐modal solar thermal propulsion system on a microsatellite platform can provide a greater than 50% increase in ΔV vs. chemical systems while maintaining delivery times measured in days. The realization of a microsatellite scale bi‐modal STP system requires the integration of multiple new technologies, and with the exception of high performance thermal energy storage, the long history of STP development has provided “ready" solutions. ❧ For the target bi‐modal STP microsatellite, sensible heat thermal energy storage is insufficient and the development of high temperature latent heat thermal energy storage is an enabling technology for the platform. The use of silicon and boron as high temperature latent heat thermal energy storage materials has been in the background of solar thermal research for decades without a substantial investigation. This is despite a broad agreement in the literature about the performance benefits obtainable from a latent heat mechanisms which provides a high energy storage density and quasi‐isothermal heat release at high temperature. ❧ In this work, an experimental approach was taken to uncover the practical concerns associated specifically with applying silicon as an energy storage material. A new solar furnace was built and characterized enabling the creation of molten silicon in the laboratory. These tests have demonstrated the basic feasibility of a molten silicon based thermal energy storage system and have highlighted asymmetric heat transfer as well as silicon expansion damage to be the primary engineering concerns for the technology. For cylindrical geometries, it has been shown that reduced fill factors can prevent damage to graphite walled silicon… Advisors/Committee Members: Shiflett, Geoffrey R. (Committee Chair), Sadhal, Satwindar S. (Committee Member), Ronney, Paul D. (Committee Member), Erwin, Daniel A. (Committee Member).

Subjects/Keywords: solar thermal; latent heat; thermal energy storage; microsatellites; spacecraft propulsion; advanced propulsion; thermal rocket; molten silicon; liquid silicon; solar furnace; solar concentration; phase change material; molten boron; liquid boron; radiation shielding model; convective coupling; thermal battery; thermal capacitor

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APA (6^th Edition):

Gilpin, M. R. (2015). High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites. (Doctoral Dissertation). University of Southern California. Retrieved from http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/600904/rec/3180

Chicago Manual of Style (16^th Edition):

Gilpin, Matthew R. “High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites.” 2015. Doctoral Dissertation, University of Southern California. Accessed March 04, 2021. http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/600904/rec/3180.

MLA Handbook (7^th Edition):

Gilpin, Matthew R. “High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites.” 2015. Web. 04 Mar 2021.

Vancouver:

Gilpin MR. High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites. [Internet] [Doctoral dissertation]. University of Southern California; 2015. [cited 2021 Mar 04]. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/600904/rec/3180.

Council of Science Editors:

Gilpin MR. High temperature latent heat thermal energy storage to augment solar thermal propulsion for microsatellites. [Doctoral Dissertation]. University of Southern California; 2015. Available from: http://digitallibrary.usc.edu/cdm/compoundobject/collection/p15799coll3/id/600904/rec/3180

Kingston University

19. Karaveckas, Linas. Development of low-cost pressurisation system for rocket engines.

Degree: PhD, 2019, Kingston University

URL: http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357

► Increasing demand for low-cost satellites requires new affordable launch vehicles. Rocket turbopump systems are deemed to be one of the most complex and expensive components… (more)

▼ Increasing demand for low-cost satellites requires new affordable launch vehicles. Rocket turbopump systems are deemed to be one of the most complex and expensive components of conventional rockets, thus cost reduction of these parts is essential to business success. The aim of this research was to evaluate existing rocket turbopumps and identify options for significant cost reductions. Alternative pressurisation options were also considered which could meet low-cost targets for a small satellite launch vehicle. Four pressurisation systems were identified which could meet the requirements for a low-cost launch vehicle were shortlisted for further studies. These were turbopumps, piston pumps, pressure-fed and pistonless pumps. A mass model was developed to estimate the Gross Lift off Mass (GLOM) of the launch vehicle and to carry out a mass sensitivity analysis. Based on these findings, the feasibility of the piston pump was explored for a low-cost launch vehicle. To test the concept and to evaluate the manufacturing techniques, two prototypes were built. The first demonstrator (Mark I) was used to evaluate the feasibility of the valves and to optimise performance. To avoid the complexities associated with cryogenic and oxidising liquids, the tests were carried out with water. Further trials were conducted on the Mark II to assess compatibility at cryogenic temperatures. The prototype has successfully demonstrated that selected components have functioned as intended at low temperatures. Through the process of development, it was determined that the piston pump is a very simple system - only a few parts require a high precision of manufacturing, such as the piston bore and piston. The project novelty and achievement are 1) Various modern pressurisation systems were critically evaluated and it was concluded that a piston pump could offer a low-cost alternative to the turbopump. 2) It was demonstrated that a piston pump could be used in a small launch vehicle, but further work is required to extend the validation. 3) Demonstrators were used to show which components and parts could be used with Liquid Oxygen in small launch vehicles.

