subject:(Thermal Protection System)

Delft University of Technology

1. Roorda, Evelyne (author). Thermal Protection System Analysis and Sizing for Spaceplane Configurations: Preliminary design of the TPS and optimization of the insulation layer.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:dbd513c7-346d-4a7b-972c-7eb9497f1bd8

► During its lifetime a space launcher is subjected to extreme heat loads. To protect space vehicles from these heat loads and their resulting temperatures they… (more)

▼ During its lifetime a space launcher is subjected to extreme heat loads. To protect space vehicles from these heat loads and their resulting temperatures they are equipped with a Thermal Protection System (TPS). Heat loads are typically the largest during flight through the atmosphere. The research question addressed in the thesis is: how robust is a thermal protection system design for a spaceplane wing-body configuration to variations with respect to the design parameters or trajectory taking into account heat transfer through radiation and conduction in three dimensions? To answer the research question a tool was developed which is capable of designing a TPS and optimizing the insulation layer thickness. Furthermore, a trajectory simulation was made for the reentry phase. From the trajectory specifics the heat flux over the vehicle over time could be generated, which is the source of the temperature increase. In the TPS design tool the first major task is to divide the vehicle into different TPS areas, based on the temperatures that are experienced at each of these areas of the skin surface. A thermal analysis is performed, taking into account both conduction in three dimensions and radiation to outer space as well as to the inner subsystems of the vehicle. From this analysis the maximum experienced temperature can be deduced for each area. When the TPS design is found, it is aimed to optimize the insulation layer thicknesses in all TPS areas. The goal is to find a design that is as light as possible, thus with a minimum insulation layer thickness, while not exceeding the maximum temperatures of the TPS types and underlying structure. A sensitivity study was performed to investigate the robustness of the TPS design resulting from the tool. The performance of the TPS design was tested when small changes were made to it, for the nominal reentry trajectory of the reference vehicle. Furthermore the TPS designs performance was analyzed for small changes in the trajectory. From the analysis of the results of the developed tool it was found that a TPS design can be developed for a simple wing-body configuration, under the specified conditions. However, the functionality of the TPS design is limited. Improvements must be made to the developed tool to increase its performance, so that it can come to an acceptable TPS design. It is suspected that with suggested improvements the tool will work properly, and a well functioning TPS design can be made. However, further research is required to ensure this. Advisors/Committee Members: Mooij, Erwin (mentor), Visser, Pieter (graduation committee), Sudmeijer, Kees (graduation committee), Gransden, Derek (graduation committee), Kopp, Alexander (mentor), Delft University of Technology (degree granting institution).

Subjects/Keywords: spaceplane; thermal protection system; SSTO

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APA (6^th Edition):

Roorda, E. (. (2017). Thermal Protection System Analysis and Sizing for Spaceplane Configurations: Preliminary design of the TPS and optimization of the insulation layer. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:dbd513c7-346d-4a7b-972c-7eb9497f1bd8

Chicago Manual of Style (16^th Edition):

Roorda, Evelyne (author). “Thermal Protection System Analysis and Sizing for Spaceplane Configurations: Preliminary design of the TPS and optimization of the insulation layer.” 2017. Masters Thesis, Delft University of Technology. Accessed March 01, 2021. http://resolver.tudelft.nl/uuid:dbd513c7-346d-4a7b-972c-7eb9497f1bd8.

MLA Handbook (7^th Edition):

Roorda, Evelyne (author). “Thermal Protection System Analysis and Sizing for Spaceplane Configurations: Preliminary design of the TPS and optimization of the insulation layer.” 2017. Web. 01 Mar 2021.

Vancouver:

Roorda E(. Thermal Protection System Analysis and Sizing for Spaceplane Configurations: Preliminary design of the TPS and optimization of the insulation layer. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Mar 01]. Available from: http://resolver.tudelft.nl/uuid:dbd513c7-346d-4a7b-972c-7eb9497f1bd8.

Council of Science Editors:

Roorda E(. Thermal Protection System Analysis and Sizing for Spaceplane Configurations: Preliminary design of the TPS and optimization of the insulation layer. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:dbd513c7-346d-4a7b-972c-7eb9497f1bd8

University of Manchester

2. Cong, Yuhang. Synchronized measurement technology supported operational tripping schemes.

Degree: PhD, 2016, University of Manchester

URL: https://www.research.manchester.ac.uk/portal/en/theses/synchronized-measurement-technology-supported-operational-tripping-schemes(7d472659-d352-4291-96fc-fce7e6ce5fc8).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.722280

► The increasing volume of renewable and intermittent generation that is being connected to power systems means that system operators need more advanced dynamic control tools… (more)

Subjects/Keywords: 621.319; Conductor/Transformer Heating; Dynamic Thermal Line Rating; Operational Tripping Scheme; Power System Protection; Power System; System Integrity Protection Scheme

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APA (6^th Edition):

Cong, Y. (2016). Synchronized measurement technology supported operational tripping schemes. (Doctoral Dissertation). University of Manchester. Retrieved from https://www.research.manchester.ac.uk/portal/en/theses/synchronized-measurement-technology-supported-operational-tripping-schemes(7d472659-d352-4291-96fc-fce7e6ce5fc8).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.722280

Chicago Manual of Style (16^th Edition):

Cong, Yuhang. “Synchronized measurement technology supported operational tripping schemes.” 2016. Doctoral Dissertation, University of Manchester. Accessed March 01, 2021. https://www.research.manchester.ac.uk/portal/en/theses/synchronized-measurement-technology-supported-operational-tripping-schemes(7d472659-d352-4291-96fc-fce7e6ce5fc8).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.722280.

MLA Handbook (7^th Edition):

Cong, Yuhang. “Synchronized measurement technology supported operational tripping schemes.” 2016. Web. 01 Mar 2021.

Vancouver:

Cong Y. Synchronized measurement technology supported operational tripping schemes. [Internet] [Doctoral dissertation]. University of Manchester; 2016. [cited 2021 Mar 01]. Available from: https://www.research.manchester.ac.uk/portal/en/theses/synchronized-measurement-technology-supported-operational-tripping-schemes(7d472659-d352-4291-96fc-fce7e6ce5fc8).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.722280.

Council of Science Editors:

Cong Y. Synchronized measurement technology supported operational tripping schemes. [Doctoral Dissertation]. University of Manchester; 2016. Available from: https://www.research.manchester.ac.uk/portal/en/theses/synchronized-measurement-technology-supported-operational-tripping-schemes(7d472659-d352-4291-96fc-fce7e6ce5fc8).html ; https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.722280

University of Waterloo

3. 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 (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 01, 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. 01 Mar 2021.

Vancouver:

Christopher N. Numerical Analysis of Transpiration Cooling on a Turbulent Flat Plate. [Internet] [Thesis]. University of Waterloo; 2020. [cited 2021 Mar 01]. 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

University of Vermont

4. Smith, Silas. Investigation of Subsonic and Supersonic Flow Characteristics of an Inductively Coupled Plasma Facility.

Degree: MS, Mechanical Engineering, 2013, University of Vermont

URL: https://scholarworks.uvm.edu/graddis/218

► Inductively Coupled Plasma (ICP) facilities create high enthalpy ows to recreate atmospheric entry conditions. Although no condition has been duplicated exactly in a ground test… (more)

▼ Inductively Coupled Plasma (ICP) facilities create high enthalpy ows to recreate atmospheric entry conditions. Although no condition has been duplicated exactly in a ground test facility, it is important to characterize the condition to understand how close a facility can come to doing so. An ICP facility was constructed at the University of Vermont for aerospace material testing in 2010. The current setup can operate using air, carbon dioxide, nitrogen, and argon to test samples in a chamber. In this work we investigate di erent ways to increase measured heat ux and expand our facility to operate supersonically. To do so, a water cooled injection system was designed to overcome failure points of the prior system. An investigation of heat ux methods that provide a baseline for the facility were also examined and tested. A nozzle con guration was also developed with an overall goal of increasing the plasma ow to reach sonic and supersonic velocities, allowing it to be compared with the existing subsonic system. An iterative approach was taken to develop a nozzle design that is robust enough to handle the harsh environment, yet adaptable to the pre-existing facility components. The current design uses interchangeable sonic and supersonic nozzles which also allow for appropriate plasma gas expansion. Data are taken through retractable and goose-neck probe sample holders during testing. Heat ux can be determined by use of a Gardon gage, slug calorimeter, and water cooled calorimeter. Total and static pressure are determined from a pitot tube and pressure tap, which are then manipulated into a velocity measurement. A comparison between subsonic and supersonic operation is then made with these data. Existing literature uses correlations between jet diameter and velocity gradients to determine the e ective heat ux. This investigation found that the experimental and theoretical heat ux results scale correctly according to the correlations. Advisors/Committee Members: Fletcher, Douglas.

Subjects/Keywords: subsonic; heat flux; inductively coupled plasma; supersonic; thermal protection system

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APA (6^th Edition):

Smith, S. (2013). Investigation of Subsonic and Supersonic Flow Characteristics of an Inductively Coupled Plasma Facility. (Thesis). University of Vermont. Retrieved from https://scholarworks.uvm.edu/graddis/218

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):

Smith, Silas. “Investigation of Subsonic and Supersonic Flow Characteristics of an Inductively Coupled Plasma Facility.” 2013. Thesis, University of Vermont. Accessed March 01, 2021. https://scholarworks.uvm.edu/graddis/218.

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

MLA Handbook (7^th Edition):

Smith, Silas. “Investigation of Subsonic and Supersonic Flow Characteristics of an Inductively Coupled Plasma Facility.” 2013. Web. 01 Mar 2021.

Vancouver:

Smith S. Investigation of Subsonic and Supersonic Flow Characteristics of an Inductively Coupled Plasma Facility. [Internet] [Thesis]. University of Vermont; 2013. [cited 2021 Mar 01]. Available from: https://scholarworks.uvm.edu/graddis/218.