Subjects/Keywords: rocket piston pump; rocket pressurisation systems; rocket turbopump; rocket reciprocating pump; low-cost rocket pump

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APA (6^th Edition):

Karaveckas, L. (2019). Development of low-cost pressurisation system for rocket engines. (Doctoral Dissertation). Kingston University. Retrieved from http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357

Chicago Manual of Style (16^th Edition):

Karaveckas, Linas. “Development of low-cost pressurisation system for rocket engines.” 2019. Doctoral Dissertation, Kingston University. Accessed March 04, 2021. http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357.

MLA Handbook (7^th Edition):

Karaveckas, Linas. “Development of low-cost pressurisation system for rocket engines.” 2019. Web. 04 Mar 2021.

Vancouver:

Karaveckas L. Development of low-cost pressurisation system for rocket engines. [Internet] [Doctoral dissertation]. Kingston University; 2019. [cited 2021 Mar 04]. Available from: http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357.

Council of Science Editors:

Karaveckas L. Development of low-cost pressurisation system for rocket engines. [Doctoral Dissertation]. Kingston University; 2019. Available from: http://eprints.kingston.ac.uk/id/eprint/43962/ ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789357

Colorado School of Mines

20. Teague, Melissa Christine. Characterization and modeling of high burn-up mixed oxide fuel.

Degree: PhD, Metallurgical and Materials Engineering, 2013, Colorado School of Mines

URL: http://hdl.handle.net/11124/78991

► Currently, fast reactor performance is largely constrained by the limitations of the materials involved in these reactors. The fuel is particularly limiting due to fission… (more)

Subjects/Keywords: thermal conductivity; MOX; high burn-up; Nuclear fuels – Thermal conductivity; Nuclear fuel claddings; Irradiation; Sodium cooled reactors

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APA (6^th Edition):

Teague, M. C. (2013). Characterization and modeling of high burn-up mixed oxide fuel. (Doctoral Dissertation). Colorado School of Mines. Retrieved from http://hdl.handle.net/11124/78991

Chicago Manual of Style (16^th Edition):

Teague, Melissa Christine. “Characterization and modeling of high burn-up mixed oxide fuel.” 2013. Doctoral Dissertation, Colorado School of Mines. Accessed March 04, 2021. http://hdl.handle.net/11124/78991.

MLA Handbook (7^th Edition):

Teague, Melissa Christine. “Characterization and modeling of high burn-up mixed oxide fuel.” 2013. Web. 04 Mar 2021.

Vancouver:

Teague MC. Characterization and modeling of high burn-up mixed oxide fuel. [Internet] [Doctoral dissertation]. Colorado School of Mines; 2013. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/11124/78991.

Council of Science Editors:

Teague MC. Characterization and modeling of high burn-up mixed oxide fuel. [Doctoral Dissertation]. Colorado School of Mines; 2013. Available from: http://hdl.handle.net/11124/78991

University of Kentucky

21. Sparks, James Devin. The Kentucky Re-entry Universal Payload System (KRUPS): Sub-orbital Flights.

Degree: 2018, University of Kentucky

URL: https://uknowledge.uky.edu/me_etds/123

► The Kentucky Re-entry Universal Payload System (KRUPS) is an adaptable testbed for atmosphere entry science experiments, with an initial application to thermal protection systems (TPS).… (more)

Subjects/Keywords: Thermal Protection System (TPS); Sounding Rocket; International Space Station (ISS); Re-entry Vehicle; Aviation and Space Education; Computer-Aided Engineering and Design; Heat Transfer, Combustion; Manufacturing

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APA (6^th Edition):

Sparks, J. D. (2018). The Kentucky Re-entry Universal Payload System (KRUPS): Sub-orbital Flights. (Masters Thesis). University of Kentucky. Retrieved from https://uknowledge.uky.edu/me_etds/123

Chicago Manual of Style (16^th Edition):

Sparks, James Devin. “The Kentucky Re-entry Universal Payload System (KRUPS): Sub-orbital Flights.” 2018. Masters Thesis, University of Kentucky. Accessed March 04, 2021. https://uknowledge.uky.edu/me_etds/123.

MLA Handbook (7^th Edition):

Sparks, James Devin. “The Kentucky Re-entry Universal Payload System (KRUPS): Sub-orbital Flights.” 2018. Web. 04 Mar 2021.

Vancouver:

Sparks JD. The Kentucky Re-entry Universal Payload System (KRUPS): Sub-orbital Flights. [Internet] [Masters thesis]. University of Kentucky; 2018. [cited 2021 Mar 04]. Available from: https://uknowledge.uky.edu/me_etds/123.

Council of Science Editors:

Sparks JD. The Kentucky Re-entry Universal Payload System (KRUPS): Sub-orbital Flights. [Masters Thesis]. University of Kentucky; 2018. Available from: https://uknowledge.uky.edu/me_etds/123

University of New Mexico

22. Talley, Darren G. Investigation of the Coupled Nuclear, Thermal-Hydraulic, and Thermomechanical Response of a Natural Circulation Research Reactor Under Severe Reactivity-Initiated Accident Transients.

Degree: Mechanical Engineering, 2019, University of New Mexico

URL: https://digitalrepository.unm.edu/me_etds/167

► Research reactors play an important role in higher education, scientific research, and medical radioisotope production around the world. It is thus important to ensure… (more)

Subjects/Keywords: research reactor; safety analysis; reactor kinetics; thermal-hydraulics; thermal expansion; thermal stress; Mechanical Engineering; Nuclear Engineering

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APA (6^th Edition):

Talley, D. G. (2019). Investigation of the Coupled Nuclear, Thermal-Hydraulic, and Thermomechanical Response of a Natural Circulation Research Reactor Under Severe Reactivity-Initiated Accident Transients. (Doctoral Dissertation). University of New Mexico. Retrieved from https://digitalrepository.unm.edu/me_etds/167

Chicago Manual of Style (16^th Edition):

Talley, Darren G. “Investigation of the Coupled Nuclear, Thermal-Hydraulic, and Thermomechanical Response of a Natural Circulation Research Reactor Under Severe Reactivity-Initiated Accident Transients.” 2019. Doctoral Dissertation, University of New Mexico. Accessed March 04, 2021. https://digitalrepository.unm.edu/me_etds/167.

MLA Handbook (7^th Edition):

Talley, Darren G. “Investigation of the Coupled Nuclear, Thermal-Hydraulic, and Thermomechanical Response of a Natural Circulation Research Reactor Under Severe Reactivity-Initiated Accident Transients.” 2019. Web. 04 Mar 2021.

Vancouver:

Talley DG. Investigation of the Coupled Nuclear, Thermal-Hydraulic, and Thermomechanical Response of a Natural Circulation Research Reactor Under Severe Reactivity-Initiated Accident Transients. [Internet] [Doctoral dissertation]. University of New Mexico; 2019. [cited 2021 Mar 04]. Available from: https://digitalrepository.unm.edu/me_etds/167.