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

Council of Science Editors:

Smith S. Investigation of Subsonic and Supersonic Flow Characteristics of an Inductively Coupled Plasma Facility. [Thesis]. University of Vermont; 2013. Available from: https://scholarworks.uvm.edu/graddis/218

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

Delft University of Technology

5. Ahuja, Aditi (author). Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design.

Degree: 2020, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:a61aff50-928c-458b-856d-41d075f853b1

►

The next step in spaceflight, among others, is the development of a reusable launch vehicle (RLV) suitable for manned missions. All existing designs of re-entry… (more)

▼

The next step in spaceflight, among others, is the development of a reusable launch vehicle (RLV) suitable for manned missions. All existing designs of re-entry vehicles are either ballistic or low L/D vehicles. In the future, the aim is to develop a high L/D vehicle, because such vehicles experience lower g-loads, making the flight comfortable for manned flights. The development of these vehicles can be useful for both, space (for example, space tourism) and military applications (for example, long-range missiles). Thermal protection system (TPS) is deemed critical to the RLV development, as high L/D vehicles are expected to experience higher thermal loads. Existing TPS solutions are not suitable for this purpose. Therefore, arises the need to find reusable TPS solutions that can sustain the desired thermal loads. Flight testing is a crucial step for developing any hypersonic system, this applies to the TPS design as well. This study aims to investigate the influence of TPS on designing the mission and vehicle for a test flight. From the various developed and proposed TPS designs in literature, a TPS solution is selected, to meet the requirements identified for future RLVs. The solution is an active cooling concept (cooled metallic TPS), named Enhanced radiation cooling, that uses water as a coolant. Based on a preliminary design investigation, suitable materials are selected and the thickness of the layer is determined. The performance of the proposed TPS design, i.e., the thermal load-bearing ability, is assessed using a transient thermal analysis tool developed for this purpose. The outcome of this analysis proves that the proposed design does not meet the thermal load requirements identified in this study. Nonetheless, the concept shows substantial improvement in performance, it can sustain almost double the heat flux as compared to an uncooled system. To meet the heat flux requirements, a few modifications in the design are proposed and analysed. These modifications increase the complexity of the system and have other adverse consequences that must be addressed. However, thermal analysis proves that the heat flux requirements, identified at the start of this study, are satisfied. A sensitivity analysis of this modified cooling system shows that the performance of the design is not influenced by material uncertainties. Additionally, the design is found to be robust under varying mission and design parameters, within reasonable bounds. These results can serve as a preliminary input for designing a test vehicle and mission.

Aerospace Engineering

Advisors/Committee Members: Mooij, Erwin (mentor), Sudmeijer, Kees (graduation committee), van der Wal, Wouter (graduation committee), De Breuker, Roeland (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Active thermal protection system; Reusable launch vehicle; Conceptual design

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

APA (6^th Edition):

Ahuja, A. (. (2020). Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:a61aff50-928c-458b-856d-41d075f853b1

Chicago Manual of Style (16^th Edition):

Ahuja, Aditi (author). “Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design.” 2020. Masters Thesis, Delft University of Technology. Accessed March 01, 2021. http://resolver.tudelft.nl/uuid:a61aff50-928c-458b-856d-41d075f853b1.

MLA Handbook (7^th Edition):

Ahuja, Aditi (author). “Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design.” 2020. Web. 01 Mar 2021.

Vancouver:

Ahuja A(. Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design. [Internet] [Masters thesis]. Delft University of Technology; 2020. [cited 2021 Mar 01]. Available from: http://resolver.tudelft.nl/uuid:a61aff50-928c-458b-856d-41d075f853b1.

Council of Science Editors:

Ahuja A(. Active Thermal Protection System for Reusable Launch Vehicle: A Conceptual Design. [Masters Thesis]. Delft University of Technology; 2020. Available from: http://resolver.tudelft.nl/uuid:a61aff50-928c-458b-856d-41d075f853b1

Texas A&M University

6. Gesting, Peter Paul. A photogrammetric on-orbit inspection for orbiter thermal protection system.

Degree: MS, Aerospace Engineering, 2006, Texas A&M University

URL: http://hdl.handle.net/1969.1/3191

► Due to the Columbia Space Shuttle Accident of February 2003, the Columbia Accident Investigation Board determined the need for an on-orbit inspection system for the… (more)

▼ Due to the Columbia Space Shuttle Accident of February 2003, the Columbia Accident Investigation Board determined the need for an on-orbit inspection system for the Thermal Protection System that accurately determines damage depth to 0.25". NASA contracted the Spacecraft Technology Center in College Station, Texas, for a proof-of-concept photogrammetric system. This system involves a high quality digital camera placed on the International Space Station, capable of taking high fidelity images of the orbiter as it rotates through the Rendezvous Pitch Maneuver. Due to the pitch rotation, the images are tilted at different angles. The tilt causes the damage to exhibit parallax between multiple images. The tilted images are therefore registered to the near-vertical images using visually striking features on the undamaged surface of the Thermal Protection System that appear in multiple images taken at different tilt angles. The images become relatively oriented after registration, and features in one image are ensured to lie on the epipolar line in the other images. Features that do not lie on the undamaged surface, however, are shifted in the tilted images. These pixels are matched to the near-vertical image using a sliding-window area-matching approach. The windows are matched using a least-squares error method. The change in location for a pixel in a tilted image from its expected location on the undamaged surface is called the pixel disparity. This disparity is linearly scaled using the tilt angle and the pixel sampling to determine the depth of the damage at that pixel location. The algorithm is tested on a set of damaged tiles at the Johnson Space Center in Houston and the photogrammetric damage depth is then compared to a set of truth data provided by NASA. The photogrammetric method shows promise, with the 0.25" error limit being exceeded in only a few pixel locations. Once the camera properties are fully known from calibration, this systematic error should be reduced. Advisors/Committee Members: Hurtado, John (advisor), Junkins, John (committee member), Langari, Reza (committee member), Valasek, John (committee member).

Subjects/Keywords: Image Processing; Photogrammetry; Thermal Protection System

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APA (6^th Edition):

Gesting, P. P. (2006). A photogrammetric on-orbit inspection for orbiter thermal protection system. (Masters Thesis). Texas A&M University. Retrieved from http://hdl.handle.net/1969.1/3191

Chicago Manual of Style (16^th Edition):

Gesting, Peter Paul. “A photogrammetric on-orbit inspection for orbiter thermal protection system.” 2006. Masters Thesis, Texas A&M University. Accessed March 01, 2021. http://hdl.handle.net/1969.1/3191.

MLA Handbook (7^th Edition):

Gesting, Peter Paul. “A photogrammetric on-orbit inspection for orbiter thermal protection system.” 2006. Web. 01 Mar 2021.

Vancouver:

Gesting PP. A photogrammetric on-orbit inspection for orbiter thermal protection system. [Internet] [Masters thesis]. Texas A&M University; 2006. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/1969.1/3191.

Council of Science Editors:

Gesting PP. A photogrammetric on-orbit inspection for orbiter thermal protection system. [Masters Thesis]. Texas A&M University; 2006. Available from: http://hdl.handle.net/1969.1/3191

Delft University of Technology

7. Dubois, Wouter (author). Enhanced Radiation Cooling: Design of an active thermal protection system.

Degree: 2017, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:e7a4ba62-6949-41bd-99e7-07170b4c5979

► Current-day space vehicle are equipped with a passive Thermal Protection System (TPS), but these systems operate at the edge of their capabilities. The research into… (more)

▼ Current-day space vehicle are equipped with a passive Thermal Protection System (TPS), but these systems operate at the edge of their capabilities. The research into the next generation reusable space vehicle demands the use of active TPS, these systems are not limited to the capabilities of the used material but depend on the active cooling mechanism. A system of cooled metallic TPS is developed at the TU Delft resulting in an increase in the maximum allowable thermal load for a given TPS temperature, this system is the enhanced radiation cooling TPS. The research question is: "Can an active thermal protection system improve the flying characteristics and the flight performance of a re-entry vehicle?". The first step in answering this question is to verify the process behind the active TPS. This thesis aims to design an experiment to verify this process. To answer the research question two tools were developed: a flight simulator and a thermodynamic analyser. The flight simulator provides insight in the behaviour of the rocket and shows the consequences of implementing the enhanced radiation cooling TPS on the rocket. The thermodynamic analyser is used to estimate the wall temperature of the system and shows the effect of the sensitivity analysis of the design of the cooling subsystem. The enhanced radiation cooling system is designed to be mounted on the T-Minus Dart and an experiment to verify the impact of the active TPS is derived using the nominal mission of the rocket. Sensitivity analysis resulted in thin outer shell and a insulation sphere filled with the coolant. The outer shell needs to be as thin as possible in order to maximize the cooling effect. For an outer shell of 0.5 millimetres, the maximum allowable thermal load can be doubled in comparison with an non-cooled flight. If an identical thermal loading is assumed for two return vehicles, the active cooled vehicle can be designed with a nose radius of around 30 % smaller that the non-cooled vehicle. This will result in a vehicle with a higher lift-over-drag ratio, extending the return trajectory which increases the safety of the re-entry flight. The validity of performing an enhanced radiation cooling experiment is shown by the use of the tools developed in this thesis. The incoming heat flux can be doubled while maintaining the same wall temperatures if the cooling system is applied. This opens the possibility of redesigning re-entry vehicles to achieve a high lift-to-drag ratio. Advisors/Committee Members: Mooij, Erwin (mentor), Sudmeijer, Kees (mentor), Visser, Pieter (graduation committee), Schrijer, Ferdinand (graduation committee), Delft University of Technology (degree granting institution).

Subjects/Keywords: Active thermal protection system; Enhanced radiation cooling; 6 Degree of Freedom modelling

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APA (6^th Edition):

Dubois, W. (. (2017). Enhanced Radiation Cooling: Design of an active thermal protection system. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:e7a4ba62-6949-41bd-99e7-07170b4c5979

Chicago Manual of Style (16^th Edition):

Dubois, Wouter (author). “Enhanced Radiation Cooling: Design of an active thermal protection system.” 2017. Masters Thesis, Delft University of Technology. Accessed March 01, 2021. http://resolver.tudelft.nl/uuid:e7a4ba62-6949-41bd-99e7-07170b4c5979.

MLA Handbook (7^th Edition):

Dubois, Wouter (author). “Enhanced Radiation Cooling: Design of an active thermal protection system.” 2017. Web. 01 Mar 2021.

Vancouver:

Dubois W(. Enhanced Radiation Cooling: Design of an active thermal protection system. [Internet] [Masters thesis]. Delft University of Technology; 2017. [cited 2021 Mar 01]. Available from: http://resolver.tudelft.nl/uuid:e7a4ba62-6949-41bd-99e7-07170b4c5979.