Council of Science Editors:

Talley DG. Investigation of the Coupled Nuclear, Thermal-Hydraulic, and Thermomechanical Response of a Natural Circulation Research Reactor Under Severe Reactivity-Initiated Accident Transients. [Doctoral Dissertation]. University of New Mexico; 2019. Available from: https://digitalrepository.unm.edu/me_etds/167

23. Singh, Sajan B. A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core.

Degree: MS, Mechanical Engineering, 2013, University of New Orleans

URL: https://scholarworks.uno.edu/td/1766

► Two mathematical models (a one and a three-dimensional) were adopted to study, numerically, the thermal hydrodynamic behavior of flow inside a single cooling channel… (more)

Subjects/Keywords: Nuclear; Rocket; Temperature; Velocity; Model; Heat Transfer, Combustion; Mechanical Engineering

…Thermal Rocket (NTR) engine. The first model assumes the flow in the cooling channel… …in a Nuclear Thermal Rocket engine. For this purpose, the existing one-dimensional and… …simulators to test candidate fuel elements for NTRs under the program called Nuclear Thermal Rocket… …Chapter 2 Literature Survey Thermohydraulic and Neutronic modeling of nuclear thermal rocket… …also predicted the steady-state Mach number distribution for a generic Nuclear Thermal Rocket…

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APA (6^th Edition):

Singh, S. B. (2013). A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core. (Thesis). University of New Orleans. Retrieved from https://scholarworks.uno.edu/td/1766

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Singh, Sajan B. “A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core.” 2013. Thesis, University of New Orleans. Accessed March 04, 2021. https://scholarworks.uno.edu/td/1766.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Singh, Sajan B. “A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core.” 2013. Web. 04 Mar 2021.

Vancouver:

Singh SB. A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core. [Internet] [Thesis]. University of New Orleans; 2013. [cited 2021 Mar 04]. Available from: https://scholarworks.uno.edu/td/1766.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Singh SB. A Numerical Study of High Temperature and High Velocity Gaseous Hydrogen Flow in a Cooling Channel of a NTR Core. [Thesis]. University of New Orleans; 2013. Available from: https://scholarworks.uno.edu/td/1766

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Tennessee – Knoxville

24. DeVoe, Remy Russell. Sensitivity Analysis of Fuel Cladding Temperature to Dry Cask Loading and Storage Conditions.

Degree: MS, Nuclear Engineering, 2015, University of Tennessee – Knoxville

URL: https://trace.tennessee.edu/utk_gradthes/3469

► Dry cask safety analyses and material degradation studies depend on reliable best- estimate thermal models. Gaps in design data and storage site conditions require… (more)

Subjects/Keywords: Thermal Modeling; Used Nuclear Fuel; Sensitivity Analysis; Nuclear Reactors; Dry Cask Storage; MAGNASTOR; Cladding Temperature; Nuclear Engineering

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APA (6^th Edition):

DeVoe, R. R. (2015). Sensitivity Analysis of Fuel Cladding Temperature to Dry Cask Loading and Storage Conditions. (Thesis). University of Tennessee – Knoxville. Retrieved from https://trace.tennessee.edu/utk_gradthes/3469

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

DeVoe, Remy Russell. “Sensitivity Analysis of Fuel Cladding Temperature to Dry Cask Loading and Storage Conditions.” 2015. Thesis, University of Tennessee – Knoxville. Accessed March 04, 2021. https://trace.tennessee.edu/utk_gradthes/3469.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

DeVoe, Remy Russell. “Sensitivity Analysis of Fuel Cladding Temperature to Dry Cask Loading and Storage Conditions.” 2015. Web. 04 Mar 2021.

Vancouver:

DeVoe RR. Sensitivity Analysis of Fuel Cladding Temperature to Dry Cask Loading and Storage Conditions. [Internet] [Thesis]. University of Tennessee – Knoxville; 2015. [cited 2021 Mar 04]. Available from: https://trace.tennessee.edu/utk_gradthes/3469.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

DeVoe RR. Sensitivity Analysis of Fuel Cladding Temperature to Dry Cask Loading and Storage Conditions. [Thesis]. University of Tennessee – Knoxville; 2015. Available from: https://trace.tennessee.edu/utk_gradthes/3469

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Michigan State University

25. Pang, Gregory Keith. Development of radiofrequency carpets for ion transport at the NSCL.

Degree: 2011, Michigan State University

URL: http://etd.lib.msu.edu/islandora/object/etd:54

►

Thesis Ph. D. Michigan State University. Chemistry 2011.