Council of Science Editors:

Dubois W(. Enhanced Radiation Cooling: Design of an active thermal protection system. [Masters Thesis]. Delft University of Technology; 2017. Available from: http://resolver.tudelft.nl/uuid:e7a4ba62-6949-41bd-99e7-07170b4c5979

University of Illinois – Urbana-Champaign

8. Harpale, Abhilash. Scale-bridging molecular dynamics simulations of plasma-surface interactions.

Degree: PhD, Aerospace Engineering, 2018, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/100909

► Plasma processing of materials plays a vital part in electronic, aerospace, automobile, metal manufacturing and biomedical industries. Plasma-surface interactions can be divided into two categories:… (more)

▼ Plasma processing of materials plays a vital part in electronic, aerospace, automobile, metal manufacturing and biomedical industries. Plasma-surface interactions can be divided into two categories: controlled and erosive. Controlled plasma interactions are used to pattern the surfaces of materials to achieve desirable electronic and mechanical properties in an ionizing chamber. Examples include focused ion beam (FIB) milling of silicon thin films and plasma patterning of graphene. Erosive interactions typically involve damage to surfaces in close proximity to high temperature, ionized gases in an uncontrolled environment. Examples include plasma facing components in reactor vessels and thermal protection system in re-entry spacecraft. Due to the complex chemistry at the plasma surface boundaries, it is difficulty to either control or predict the effect of plasma on the patterning or erosion of the material. In this dissertation, atomic scale simulations coupled with micromechanics models are used to study the patterning of graphene and the ablation of thermal protection systems resulting from controlled and erosive plasma-surface interactions, respectively. Scalable and precise nanopatterning of graphene is an essential step for graphene-based device fabrication. Hydrogen-plasma reactions have been shown to narrow graphene only from the edges, or to selectively produce circular or hexagonal holes in the basal plane of graphene, but the underlying plasma-graphene chemistry is unknown. In part I of this dissertation, we characterize the surface patterning of graphene via low energy hydrogen plasma treatment across a range of ion energies, using scale-bridging molecular dynamic simulations. Our results uncover distinct etching mechanisms, operative within narrow ion energy windows, which explain the various plasma-graphene reactions observed experimentally. For monolayer graphene, specific ion energy ranges are demonstrated for stable isotropic (∼2 eV) versus anisotropic hole growth (∼20-30 eV) within the basal plane of graphene, as well as for pure edge etching (∼1 eV). For multilayered graphene, our results demonstrate the initial development of columnar holes, which transition to stepped-edge holes at higher fluence due to cumulative effects of basal-plane etching. The contributions of thermal radicals and dehydrogenation effects on the hole growth process are also discussed. In part II of this dissertation, multi-scale simulations are used to study the erosive role of high temperature plasma generated by the shock heating of ambient gases on the surfaces of high velocity atmospheric re-entry space craft. We specifically examine the ablation of AVCOAT, which is a composite thermal protection system (TPS) material attached to the leading edge of the Orion multi-purpose crew vehicle. Phenol formaldehyde resin used as the matrix material in AVCOAT is modeled and its pyrolysis kinetics are determined using ReaxFF-based molecular dynamics (MD) simulations. Our MD simulations show that bulk pyrolysis starts at… Advisors/Committee Members: Chew, Huck Beng (advisor), Chew, Huck Beng (Committee Chair), Levin, Deborah (committee member), Geubelle, Philippe H. (committee member), Johnson, Harley (committee member).

Subjects/Keywords: graphene; plasma; molecular dynamics; atomic scale simulations; surfaces; thermal protection system; NASA; spacecraft

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APA (6^th Edition):

Harpale, A. (2018). Scale-bridging molecular dynamics simulations of plasma-surface interactions. (Doctoral Dissertation). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/100909

Chicago Manual of Style (16^th Edition):

Harpale, Abhilash. “Scale-bridging molecular dynamics simulations of plasma-surface interactions.” 2018. Doctoral Dissertation, University of Illinois – Urbana-Champaign. Accessed March 01, 2021. http://hdl.handle.net/2142/100909.

MLA Handbook (7^th Edition):

Harpale, Abhilash. “Scale-bridging molecular dynamics simulations of plasma-surface interactions.” 2018. Web. 01 Mar 2021.

Vancouver:

Harpale A. Scale-bridging molecular dynamics simulations of plasma-surface interactions. [Internet] [Doctoral dissertation]. University of Illinois – Urbana-Champaign; 2018. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/2142/100909.

Council of Science Editors:

Harpale A. Scale-bridging molecular dynamics simulations of plasma-surface interactions. [Doctoral Dissertation]. University of Illinois – Urbana-Champaign; 2018. Available from: http://hdl.handle.net/2142/100909

University of Maryland

9. Beerman, Adam Farrell. THE EFFECTS OF FINITE-RATE REACTIONS AT THE GAS/SURFACE INTERFACE IN SUPPORT OF THERMAL PROTECTION SYSTEM DESIGN.

Degree: Aerospace Engineering, 2011, University of Maryland

URL: http://hdl.handle.net/1903/11515

► Gas-surface modeling is dependent on material type and atmospheric reentry conditions. Lower molecular collisions at the low pressure trajectories make it more likely for occurrences… (more)

▼ Gas-surface modeling is dependent on material type and atmospheric reentry conditions. Lower molecular collisions at the low pressure trajectories make it more likely for occurrences of nonequilibrium, or finite-rate, reactions. Equilibrium is often assumed at the surface of a material as it is a subset of nonequilibrium and is easier to compute, though it can lead to overly conservative predictions. A case where a low density material experiences a low pressure trajectory and designed for equilibrium is the Stardust Return Capsule (SRC) with the Phenolic Impregnated Carbon Ablator (PICA) as its heatshield. Post-flight analysis of the recession on the SRC found that the prediction from the equilibrium model can be more than 50% larger than the measured recession. The Modified Park Model was chosen as the finite-rate model as it contains simple four reactions (oxidation, sublimation, and nitridation) and has been previously used to study individual points of the SRC trajectory. The Modified Park Model cannot model equilibrium so a model BFIAT was developed that allows finite-rate reactions to be applied to the surface for a certain length of time. Finite-rate sublimation was determined to be reaction of importance in the Park Model for SRC-like conditions. The predicted recession on the SRC heatshield experienced a reduction in its overprediction; the finite-rate predictions fall with the measurement error of the recession at three points on the heatshield. The recession reduction was driven by a significant reduction in char formation. There was little change in the pyrolysis gas rate. The finite-rate model was also applied to simulations of various arc-jet tests that covered a range of heating conditions on the surface of the PICA material. Comparison to this experimental data further showed the role of finite-rate reactions and sublimation in the Park Model and conditions that favor the nonequilibrium assumption (heating over 1000 W/cm2). For the emerging PICA material, used for the Mars Science Laboratory and one of two material choices for the Crew Exploration Vehicle, and SRC-like trajectories, a finite-rate model was developed such that the more robust nonequilibrium assumption can be applied to design processes to reduce heatshield mass. Advisors/Committee Members: Lewis, Mark J (advisor).

Subjects/Keywords: Aerospace Engineering; ablation; aerothermodynamics; finite-rate reaction; hypersonics; recession; thermal protection system

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APA (6^th Edition):

Beerman, A. F. (2011). THE EFFECTS OF FINITE-RATE REACTIONS AT THE GAS/SURFACE INTERFACE IN SUPPORT OF THERMAL PROTECTION SYSTEM DESIGN. (Thesis). University of Maryland. Retrieved from http://hdl.handle.net/1903/11515

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):

Beerman, Adam Farrell. “THE EFFECTS OF FINITE-RATE REACTIONS AT THE GAS/SURFACE INTERFACE IN SUPPORT OF THERMAL PROTECTION SYSTEM DESIGN.” 2011. Thesis, University of Maryland. Accessed March 01, 2021. http://hdl.handle.net/1903/11515.

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

MLA Handbook (7^th Edition):

Beerman, Adam Farrell. “THE EFFECTS OF FINITE-RATE REACTIONS AT THE GAS/SURFACE INTERFACE IN SUPPORT OF THERMAL PROTECTION SYSTEM DESIGN.” 2011. Web. 01 Mar 2021.

Vancouver:

Beerman AF. THE EFFECTS OF FINITE-RATE REACTIONS AT THE GAS/SURFACE INTERFACE IN SUPPORT OF THERMAL PROTECTION SYSTEM DESIGN. [Internet] [Thesis]. University of Maryland; 2011. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/1903/11515.

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

Council of Science Editors:

Beerman AF. THE EFFECTS OF FINITE-RATE REACTIONS AT THE GAS/SURFACE INTERFACE IN SUPPORT OF THERMAL PROTECTION SYSTEM DESIGN. [Thesis]. University of Maryland; 2011. Available from: http://hdl.handle.net/1903/11515

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

Penn State University

10. Weir, Erik David. DESIGN AND APPLICATIONS OF ZIGBEE-ENABLED WIRELESS SENSOR SYSTEMS FOR A SPACE RELEVANT ENVIRONMENT.

Degree: 2010, Penn State University

URL: https://submit-etda.libraries.psu.edu/catalog/11235

► A prototype wireless sensor system is developed to collect data from sensors that are of importance on space platforms, and also important in the testing… (more)

▼ A prototype wireless sensor system is developed to collect data from sensors that are of importance on space platforms, and also important in the testing of these systems in space-relevant environments. The elimination of wires and the associated failures such as chafing, sparking, ageing, and connector issues can increase reliability and design flexibility while reducing costs. These factors present an appealing case for the pursuit of wireless solutions for harsh environments and particularly for their use in space and on spacecraft. Recent testing of this prototype system in the NASA Ames Research Center’s Aerodynamic Heating Facility during Test 289 in January 2010, demonstrated the feasibility of using wireless sensors in ground test programs and point to their use on flight vehicles. The test demonstrated data collection of a type-K thermocouple at ±2.5 °C resolution, with real-time data rates of 1 Hz, and high-speed data collection rates of 60 Hz and higher. The presence of the plasma, heat, and vacuum within the chamber did not inhibit data acquisition, although there was a period of radio blackout while there was plasma between the system and the receiver. A further test was attempted in the Panel Test Facility to show 100% communication uptime and multiple sensor support, and although that test was halted by critical battery failure, an upcoming “wedge” test in the Interaction Heating Facility, will showcase a fully functional system. With continued refinement, the next version of the wireless sensor system has the potential to exhibit an increase in data frequency, a dramatic increase in battery life, and a marked reduction in size. This thesis demonstrates that wireless sensor systems have the capability to replace wired systems in space applications. Future testing will further increase the technology readiness level of the wireless sensor system, verifying that wireless systems have a place on future flight missions. Advisors/Committee Members: Sven G Bilen, Thesis Advisor/Co-Advisor, Sven G Bilen, Thesis Advisor/Co-Advisor, Julio Urbina, Thesis Advisor/Co-Advisor.

Subjects/Keywords: wireless sensor system; zigbee; thermal protection system; thermocouple

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

APA (6^th Edition):

Weir, E. D. (2010). DESIGN AND APPLICATIONS OF ZIGBEE-ENABLED WIRELESS SENSOR SYSTEMS FOR A SPACE RELEVANT ENVIRONMENT. (Thesis). Penn State University. Retrieved from https://submit-etda.libraries.psu.edu/catalog/11235

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):

Weir, Erik David. “DESIGN AND APPLICATIONS OF ZIGBEE-ENABLED WIRELESS SENSOR SYSTEMS FOR A SPACE RELEVANT ENVIRONMENT.” 2010. Thesis, Penn State University. Accessed March 01, 2021. https://submit-etda.libraries.psu.edu/catalog/11235.

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

MLA Handbook (7^th Edition):

Weir, Erik David. “DESIGN AND APPLICATIONS OF ZIGBEE-ENABLED WIRELESS SENSOR SYSTEMS FOR A SPACE RELEVANT ENVIRONMENT.” 2010. Web. 01 Mar 2021.

Vancouver:

Weir ED. DESIGN AND APPLICATIONS OF ZIGBEE-ENABLED WIRELESS SENSOR SYSTEMS FOR A SPACE RELEVANT ENVIRONMENT. [Internet] [Thesis]. Penn State University; 2010. [cited 2021 Mar 01]. Available from: https://submit-etda.libraries.psu.edu/catalog/11235.

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

Council of Science Editors:

Weir ED. DESIGN AND APPLICATIONS OF ZIGBEE-ENABLED WIRELESS SENSOR SYSTEMS FOR A SPACE RELEVANT ENVIRONMENT. [Thesis]. Penn State University; 2010. Available from: https://submit-etda.libraries.psu.edu/catalog/11235

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

University of Vermont

11. Owens, Walten. Aero-Thermal Characterization Of Silicon Carbide Flexible Tps Using A 30kw Icp Torch.

Degree: PhD, Mechanical Engineering, 2015, University of Vermont

URL: https://scholarworks.uvm.edu/graddis/363

► Flexible thermal protection systems are of interest due to their necessity for the success of future atmospheric entry vehicles. Current non-ablative flexible designs incorporate… (more)

Subjects/Keywords: Catalycity; Oxidation; SiC; Silicon Carbide; Thermal Protection System; TPS; Aerospace Engineering; Mechanical Engineering; Mechanics of Materials

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

APA (6^th Edition):

Owens, W. (2015). Aero-Thermal Characterization Of Silicon Carbide Flexible Tps Using A 30kw Icp Torch. (Doctoral Dissertation). University of Vermont. Retrieved from https://scholarworks.uvm.edu/graddis/363

Chicago Manual of Style (16^th Edition):

Owens, Walten. “Aero-Thermal Characterization Of Silicon Carbide Flexible Tps Using A 30kw Icp Torch.” 2015. Doctoral Dissertation, University of Vermont. Accessed March 01, 2021. https://scholarworks.uvm.edu/graddis/363.

MLA Handbook (7^th Edition):

Owens, Walten. “Aero-Thermal Characterization Of Silicon Carbide Flexible Tps Using A 30kw Icp Torch.” 2015. Web. 01 Mar 2021.

Vancouver:

Owens W. Aero-Thermal Characterization Of Silicon Carbide Flexible Tps Using A 30kw Icp Torch. [Internet] [Doctoral dissertation]. University of Vermont; 2015. [cited 2021 Mar 01]. Available from: https://scholarworks.uvm.edu/graddis/363.

Council of Science Editors:

Owens W. Aero-Thermal Characterization Of Silicon Carbide Flexible Tps Using A 30kw Icp Torch. [Doctoral Dissertation]. University of Vermont; 2015. Available from: https://scholarworks.uvm.edu/graddis/363

Delft University of Technology

12. Buursink, J. On the development of a cooled metallic thermal protection system for spacecraft.

Degree: 2005, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf

► To achieve a significant cost reduction for launch of payloads to space, it is essential that the launcher is reused to the largest possible extent,… (more)

Subjects/Keywords: thermal protection system; water cooling; reusable launcher

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APA (6^th Edition):

Buursink, J. (2005). On the development of a cooled metallic thermal protection system for spacecraft. (Doctoral Dissertation). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf

Chicago Manual of Style (16^th Edition):

Buursink, J. “On the development of a cooled metallic thermal protection system for spacecraft.” 2005. Doctoral Dissertation, Delft University of Technology. Accessed March 01, 2021. http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf.

MLA Handbook (7^th Edition):

Buursink, J. “On the development of a cooled metallic thermal protection system for spacecraft.” 2005. Web. 01 Mar 2021.

Vancouver:

Buursink J. On the development of a cooled metallic thermal protection system for spacecraft. [Internet] [Doctoral dissertation]. Delft University of Technology; 2005. [cited 2021 Mar 01]. Available from: http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf.

Council of Science Editors:

Buursink J. On the development of a cooled metallic thermal protection system for spacecraft. [Doctoral Dissertation]. Delft University of Technology; 2005. Available from: http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; urn:NBN:nl:ui:24-uuid:8f648295-c060-4575-80ab-a2cd175813cf ; http://resolver.tudelft.nl/uuid:8f648295-c060-4575-80ab-a2cd175813cf

University of Michigan

13. Ng, Wei Heok. Thermomechanical Analysis of a Damaged Thermal Protection System.

Degree: PhD, Aerospace Engineering, 2007, University of Michigan

URL: http://hdl.handle.net/2027.42/57597

► Research on the effects of damage on the thermomechanical performance and structural integrity of thermal protection systems (TPS) has been limited. The objective of this… (more)

▼ Research on the effects of damage on the thermomechanical performance and structural integrity of thermal protection systems (TPS) has been limited. The objective of this research is to address this need by conducting experiments and finite element (FE) analysis on damaged TPS. The TPS selected for study is the High-Temperature Reusable Insulation (HRSI) tiles used on NASA's Space Shuttle Orbiter. The TPS consists of a LI-900 tile, the strain isolator pad and the underlying structure, is subjected to the thermal loading and re-entry static pressure of the Access to Space reference vehicle. The damage to the TPS emulates hypervelocity-impact-type damage. Preliminary FE analysis using several simplifying assumptions, was conducted to determine the accuracy of using an approximate axisymmetric model compared to a complete three-dimensional model. Temperature results were found to be reasonable close; however, thermal stress results displayed significant differences. The sensitivity of the FE results to the various simplifying assumptions was also examined and it was concluded that for reliable results, the simplifying assumptions were not acceptable. Subsequently, an exact three-dimensional model was developed and validated by comparison with experimental data. Re-entry static pressures and temperatures were simulated using a high-temperature experimental facility that consists of a quartz radiant heater and a vacuum chamber with appropriate instrumentation. This facility was developed during the course of this dissertation. Temperatures on the top and bottom surfaces of the TPS specimen as well as strains in the underlying structure were recorded for FE model validation. The validated FE model was then combined with improved thermal loads based on the interactions of hypersonic flow past a cavity representing the damage. Damage increases the thermal loads on the TPS and significantly reduces the heat rejection capability of the surface of the tile, resulting in elevated temperatures. The higher temperatures coupled with the stress concentrations introduced by the damage cause a substantial increase in thermal stresses. For the damage sizes considered, the elevated thermal stresses alone are not likely to cause material failure. However, a modest damage size of 0.5" is capable of raising temperatures in the tile to exceed its melting point. Advisors/Committee Members: Friedmann, Peretz P. (committee member), Waas, Anthony M. (committee member), Cesnik, Carlos E. (committee member), Epureanu, Bogdan I. (committee member).

Subjects/Keywords: Thermal Protection System; Finite Element; Thermal Stress; Heat Transfer; Aerospace Engineering; Engineering

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

APA (6^th Edition):

Ng, W. H. (2007). Thermomechanical Analysis of a Damaged Thermal Protection System. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/57597

Chicago Manual of Style (16^th Edition):

Ng, Wei Heok. “Thermomechanical Analysis of a Damaged Thermal Protection System.” 2007. Doctoral Dissertation, University of Michigan. Accessed March 01, 2021. http://hdl.handle.net/2027.42/57597.

MLA Handbook (7^th Edition):

Ng, Wei Heok. “Thermomechanical Analysis of a Damaged Thermal Protection System.” 2007. Web. 01 Mar 2021.

Vancouver:

Ng WH. Thermomechanical Analysis of a Damaged Thermal Protection System. [Internet] [Doctoral dissertation]. University of Michigan; 2007. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/2027.42/57597.

Council of Science Editors:

Ng WH. Thermomechanical Analysis of a Damaged Thermal Protection System. [Doctoral Dissertation]. University of Michigan; 2007. Available from: http://hdl.handle.net/2027.42/57597

14. Le Foll, Sébastien. Modélisation du couplage conduction/rayonnement dans les systèmes de protection thermique soumis à de très hauts niveaux de températures : Coupled radiative/conductive heat transfer modeling in thermal protection systems at high temperature.