The low-energy research program at the NSCL is dependent on gas thermalization techniques to convert the energetic… (more)

Subjects/Keywords: National Superconducting Cyclotron Laboratory (U.S.); Nuclear physics; Cyclotrons; Particles (Nuclear physics); Particle accelerators; Thermal neutrons; Ion flow dynamics; Nuclear chemistry

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APA (6^th Edition):

Pang, G. K. (2011). Development of radiofrequency carpets for ion transport at the NSCL. (Thesis). Michigan State University. Retrieved from http://etd.lib.msu.edu/islandora/object/etd:54

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Pang, Gregory Keith. “Development of radiofrequency carpets for ion transport at the NSCL.” 2011. Thesis, Michigan State University. Accessed March 04, 2021. http://etd.lib.msu.edu/islandora/object/etd:54.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Pang, Gregory Keith. “Development of radiofrequency carpets for ion transport at the NSCL.” 2011. Web. 04 Mar 2021.

Vancouver:

Pang GK. Development of radiofrequency carpets for ion transport at the NSCL. [Internet] [Thesis]. Michigan State University; 2011. [cited 2021 Mar 04]. Available from: http://etd.lib.msu.edu/islandora/object/etd:54.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Pang GK. Development of radiofrequency carpets for ion transport at the NSCL. [Thesis]. Michigan State University; 2011. Available from: http://etd.lib.msu.edu/islandora/object/etd:54

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of KwaZulu-Natal

26. Balmogim, Udil. Design and development of the Phoenix-1B hybrid rocket.

Degree: 2017, University of KwaZulu-Natal

URL: http://hdl.handle.net/10413/16062

► In August 2014, South Africa’s first university-based hybrid rocket, Phoenix-1A, was launched at the Overberg Test Range near Cape Agulhas. The vehicle suffered nozzle and… (more)

▼ In August 2014, South Africa’s first university-based hybrid rocket, Phoenix-1A, was launched at the Overberg Test Range near Cape Agulhas. The vehicle suffered nozzle and parachute failures during flight which, together with a reduced oxidiser load, reduced the nominal design apogee of 10 km to 2.5 km. The aim of this research was to improve on the design and performance of the prototype demonstrator and thereby develop a workhorse hybrid sounding rocket, named Phoenix-1B, to serve as a reliable platform for future hybrid rocket research at the University of KwaZulu-Natal (UKZN). Analysis of Phoenix-1A shortcomings served as the starting point for the new design, which utilises a paraffin wax and nitrous oxide propellant combination. The focus of this research was the propulsion system, with specific attention being paid to the nozzle and injector designs. In addition, an aerodynamic study was applied to the 1 m long ¾ parabolic nose cone and four tapered swept fins. Final design of the aluminium oxidiser tank and combustion chamber bulkheads incorporated finite element analyses to ensure an operational safety factor greater than 1.5. The oxidiser tank and combustion chamber assemblies were pressure tested to 80 and 60 bars respectively. A key output of the present work is an analysis of the effect of aluminium loading in the paraffin wax fuel grain, which indicated a potential rocket mass reduction of 23 kg when transitioning from a pure paraffin grain to one containing 40% aluminium by mass. The analysis also indicated that combustion temperature rises with aluminium loading, increasing from 3300 K for pure paraffin to 3600 K for 40% aluminised fuel. Consequently, an iterative transient thermo-structural analysis was conducted on the nozzle, resulting in an optimised design able to sustain the higher operating temperatures as well as mitigate the risk of failure as seen with Phoenix-1A. The final manufactured composite nozzle has a throat diameter of 32 mm, an expansion ratio of 6.38, and a length of 156 mm. The nozzle has a steel casing which provides structural support to the silica phenolic insulation and graphite throat insert. A two phase CFD analysis, coupled with analytical mass flow rate models, was used to configure the axial injector and reduce the potential for combustion instabilities associated with the nitrous oxide flow. The Phoenix-1B motor has a design thrust of 5 kN to propel the fully loaded vehicle, with a mass of 70 kg, a length of 4.3 m and a diameter of 164 mm, to an altitude of 16 km. Advisors/Committee Members: Brooks, Michael John. (advisor), Veale, Kirsty Lynn. (advisor), De La Beaujardiere, Jean-Francois Pitot. (advisor).