Degree: Docteur es, Thermique et énergétique, 2014, INSA Lyon

URL: http://www.theses.fr/2014ISAL0079

►

Les travaux présentés dans cette thèse CIFRE financée par AIRBUS Defence & Space s’intègrent dans une problématique de développement de nouveaux Systèmes de Protection Thermique… (more)

▼

Les travaux présentés dans cette thèse CIFRE financée par AIRBUS Defence & Space s’intègrent dans une problématique de développement de nouveaux Systèmes de Protection Thermique (TPS) pour l’entrée atmosphérique. Ils se focalisent sur l’étude du transfert radiatif dans la zone d’ablation du TPS et son couplage avec le transfert conductif au travers de la matrice fibreuse de faible densité. Pour réaliser cette étude, il a été nécessaire d’évaluer les propriétés thermiques de ces matériaux, notamment les propriétés radiatives qui, contrairement aux conductivités thermiques, demeurent mal connues. La première étape de cette étude a donc visé à caractériser les propriétés optiques et radiatives de certains matériaux fournis par AIRBUS Defence & Space et par le CREE Saint-Gobain. Pour réaliser ces caractérisations, nous avons développé une méthode originale d’identification des propriétés radiatives basée sur des mesures de l’émission propre. Les spectres d’émission à haute température, réalisés sur des échantillons en fibre de silice ou en feutre de carbone nécessaires à l’identification, sont obtenus sur un banc de spectrométrie FTIR développé lors de ces travaux. Les échantillons sont chauffés à haute température à l’aide d’un laser CO2 et un montage optique permet de choisir entre la mesure du flux émis par l’échantillon ou un corps noir servant à l’étalonnage du banc. L’identification des propriétés repose sur la modélisation des facteurs de distribution du rayonnement calculés à l’aide d’une méthode de lancé de rayons Monte Carlo utilisant la théorie de Mie pour un cylindre infini pour le calcul des propriétés radiatives. Les températures identifiées sont comparées aux températures mesurées par pyrométrie au point de Christiansen dans le cas de la silice et montrent un bon accord avec ces dernières. Enfin la dernière partie de ce document est consacrée au couplage conduction-rayonnement dans ce type de milieu. Les échantillons ayant une très forte extinction, le modèle utilisé repose sur la définition d’une conductivité équivalente de Rosseland pour traiter les transferts radiatifs volumiques et ainsi simuler les champs de température au sein des échantillons dans les conditions de chauffage utilisées lors de l’identification. Dans le cas de la silice, cependant, les températures prédites par le modèle utilisant la conductivité équivalente de Rosseland, sont nettement supérieures à celles obtenues par identification ou par pyrométrie au point de Christiansen. Le fait que la conductivité équivalente de Rosseland ne fasse pas la distinction entre une forte extinction due à la diffusion ou à l’absorption est probablement la cause de cette différence.

The work presented in this thesis has been financed by AIRBUS Defence and Space. It is part of the development strategy of new Thermal Protection Systems (TPS) for atmospheric reentry purposes. The aim is to study the radiative transfer in the ablation zone of the TPS as well as the coupling of the radiative and conductive heat transfer in the low density fibrous…

Advisors/Committee Members: André, Frédéric (thesis director), Delmas, Agnès (thesis director).

Subjects/Keywords: Thermique; Rentrée atmosphérique; Haute température; Système de protection thermique; Propriété radiative; Pyrolyse; Conductivité thermique; Rayonnement thermique; Carbone; Silice; Thermics; Atmospheric entry; High temperature; Thermal protection system; Radiative properties; Pyrolysis; Thermal conductivity; Heat transfer; Carbon; Silica; 536.230 72

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

APA (6^th Edition):

Le Foll, S. (2014). Modélisation du couplage conduction/rayonnement dans les systèmes de protection thermique soumis à de très hauts niveaux de températures : Coupled radiative/conductive heat transfer modeling in thermal protection systems at high temperature. (Doctoral Dissertation). INSA Lyon. Retrieved from http://www.theses.fr/2014ISAL0079

Chicago Manual of Style (16^th Edition):

Le Foll, Sébastien. “Modélisation du couplage conduction/rayonnement dans les systèmes de protection thermique soumis à de très hauts niveaux de températures : Coupled radiative/conductive heat transfer modeling in thermal protection systems at high temperature.” 2014. Doctoral Dissertation, INSA Lyon. Accessed March 01, 2021. http://www.theses.fr/2014ISAL0079.

MLA Handbook (7^th Edition):

Le Foll, Sébastien. “Modélisation du couplage conduction/rayonnement dans les systèmes de protection thermique soumis à de très hauts niveaux de températures : Coupled radiative/conductive heat transfer modeling in thermal protection systems at high temperature.” 2014. Web. 01 Mar 2021.

Vancouver:

Le Foll S. Modélisation du couplage conduction/rayonnement dans les systèmes de protection thermique soumis à de très hauts niveaux de températures : Coupled radiative/conductive heat transfer modeling in thermal protection systems at high temperature. [Internet] [Doctoral dissertation]. INSA Lyon; 2014. [cited 2021 Mar 01]. Available from: http://www.theses.fr/2014ISAL0079.

Council of Science Editors:

Le Foll S. Modélisation du couplage conduction/rayonnement dans les systèmes de protection thermique soumis à de très hauts niveaux de températures : Coupled radiative/conductive heat transfer modeling in thermal protection systems at high temperature. [Doctoral Dissertation]. INSA Lyon; 2014. Available from: http://www.theses.fr/2014ISAL0079

15. -9034-9438. Simulation of pyrolysis gas in a charring ablative thermal protection material using gas injection through a porous graphite sample.

Degree: PhD, Aerospace Engineering, 2018, University of Texas – Austin

URL: http://hdl.handle.net/2152/72664

► When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and friction heat the surrounding air to temperatures in excess of 6,000… (more)

▼ When a spacecraft traveling at orbital speeds enters a planetary atmosphere, shock waves and friction heat the surrounding air to temperatures in excess of 6,000 K. Often the only way to protect the spacecraft structure is to insulate it with a layer of sacrificial material that absorbs the heat by thermally degrading and ablating away. As the interior of the material heats up, it pyrolyzes into gaseous byproducts which are expelled through the charred surface of the material and provide an extra buffer between the hot free stream and the spacecraft. The performance of these charring ablative materials depends on poorly understood chemical, thermal, and mass flow interactions of the material with the superheated free stream fluid. The current work characterizes the flow and operating range of a new inductively coupled plasma based high enthalpy flow facility for testing high-temperature thermal protection materials. The facility uses magnetic induction to heat up to 1.5 g/s of air to temperatures of between 5000 K and 6500 K. The flow uniformity, total enthalpy and heat flux of the plasma stream are measured. Raman spectroscopy is used to measure the gas temperature within the flow and calculate an enthalpy distribution. The facility is used to investigate the effect that injection of ablation products into the boundary layer has on the heat flux into the material and mass loss rate of the char surface. The ablation process is simulated by injecting a gas mixture through a FiberForm test sample so that the flow and composition of pyrolysis products, which usually depend on the specific material composition, can be varied independently. It was found that all gas compositions tested reduced the rate of surface recession and chemically reactive mixtures reduced it the most. Emission spectroscopy in the boundary layer showed the mechanism to be reduced oxygen diffusion to the surface. However, if the heat of combustion of the pyrolysis products was too high, the heat flux to the surface was not reduced. For materials with above a 60% char yield, pyrolysis gases have little effect. Advisors/Committee Members: Clemens, Noel T. (advisor), Varghese, Philip L. (advisor), Raja, Laxminarayan (committee member), Hallock, Gary (committee member), Koo, Joseph (committee member), Greene, Benton (committee member).

Subjects/Keywords: Raman scattering; Plasma; ICP; Pyrolysis; Inductively coupled plasma; Ablation; Thermal protection system; Thermal protection; Charring ablator

…Spectroscopy .................................................... 22 1.3 Thermal Protection System… …thermal protection system mass in the overall spacecraft launch mass was the Galileo Probe… …give is that the instrumentation on the Galileo probe thermal protection system indicated… …developed for thermal protection system testing in the Soviet Union, with two facilities, IPG-1… …that the most important factor in the design of a thermal protection system is heat transfer…

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APA (6^th Edition):

-9034-9438. (2018). Simulation of pyrolysis gas in a charring ablative thermal protection material using gas injection through a porous graphite sample. (Doctoral Dissertation). University of Texas – Austin. Retrieved from http://hdl.handle.net/2152/72664

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Chicago Manual of Style (16^th Edition):

-9034-9438. “Simulation of pyrolysis gas in a charring ablative thermal protection material using gas injection through a porous graphite sample.” 2018. Doctoral Dissertation, University of Texas – Austin. Accessed March 01, 2021. http://hdl.handle.net/2152/72664.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

MLA Handbook (7^th Edition):

-9034-9438. “Simulation of pyrolysis gas in a charring ablative thermal protection material using gas injection through a porous graphite sample.” 2018. Web. 01 Mar 2021.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Vancouver:

-9034-9438. Simulation of pyrolysis gas in a charring ablative thermal protection material using gas injection through a porous graphite sample. [Internet] [Doctoral dissertation]. University of Texas – Austin; 2018. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/2152/72664.

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Council of Science Editors:

-9034-9438. Simulation of pyrolysis gas in a charring ablative thermal protection material using gas injection through a porous graphite sample. [Doctoral Dissertation]. University of Texas – Austin; 2018. Available from: http://hdl.handle.net/2152/72664

Note: this citation may be lacking information needed for this citation format:
Author name may be incomplete

Indian Institute of Science

16. Ajith, M R. Synthesis and Characterization of Silica-Silica Porous Composite and Calcium Strontium Zirconium Phosphate Ceramics for Thermal Protection Applications.

Degree: PhD, Faculty of Science, 2018, Indian Institute of Science

URL: http://etd.iisc.ac.in/handle/2005/3901

► A porous silica –silica composite was processed with varying fiber diameters using the slurry moulding technique. The advantage of the process was that the density… (more)

▼ A porous silica –silica composite was processed with varying fiber diameters using the slurry moulding technique. The advantage of the process was that the density of the composite could be processed to the required levels. The reinforcements used were fibers obtained by leaching E-glass cloth, imported silica fibers with diameter <1.8µ and hollow silica fibers processed using sol-gel method. All the properties depend on the density of the composite. The compressive strength was measured in the perpendicular and parallel directions. Strength was high when the load axis was along the fiber direction. The composite with fine fibers (< 1.8 µ pure silica fibers) showed higher strength compared to the leached silica fibers. The thermal conductivity measurement on these composites showed an increase with temperature owing to the domination of radiation at high temperatures. As the vacuum level was approached, the thermal conductivity showed a decrease due to the absence of the convective part of the thermal transfer process. For use as a thermal protection system, it is important to measure the thermal response of these tiles in a simulated re-entry environment. Tests were done to measure this response for a given heat flux conditions at 38W/cm2 to 75W/cm2 and the backwall temperature was measured for various types of silica -silica composites. The role of impurities like sodium and B2O3 was also studied with respect to the conversion from amorphous to crystalline forms of SiO2. The severe increase in the coefficient of thermal expansion when SiO2 converted from amorphous to α– crystoballite was also measured. CSZP CSZP which belongs to the NZP family was processed using the co-precipitation technique. The influence of substituting the ‘P’ site with ‘Si’ atom was studied for its influence on thermal expansion – both at the bulk level by dilatometry and at the intrinsic level using high temperature XRD. For many anisotropic materials micro-cracking is a serious issue while cooling from the sintering temperature. It has been previously proved that this extent of micro-cracking depends on the particle size. Smaller the particle size is therefore preferred. One of the significant results obtained in this study was the successful use of microwaves to process crack free CSZP with fine grain size. CSZP with 95% density having a grain size as small as 1µ have been processed using microwave sintering. Dielectric property evaluation namely dielectric constant, dielectric loss and temperature coefficient of resonant frequency which are vital parameters required if this material is to be used as a candidate TPS have also been measured. The thermal conductivity of the sample was measured using Laser flash apparatus and was found to be 0.9 W/mk which provides an indication that this material can be used as a successful material for TPS. Finally a composite consisting of silica fiber with CSZP as matrix was processed and tested for heat flux. The low back wall temperature indicates that this material is a potential replacement for… Advisors/Committee Members: Umarji, Arun M (advisor).

Subjects/Keywords: Silica-Silica Porous Composites; Calcium Strontium Zirconium Phosphaste Ceramics; Ceramics, Thermal Protection System; Amorphous Silica Fibers; Silica Fibers; Silica Composites; Silica Matrix Composites; CSZP; Ca0.5Sr0.5Zr4P6O24; Silica-Sllica Composites; Materials Science

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APA (6^th Edition):

Ajith, M. R. (2018). Synthesis and Characterization of Silica-Silica Porous Composite and Calcium Strontium Zirconium Phosphate Ceramics for Thermal Protection Applications. (Doctoral Dissertation). Indian Institute of Science. Retrieved from http://etd.iisc.ac.in/handle/2005/3901

Chicago Manual of Style (16^th Edition):

Ajith, M R. “Synthesis and Characterization of Silica-Silica Porous Composite and Calcium Strontium Zirconium Phosphate Ceramics for Thermal Protection Applications.” 2018. Doctoral Dissertation, Indian Institute of Science. Accessed March 01, 2021. http://etd.iisc.ac.in/handle/2005/3901.

MLA Handbook (7^th Edition):

Ajith, M R. “Synthesis and Characterization of Silica-Silica Porous Composite and Calcium Strontium Zirconium Phosphate Ceramics for Thermal Protection Applications.” 2018. Web. 01 Mar 2021.

Vancouver:

Ajith MR. Synthesis and Characterization of Silica-Silica Porous Composite and Calcium Strontium Zirconium Phosphate Ceramics for Thermal Protection Applications. [Internet] [Doctoral dissertation]. Indian Institute of Science; 2018. [cited 2021 Mar 01]. Available from: http://etd.iisc.ac.in/handle/2005/3901.

Council of Science Editors:

Ajith MR. Synthesis and Characterization of Silica-Silica Porous Composite and Calcium Strontium Zirconium Phosphate Ceramics for Thermal Protection Applications. [Doctoral Dissertation]. Indian Institute of Science; 2018. Available from: http://etd.iisc.ac.in/handle/2005/3901

University of Vermont

17. Dougherty, Maximilian. Numerical Simulations of Reacting Flow in an Inductively Coupled Plasma Torch.

Degree: PhD, Mechanical Engineering, 2015, University of Vermont

URL: https://scholarworks.uvm.edu/graddis/512

► In the design of a thermal protection system for atmospheric entry, aerothermal heating presents a major impediment to efficient heat shield design. Recombination of… (more)

▼ In the design of a thermal protection system for atmospheric entry, aerothermal heating presents a major impediment to efficient heat shield design. Recombination of atomic species in the boundary layer results in highly exothermic surface-catalyzed recombination reactions and an increase in the heat flux experienced at the surface. The degree to which these reactions increase the surface heat flux is partly a function of the heat shield material. Characterization of the catalytic behavior of these materials takes place in experimental facilities, however there is a dearth of detailed computational models for the fluid dynamic and chemical behavior of such facilities. A numerical model coupling finite rate chemical kinetics and high temperature thermodynamic and transport properties with a computational fluid dynamics flow solver has been developed to model the chemically reacting flow in the inductively coupled plasma torch facility at the University of Vermont. Simulations were performed modeling the plasma jet for hybrid oxygen-argon and nitrogen plasmas in order to validate the models developed in this work by comparison to experimentally-obtained data for temperature and relative species concentrations in the boundary layer above test articles. Surface boundary conditions for wall temperature and catalytic efficiency were utilized to represent the different test article materials used in the experimental facility. Good agreement between measured and computed data is observed. In addition, a code-to-code validation exercise was performed benchmarking the performance of the models developed in this dissertation by comparison to previously published results. Results obtained show good agreement for boundary layer temperature and species concentrations despite significant differences in the codes. Lastly, a series of simulations were performed investigating the effects of recombination reaction rates and pressure on the composition of a nitrogen plasma jet in chemical nonequilibrium in order to better understand the composition at the boundary layer edge above a test article. Results from this study suggest that, for typical test conditions, the boundary layer edge will be in a state of chemical nonequilibrium, leading to a nonequilibrium condition across the entire boundary layer for test article materials with high catalytic efficiencies. Advisors/Committee Members: Douglas Fletcher.

Subjects/Keywords: chemical nonequilibrium; finite rate chemistry; inductively coupled plasma; planetary entry; surface catalycity; thermal protection system; Aerospace Engineering; Mechanical Engineering; Plasma and Beam Physics

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APA (6^th Edition):

Dougherty, M. (2015). Numerical Simulations of Reacting Flow in an Inductively Coupled Plasma Torch. (Doctoral Dissertation). University of Vermont. Retrieved from https://scholarworks.uvm.edu/graddis/512

Chicago Manual of Style (16^th Edition):

Dougherty, Maximilian. “Numerical Simulations of Reacting Flow in an Inductively Coupled Plasma Torch.” 2015. Doctoral Dissertation, University of Vermont. Accessed March 01, 2021. https://scholarworks.uvm.edu/graddis/512.

MLA Handbook (7^th Edition):

Dougherty, Maximilian. “Numerical Simulations of Reacting Flow in an Inductively Coupled Plasma Torch.” 2015. Web. 01 Mar 2021.

Vancouver:

Dougherty M. Numerical Simulations of Reacting Flow in an Inductively Coupled Plasma Torch. [Internet] [Doctoral dissertation]. University of Vermont; 2015. [cited 2021 Mar 01]. Available from: https://scholarworks.uvm.edu/graddis/512.

Council of Science Editors:

Dougherty M. Numerical Simulations of Reacting Flow in an Inductively Coupled Plasma Torch. [Doctoral Dissertation]. University of Vermont; 2015. Available from: https://scholarworks.uvm.edu/graddis/512

University of Central Florida

18. Snapp, Cooper. Evaluation Of Space Shuttle Tile Subnominal Bonds.

Degree: 2006, University of Central Florida

URL: https://stars.library.ucf.edu/etd/831

► This study researched the history of Space Shuttle Reusable Surface Insulation which was designed and developed for use on the United States Orbiter fleet to… (more)

Subjects/Keywords: Space Shuttle; Thermal Protection System; tile; Orbiter; subnominal bond; Aerospace Engineering; Engineering

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APA (6^th Edition):

Snapp, C. (2006). Evaluation Of Space Shuttle Tile Subnominal Bonds. (Masters Thesis). University of Central Florida. Retrieved from https://stars.library.ucf.edu/etd/831

Chicago Manual of Style (16^th Edition):

Snapp, Cooper. “Evaluation Of Space Shuttle Tile Subnominal Bonds.” 2006. Masters Thesis, University of Central Florida. Accessed March 01, 2021. https://stars.library.ucf.edu/etd/831.

MLA Handbook (7^th Edition):

Snapp, Cooper. “Evaluation Of Space Shuttle Tile Subnominal Bonds.” 2006. Web. 01 Mar 2021.

Vancouver:

Snapp C. Evaluation Of Space Shuttle Tile Subnominal Bonds. [Internet] [Masters thesis]. University of Central Florida; 2006. [cited 2021 Mar 01]. Available from: https://stars.library.ucf.edu/etd/831.

Council of Science Editors:

Snapp C. Evaluation Of Space Shuttle Tile Subnominal Bonds. [Masters Thesis]. University of Central Florida; 2006. Available from: https://stars.library.ucf.edu/etd/831

University of Kentucky

19. Smith, David L. Comparisons of Ablator Experimental Performance to Response Modeling and Effects of Water Phase Transition in Porous TPS Materials.

Degree: 2016, University of Kentucky

URL: https://uknowledge.uky.edu/me_etds/83

► The Mars Science Laboratory Entry Descent and Landing Instrumentation (MEDLI) project performed extensive arc jet tests for development, qualification, and calibration of instrumented heat shield… (more)

▼ The Mars Science Laboratory Entry Descent and Landing Instrumentation (MEDLI) project performed extensive arc jet tests for development, qualification, and calibration of instrumented heat shield plugs. These plugs each contained several thermocouples for recording near-surface and in-depth temperature response of the Phenolic Impregnated Carbon Ablator (PICA) heat shield. The arc jet test results are entered into a comprehensive database so that broad trends across the test series can be compared. One method of analysis is to compare with ablator material response calculations and solve the in-depth heat conduction equations. Using the near-surface thermocouple measurements as a boundary condition in numerical simulations, comparisons are made with other thermocouple measurements taken deeper within the TPS test article. The work presented here uses this technique to compare test results with model simulations using several metrics, such as peak-temperature difference, maximum difference in temperature, and a total integrated temperature deviation. A significant difference in prediction behavior with respect to the location of source thermocouple is shown based on these comparisons. The temperature prediction accuracy is quantified for the tested material and material response code and is found to be highly dependent on the distance between the boundary condition thermocouple and the deeper reference thermocouple. Based on this test data, it is shown that numerical models can predict in-depth temperature measurements equally well for sensor plugs installed in the arc jet test model with or without a silicone adhesive. It is found that predicted temperatures are consistently greater than measured values, indicating the PICA material model is generally conservative for in-depth temperature predictions. In addition, a low-temperature phenomenon was consistently observed through thermocouple measurements deep within the material during the MEDLI arc jet testing. This anomaly, referred to here as the "hump," consists of a change in concavity of the temperature profile well below the maximum temperature and is seen in various TPS materials and atmospheric conditions, and typically occurs around 40 ºC. It is proposed that the observed ``hump" is a result of the heat of vaporization during the endothermic phase transition of water within the TPS material. This is supported by the known absorption of water by PICA from the atmosphere prior to testing or flight. The presented material response model captures energy effects of phase transition from a pre-existing water presence. This work shows that water presence currently appears to be the most probable cause for the phenomenon, which is observed in multiple different porous TPS materials.