Subjects/Keywords: Rocket design.; Rocket engine.; Hybrid rocket.; Pheonix-1B hybrid rocket.; Hybrid propultasion system.

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APA (6^th Edition):

Balmogim, U. (2017). Design and development of the Phoenix-1B hybrid rocket. (Thesis). University of KwaZulu-Natal. Retrieved from http://hdl.handle.net/10413/16062

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Balmogim, Udil. “Design and development of the Phoenix-1B hybrid rocket.” 2017. Thesis, University of KwaZulu-Natal. Accessed March 04, 2021. http://hdl.handle.net/10413/16062.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Balmogim, Udil. “Design and development of the Phoenix-1B hybrid rocket.” 2017. Web. 04 Mar 2021.

Vancouver:

Balmogim U. Design and development of the Phoenix-1B hybrid rocket. [Internet] [Thesis]. University of KwaZulu-Natal; 2017. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/10413/16062.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Balmogim U. Design and development of the Phoenix-1B hybrid rocket. [Thesis]. University of KwaZulu-Natal; 2017. Available from: http://hdl.handle.net/10413/16062

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Oregon State University

27. Willison, James Stuart. Thermal conductivity modeling of unrestructured sphere pac nuclear fuels.

Degree: MS, Nuclear Engineering, 1981, Oregon State University

URL: http://hdl.handle.net/1957/41979

► In order to properly model the temperature distribution of a nuclear fuel pin, the thermal conductivity of the fuel must be known. For sphere pac… (more)

Subjects/Keywords: Nuclear fuel rods – Thermal properties

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APA (6^th Edition):

Willison, J. S. (1981). Thermal conductivity modeling of unrestructured sphere pac nuclear fuels. (Masters Thesis). Oregon State University. Retrieved from http://hdl.handle.net/1957/41979

Chicago Manual of Style (16^th Edition):

Willison, James Stuart. “Thermal conductivity modeling of unrestructured sphere pac nuclear fuels.” 1981. Masters Thesis, Oregon State University. Accessed March 04, 2021. http://hdl.handle.net/1957/41979.

MLA Handbook (7^th Edition):

Willison, James Stuart. “Thermal conductivity modeling of unrestructured sphere pac nuclear fuels.” 1981. Web. 04 Mar 2021.

Vancouver:

Willison JS. Thermal conductivity modeling of unrestructured sphere pac nuclear fuels. [Internet] [Masters thesis]. Oregon State University; 1981. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1957/41979.

Council of Science Editors:

Willison JS. Thermal conductivity modeling of unrestructured sphere pac nuclear fuels. [Masters Thesis]. Oregon State University; 1981. Available from: http://hdl.handle.net/1957/41979

Texas A&M University

28. Blamer, Brandon James. Characterization of Uranium Metal Alloy Fuel Forms for Advanced Nuclear Reactor Applications.

Degree: PhD, Nuclear Engineering, 2017, Texas A&M University

URL: http://hdl.handle.net/1969.1/187179

► An engineering investigation of the fabrication process for low smear density uranium alloy nuclear fuel forms was completed and the resulting alloys were characterized. The… (more)

▼ An engineering investigation of the fabrication process for low smear density uranium alloy nuclear fuel forms was completed and the resulting alloys were characterized. The metal fuel alloys investigated in this project were uranium metal, uranium – 5 wt% zirconium (U-5Zr), and uranium – 10 wt% zirconium (U-10Zr). The physical fuel forms of interest included 1) dense, solid rods that could be used be used in low smear density nuclear fuel applications, 2) extruded tubes designed to begin fuel service in constant contact with cladding yet having a low smear density, and 3) low density pellets designed to simulate low density fuel structures. Extrusion was shown to be an industrially viable option for the production of uranium and U-10Zr rods and tubes. Extrusion experiments were performed in the uranium alpha phase in the temperatures range of 550 to 650°C. The reduction ratio was varied between 4 and 15. The extrusion constant, K, was empirically estimated from the data collected and ranged from 45 to 160 ksi over the course of this study. Larger extrusion ratios as well as higher temperatures resulted in lower extrusion constants. The microstructures of the extruded products were studied using scanning electron microscopy and neutron diffraction. The specimens exhibited elongated grains in the extrusion direction. The U-10Zr also displayed aligned and elongated α zirconium grains. Neutron diffraction of the U-10Zr product revealed α uranium texture in the (100) and (110) direction as well as δ-UZr2 texture in the (0001) direction. The δ-UZr2 texture was found to persist through high temperature heat treatment, but the α uranium texture did not. To examine low density porous alloys, U, U-5Zr, and U-10Zr powders were fabricated with a range of densities from ~45 to ~89 %TD. The resulting alloy microstructures were characterized via scanning electron microscopy. The structures of the pellets were typically homogeneous. The microstructures created were similar to the microstructures of fuel that has undergone irradiation swelling. The porosity-dependent thermal diffusivity of the alloys was measured in the temperatures range of 20 to 300ºC. As sample porosity increased, the diffusivity was observed to decrease linearly over the entire sample set. Diffusivity values for uranium ranged from 10.7 mm²/s at 88.6 %TD and 300ºC to 2.54 mm²/s at 46.6 %TD and 30ºC. The empirical relationship between the thermal conductivity and porosity corresponded well with the predicted values from the effective medium theory structural model for modelling the thermal conductivity of two phase materials. Advisors/Committee Members: McDeavitt, Sean (advisor), Tsvetkov, Pavel (committee member), Cagin, Tahir (committee member), Perez-Nunez, Delia (committee member), Ortega, Luis (committee member).

Subjects/Keywords: uranium; U-10Zr; nuclear fuel; porosity; thermal diffusivity; extrusion

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APA (6^th Edition):

Blamer, B. J. (2017). Characterization of Uranium Metal Alloy Fuel Forms for Advanced Nuclear Reactor Applications. (Doctoral Dissertation). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/187179

Chicago Manual of Style (16^th Edition):

Blamer, Brandon James. “Characterization of Uranium Metal Alloy Fuel Forms for Advanced Nuclear Reactor Applications.” 2017. Doctoral Dissertation, Texas A&M University. Accessed March 04, 2021. http://hdl.handle.net/1969.1/187179.

MLA Handbook (7^th Edition):

Blamer, Brandon James. “Characterization of Uranium Metal Alloy Fuel Forms for Advanced Nuclear Reactor Applications.” 2017. Web. 04 Mar 2021.

Vancouver:

Blamer BJ. Characterization of Uranium Metal Alloy Fuel Forms for Advanced Nuclear Reactor Applications. [Internet] [Doctoral dissertation]. Texas A&M University; 2017. [cited 2021 Mar 04]. Available from: http://hdl.handle.net/1969.1/187179.

Council of Science Editors:

Blamer BJ. Characterization of Uranium Metal Alloy Fuel Forms for Advanced Nuclear Reactor Applications. [Doctoral Dissertation]. Texas A&M University; 2017. Available from: http://hdl.handle.net/1969.1/187179

Penn State University

29. Rosenkrantz, Adam Matthew. Coupled 3D Neutronics and Thermal Hydraulics Modeling of the SAFARI-1 Materials Testing Reactor.