Subjects/Keywords: atmospheric entry; thermal protection system; material response; numerical heat transfer; arc jet testing; experimental modeling; Aerodynamics and Fluid Mechanics; Aeronautical Vehicles; Heat Transfer, Combustion; Other Mechanical Engineering; Space Vehicles

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APA (6^th Edition):

Smith, D. L. (2016). Comparisons of Ablator Experimental Performance to Response Modeling and Effects of Water Phase Transition in Porous TPS Materials. (Masters Thesis). University of Kentucky. Retrieved from https://uknowledge.uky.edu/me_etds/83

Chicago Manual of Style (16^th Edition):

Smith, David L. “Comparisons of Ablator Experimental Performance to Response Modeling and Effects of Water Phase Transition in Porous TPS Materials.” 2016. Masters Thesis, University of Kentucky. Accessed March 01, 2021. https://uknowledge.uky.edu/me_etds/83.

MLA Handbook (7^th Edition):

Smith, David L. “Comparisons of Ablator Experimental Performance to Response Modeling and Effects of Water Phase Transition in Porous TPS Materials.” 2016. Web. 01 Mar 2021.

Vancouver:

Smith DL. Comparisons of Ablator Experimental Performance to Response Modeling and Effects of Water Phase Transition in Porous TPS Materials. [Internet] [Masters thesis]. University of Kentucky; 2016. [cited 2021 Mar 01]. Available from: https://uknowledge.uky.edu/me_etds/83.

Council of Science Editors:

Smith DL. Comparisons of Ablator Experimental Performance to Response Modeling and Effects of Water Phase Transition in Porous TPS Materials. [Masters Thesis]. University of Kentucky; 2016. Available from: https://uknowledge.uky.edu/me_etds/83

University of Kentucky

20. 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 01, 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. 01 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 01]. 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 Kentucky

21. Davuluri, Raghava Sai Chaitanya. Modeling of spallation phenomenon in an arc-jet environment.

Degree: 2015, University of Kentucky

URL: https://uknowledge.uky.edu/me_etds/63

► Space vehicles, while entering the planetary atmosphere, experience high loads of heat. Ablative materials are commonly used for a thermal protection system, which undergo mass… (more)

Subjects/Keywords: atmospheric entry; thermal protection system; ablation; spallation; Aerodynamics and Fluid Mechanics; Computational Engineering; Heat Transfer, Combustion; Numerical Analysis and Scientific Computing; Thermodynamics

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APA (6^th Edition):

Davuluri, R. S. C. (2015). Modeling of spallation phenomenon in an arc-jet environment. (Masters Thesis). University of Kentucky. Retrieved from https://uknowledge.uky.edu/me_etds/63

Chicago Manual of Style (16^th Edition):

Davuluri, Raghava Sai Chaitanya. “Modeling of spallation phenomenon in an arc-jet environment.” 2015. Masters Thesis, University of Kentucky. Accessed March 01, 2021. https://uknowledge.uky.edu/me_etds/63.

MLA Handbook (7^th Edition):

Davuluri, Raghava Sai Chaitanya. “Modeling of spallation phenomenon in an arc-jet environment.” 2015. Web. 01 Mar 2021.

Vancouver:

Davuluri RSC. Modeling of spallation phenomenon in an arc-jet environment. [Internet] [Masters thesis]. University of Kentucky; 2015. [cited 2021 Mar 01]. Available from: https://uknowledge.uky.edu/me_etds/63.

Council of Science Editors:

Davuluri RSC. Modeling of spallation phenomenon in an arc-jet environment. [Masters Thesis]. University of Kentucky; 2015. Available from: https://uknowledge.uky.edu/me_etds/63

University of Cincinnati

22. Sockalingam, Subramani. Coupling of Fluid Thermal Simulation for Nonablating Hypersonic Reentry Vehicles Using Commercial Codes FLUENT and LS-DYNA.

Degree: MS, Engineering : Mechanical Engineering, 2008, University of Cincinnati

URL: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1218801526

► A frame work has been setup for the simulation of hypersonic reentry vehicles using commercial codes FLUENT and LS-DYNA. The main goal of this work… (more)

Subjects/Keywords: Mechanical Engineering; Hypersonic Reentry Vehicles; Thermal Protection System TPS; Ablation

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APA (6^th Edition):

Sockalingam, S. (2008). Coupling of Fluid Thermal Simulation for Nonablating Hypersonic Reentry Vehicles Using Commercial Codes FLUENT and LS-DYNA. (Masters Thesis). University of Cincinnati. Retrieved from http://rave.ohiolink.edu/etdc/view?acc_num=ucin1218801526

Chicago Manual of Style (16^th Edition):

Sockalingam, Subramani. “Coupling of Fluid Thermal Simulation for Nonablating Hypersonic Reentry Vehicles Using Commercial Codes FLUENT and LS-DYNA.” 2008. Masters Thesis, University of Cincinnati. Accessed March 01, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1218801526.

MLA Handbook (7^th Edition):

Sockalingam, Subramani. “Coupling of Fluid Thermal Simulation for Nonablating Hypersonic Reentry Vehicles Using Commercial Codes FLUENT and LS-DYNA.” 2008. Web. 01 Mar 2021.

Vancouver:

Sockalingam S. Coupling of Fluid Thermal Simulation for Nonablating Hypersonic Reentry Vehicles Using Commercial Codes FLUENT and LS-DYNA. [Internet] [Masters thesis]. University of Cincinnati; 2008. [cited 2021 Mar 01]. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1218801526.

Council of Science Editors:

Sockalingam S. Coupling of Fluid Thermal Simulation for Nonablating Hypersonic Reentry Vehicles Using Commercial Codes FLUENT and LS-DYNA. [Masters Thesis]. University of Cincinnati; 2008. Available from: http://rave.ohiolink.edu/etdc/view?acc_num=ucin1218801526

University of Kentucky

23. Nichols, James Tyler. The Kentucky Re-Entry Universal Payload System (KRUPS): Orbital Flight.

Degree: 2021, University of Kentucky

URL: https://uknowledge.uky.edu/me_etds/165

► Due to the uniqueness of atmospheric entry environments, ground facilities cannot accurately replicate re-entry conditions. Consequently, scientists primarily rely on numerical models to predict these… (more)

Subjects/Keywords: Thermal Protection System; TPS; Cygnus; International Space Station; ISS; Re-entry Vehicle; Atmospheric Entry; Space Vehicles; Structures and Materials; Systems Engineering and Multidisciplinary Design Optimization

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APA (6^th Edition):

Nichols, J. T. (2021). The Kentucky Re-Entry Universal Payload System (KRUPS): Orbital Flight. (Masters Thesis). University of Kentucky. Retrieved from https://uknowledge.uky.edu/me_etds/165

Chicago Manual of Style (16^th Edition):

Nichols, James Tyler. “The Kentucky Re-Entry Universal Payload System (KRUPS): Orbital Flight.” 2021. Masters Thesis, University of Kentucky. Accessed March 01, 2021. https://uknowledge.uky.edu/me_etds/165.

MLA Handbook (7^th Edition):

Nichols, James Tyler. “The Kentucky Re-Entry Universal Payload System (KRUPS): Orbital Flight.” 2021. Web. 01 Mar 2021.

Vancouver:

Nichols JT. The Kentucky Re-Entry Universal Payload System (KRUPS): Orbital Flight. [Internet] [Masters thesis]. University of Kentucky; 2021. [cited 2021 Mar 01]. Available from: https://uknowledge.uky.edu/me_etds/165.

Council of Science Editors:

Nichols JT. The Kentucky Re-Entry Universal Payload System (KRUPS): Orbital Flight. [Masters Thesis]. University of Kentucky; 2021. Available from: https://uknowledge.uky.edu/me_etds/165

24. Marley, Christopher. Thermal Management in a Scramjet-Powered Hypersonic Cruise Vehicle.

Degree: PhD, Aerospace Engineering, 2018, University of Michigan

URL: http://hdl.handle.net/2027.42/144038

► Due to the large aerodynamic heating at high Mach numbers, Thermal Protection System (TPS) design considerations are critical for hypersonic vehicles, and engineers seek to… (more)

▼ Due to the large aerodynamic heating at high Mach numbers, Thermal Protection System (TPS) design considerations are critical for hypersonic vehicles, and engineers seek to incorporate heating constraints earlier in the design process. Preliminary design studies necessitate the use of low-fidelity tools for design and optimization purposes. A number of low-fidelity models exist in the open literature for full scramjet-powered hypersonic vehicles, and some of these models incorporate passive TPS models (where the material on the outer surface of the vehicle absorbs energy, preventing the energy from seeping into the structure). However, none of the models incorporate an active TPS (where the fuel is used as a coolant in the heat exchangers surrounding the engine) in addition to a passive TPS model. In the present work, active and passive TPS models were added to a full scramjet-powered vehicle model developed at the University of Michigan. For a trimmed hypersonic waverider vehicle, computations were performed to investigate the operability limits that occur due to excessive heating of the external surface, including the nose region and combustor wall region, and the heating of the hydrogen fuel, which is used as coolant. The operability limits computed include the maximum values of flight Mach number, dynamic pressure and the flight time before one of several temperature limits is exceeded. To compute operability limits, efficient aerodynamic heating and TPS models were added to the reduced order model MASIV which contains an advanced combustion analysis and a trim code. Results show the effects of varying the thickness of the three-layer thermal protection system that consists of a radiation shield, an insulation layer and the vehicle wall. Regarding the active cooling system, the heat exchanger heat flux is modeled assuming the hydrogen fuel is a supercritical fluid and lookup tables for the fuel properties at supercritical conditions are incorporated. Recirculating the heated fuel back into the fuel tank raises the fuel temperature and decreases the fuel density (increasing the volume); the analysis computes the maximum flight time before the fuel tank temperature and fuel volume exceed acceptable limits. By extending the active cooling system to a small region of the inlet (instead of just around the isolator and combustor), the operability limits are increased from a flight Mach number of 7.3 to 8.6. Optimizations for the active and passive thermal protection systems are performed. For the passive thermal protection system, the optimal insulation thickness distributions are found which minimize the insulation mass while still ensuring that the titanium skin remains below its failure temperature. At a 40 minute cruise at Mach 6 and 80 kPa free-stream dynamic pressure, the optimized insulation mass is 74 percent less than the initial condition. For the active TPS, the parameters impacting the final fuel temperature are optimized to find the minimum fuel temperature at the end of a 40 minute cruise. The coolant… Advisors/Committee Members: Driscoll, James F (committee member), Johnsen, Eric (committee member), Cesnik, Carlos E (committee member), Martins, Joaquim R R A (committee member).