Degree: 2012, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/13747

► The purpose of this study was to create a highly accurate model of the SAFARI-1 materials testing reactor, a facility mainly used for research and… (more)

Subjects/Keywords: Neutronics; Thermal Hydraulics; Modeling; Nuclear; Reactor; Coupling; Engineering

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APA (6^th Edition):

Rosenkrantz, A. M. (2012). Coupled 3D Neutronics and Thermal Hydraulics Modeling of the SAFARI-1 Materials Testing Reactor. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/13747

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Chicago Manual of Style (16^th Edition):

Rosenkrantz, Adam Matthew. “Coupled 3D Neutronics and Thermal Hydraulics Modeling of the SAFARI-1 Materials Testing Reactor.” 2012. Thesis, Penn State University. Accessed March 04, 2021. https://submit-etda.libraries.psu.edu/catalog/13747.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

MLA Handbook (7^th Edition):

Rosenkrantz, Adam Matthew. “Coupled 3D Neutronics and Thermal Hydraulics Modeling of the SAFARI-1 Materials Testing Reactor.” 2012. Web. 04 Mar 2021.

Vancouver:

Rosenkrantz AM. Coupled 3D Neutronics and Thermal Hydraulics Modeling of the SAFARI-1 Materials Testing Reactor. [Internet] [Thesis]. Penn State University; 2012. [cited 2021 Mar 04]. Available from: https://submit-etda.libraries.psu.edu/catalog/13747.

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

Council of Science Editors:

Rosenkrantz AM. Coupled 3D Neutronics and Thermal Hydraulics Modeling of the SAFARI-1 Materials Testing Reactor. [Thesis]. Penn State University; 2012. Available from: https://submit-etda.libraries.psu.edu/catalog/13747

Note: this citation may be lacking information needed for this citation format:
Not specified: Masters Thesis or Doctoral Dissertation

University of Bath

30. Ayling, Joanna R. Evaluation of a technique for the remote measurement of surface temperature distributions in laser heated samples.

Degree: PhD, 1996, University of Bath

URL: https://researchportal.bath.ac.uk/en/studentthesis/evaluation-of-a-technique-for-the-remote-measurement-of-surface-temperature-distributions-in-laser-heated-samples(a9095f76-bfcb-486d-a5be-9eba36ed654c).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320437

Subjects/Keywords: 621.484; Nuclear fuels; Thermal behaviour

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APA · Chicago · MLA · Vancouver · CSE | Export to Zotero / EndNote / Reference Manager

APA (6^th Edition):

Ayling, J. R. (1996). Evaluation of a technique for the remote measurement of surface temperature distributions in laser heated samples. (Doctoral Dissertation). University of Bath. Retrieved from https://researchportal.bath.ac.uk/en/studentthesis/evaluation-of-a-technique-for-the-remote-measurement-of-surface-temperature-distributions-in-laser-heated-samples(a9095f76-bfcb-486d-a5be-9eba36ed654c).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320437

Chicago Manual of Style (16^th Edition):

Ayling, Joanna R. “Evaluation of a technique for the remote measurement of surface temperature distributions in laser heated samples.” 1996. Doctoral Dissertation, University of Bath. Accessed March 04, 2021. https://researchportal.bath.ac.uk/en/studentthesis/evaluation-of-a-technique-for-the-remote-measurement-of-surface-temperature-distributions-in-laser-heated-samples(a9095f76-bfcb-486d-a5be-9eba36ed654c).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320437.

MLA Handbook (7^th Edition):

Ayling, Joanna R. “Evaluation of a technique for the remote measurement of surface temperature distributions in laser heated samples.” 1996. Web. 04 Mar 2021.

Vancouver:

Ayling JR. Evaluation of a technique for the remote measurement of surface temperature distributions in laser heated samples. [Internet] [Doctoral dissertation]. University of Bath; 1996. [cited 2021 Mar 04]. Available from: https://researchportal.bath.ac.uk/en/studentthesis/evaluation-of-a-technique-for-the-remote-measurement-of-surface-temperature-distributions-in-laser-heated-samples(a9095f76-bfcb-486d-a5be-9eba36ed654c).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320437.

Council of Science Editors:

Ayling JR. Evaluation of a technique for the remote measurement of surface temperature distributions in laser heated samples. [Doctoral Dissertation]. University of Bath; 1996. Available from: https://researchportal.bath.ac.uk/en/studentthesis/evaluation-of-a-technique-for-the-remote-measurement-of-surface-temperature-distributions-in-laser-heated-samples(a9095f76-bfcb-486d-a5be-9eba36ed654c).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.320437

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