Subjects/Keywords: Hypersonic Cruise Vehicle; Active Thermal Protection System (TPS); Passive Thermal Protection System (TPS); Scramjet; Aerospace Engineering; Engineering

…the thermal protection system, compared to the present work… …10 3.1 Passive thermal protection system layers for results shown in Figs. 3.3, 3.4… …external surface passive thermal protection system for cruise at M∞ = 8, q∞ = 60 kPa… …69 Maximum temperatures in vehicle external surface passive thermal protection system at M… …x5D; energy [J] specific enthalpy [J/kg], thermal protection system…

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APA (6^th Edition):

Marley, C. (2018). Thermal Management in a Scramjet-Powered Hypersonic Cruise Vehicle. (Doctoral Dissertation). University of Michigan. Retrieved from http://hdl.handle.net/2027.42/144038

Chicago Manual of Style (16^th Edition):

Marley, Christopher. “Thermal Management in a Scramjet-Powered Hypersonic Cruise Vehicle.” 2018. Doctoral Dissertation, University of Michigan. Accessed March 01, 2021. http://hdl.handle.net/2027.42/144038.

MLA Handbook (7^th Edition):

Marley, Christopher. “Thermal Management in a Scramjet-Powered Hypersonic Cruise Vehicle.” 2018. Web. 01 Mar 2021.

Vancouver:

Marley C. Thermal Management in a Scramjet-Powered Hypersonic Cruise Vehicle. [Internet] [Doctoral dissertation]. University of Michigan; 2018. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/2027.42/144038.

Council of Science Editors:

Marley C. Thermal Management in a Scramjet-Powered Hypersonic Cruise Vehicle. [Doctoral Dissertation]. University of Michigan; 2018. Available from: http://hdl.handle.net/2027.42/144038

25. Cong, Yuhang. Synchronized Measurement Technology Supported Operational Tripping Schemes.

Degree: 2016, University of Manchester

URL: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:301116

► The increasing volume of renewable and intermittent generation that is being connected to power systems means that system operators need more advanced dynamic control tools… (more)

Subjects/Keywords: Power System; Power System Protection; System Integrity Protection Scheme; Operational Tripping Scheme; Dynamic Thermal Line Rating; Conductor/Transformer Heating

…considered to be intelligent, adaptive and efficient SIPS for the thermal protection of system… …thermal protection scheme. If a disturbance occurs in the power system, the post-fault current… …conventional thermal protection schemes and understand the thermal behaviour of system elements… …thermal protection of system elements. As such, they can be considered as a typical Smart Grid… …this thesis is to design intelligent system integrity protection schemes (SIPS)…

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

APA (6^th Edition):

Cong, Y. (2016). Synchronized Measurement Technology Supported Operational Tripping Schemes. (Doctoral Dissertation). University of Manchester. Retrieved from http://www.manchester.ac.uk/escholar/uk-ac-man-scw:301116

Chicago Manual of Style (16^th Edition):

Cong, Yuhang. “Synchronized Measurement Technology Supported Operational Tripping Schemes.” 2016. Doctoral Dissertation, University of Manchester. Accessed March 01, 2021. http://www.manchester.ac.uk/escholar/uk-ac-man-scw:301116.

MLA Handbook (7^th Edition):

Cong, Yuhang. “Synchronized Measurement Technology Supported Operational Tripping Schemes.” 2016. Web. 01 Mar 2021.

Vancouver:

Cong Y. Synchronized Measurement Technology Supported Operational Tripping Schemes. [Internet] [Doctoral dissertation]. University of Manchester; 2016. [cited 2021 Mar 01]. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:301116.

Council of Science Editors:

Cong Y. Synchronized Measurement Technology Supported Operational Tripping Schemes. [Doctoral Dissertation]. University of Manchester; 2016. Available from: http://www.manchester.ac.uk/escholar/uk-ac-man-scw:301116

Université de Bordeaux I

26. Nguyen, Huy Cuong. Modélisation électrothermique de système électrique électronique automobile et pilotage de mosfet intelligents pour protéger les faisceaux, éviter les courts circuits aggravés et diminuer la masse de câblage : The experience of the visit and construction of knowledge : the case of science museums and scientific cultural centers.

Degree: Docteur es, Automatique et productique, signal et image, 2013, Université de Bordeaux I

URL: http://www.theses.fr/2013BOR14776

►

Sur les différents calculateurs du véhicule, de plus en plus d'organes sont commandés par un interrupteur en silicium (circuit MOSFET) au lieu d'un relais. En… (more)

▼

Sur les différents calculateurs du véhicule, de plus en plus d'organes sont commandés par un interrupteur en silicium (circuit MOSFET) au lieu d'un relais. En plus de la fonction de commutation de puissance, le MOSFET peut comprendre un dispositif de mesure du courant afin de contrôler le pilotage de l'organe et/ou assurer une fonction de diagnostic. On appelle ce type de composant un commutateur intelligent de puissance ou Smart Switch. Il est aussi prévu dans le Smart Switch un dispositif de coupure du courant, en cas d'échauffement interne dû à une surintensité électrique. Avec les dernières avancées technologiques, ces composants peuvent aussi intégrer de la logique de pilotage et une interface de liaison numérique avec un microprocesseur. Cette dernière caractéristique motive lesujet de l'étude afin de définir des lois de protection améliorées contre les échauffements dus à une surintensité électrique.En effet, d’un point de vue de la protection électrique, le MOSFET a été conçu pour obtenir les mêmes caractéristiques qu’un fusible, avec la possibilité supplémentaire d’être réenclenché comme un disjoncteur. Le but est d’étudier les lois de pilotage qui pourraient permettre de mieux suivre les limites thermiques d’un conducteur électrique, en particulier dans les faibles surintensités, de façon à pouvoir diminuer le diamètre (donc le coût) des fils tout en assurant une meilleure protection face aux courts circuits impédants (courts-circuits sur une résistance un peu inférieure à la résistance nominale ducircuit, dans un rapport entre 1 et 3 par exemple).

On various vehicles Electronic Control Unit (ECU), more and more members are controlled bya MOSFET circuits instead of a relay. In addition to the power switching function, the MOSFET maymeasure the current to the steering control of the body and / or to ensure that a diagnostic function. Wecall this type of component a smart power switch or Smart Switch. It is also provided in the SmartSwitch device power failure, if the internal heating caused by electrical current. With the latesttechnology, these components can also integrate control logic and an interface for connection to adigital microprocessor. This last characteristic motivates the subject of study in order to defineimproved protection laws against overheating caused by an electrical current.Indeed, from the point of view of electrical protection, the MOSFET has been designed toachieve the same characteristics as a fuse, with the additional possibility to be reset as a circuit breaker.The aim is to study the control laws that could lead to better monitor the thermal limits of an electricalconductor, especially in low current, so as to reduce the diameter (hence the cost) of son while ensuringbetter protection against short-circuit-impedance (short circuit resistance of a little less than thenominal resistance of the circuit, in a ratio between 1 and 3 for example).

Advisors/Committee Members: Moreau, Xavier (thesis director), Sabatier, Jocelyn (thesis director).

Subjects/Keywords: Mosfet; Câblage; Modélisation électrothermique; Protection; Court-circuits; Dérivation non-entière; Estimateurs; Dimensionnement de système électrique; Electronique automobile; Contrôle/commande; Electrothermique; Fusibles; Mosfet; Harness; Thermal electrical modeling; Protection; Short circuit; Estimation; Fractional derivative; Sizing electric; Car electronic system; Control; Smart fuse; Mosfet

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

APA (6^th Edition):

Nguyen, H. C. (2013). Modélisation électrothermique de système électrique électronique automobile et pilotage de mosfet intelligents pour protéger les faisceaux, éviter les courts circuits aggravés et diminuer la masse de câblage : The experience of the visit and construction of knowledge : the case of science museums and scientific cultural centers. (Doctoral Dissertation). Université de Bordeaux I. Retrieved from http://www.theses.fr/2013BOR14776

Chicago Manual of Style (16^th Edition):

Nguyen, Huy Cuong. “Modélisation électrothermique de système électrique électronique automobile et pilotage de mosfet intelligents pour protéger les faisceaux, éviter les courts circuits aggravés et diminuer la masse de câblage : The experience of the visit and construction of knowledge : the case of science museums and scientific cultural centers.” 2013. Doctoral Dissertation, Université de Bordeaux I. Accessed March 01, 2021. http://www.theses.fr/2013BOR14776.

MLA Handbook (7^th Edition):

Nguyen, Huy Cuong. “Modélisation électrothermique de système électrique électronique automobile et pilotage de mosfet intelligents pour protéger les faisceaux, éviter les courts circuits aggravés et diminuer la masse de câblage : The experience of the visit and construction of knowledge : the case of science museums and scientific cultural centers.” 2013. Web. 01 Mar 2021.

Vancouver:

Nguyen HC. Modélisation électrothermique de système électrique électronique automobile et pilotage de mosfet intelligents pour protéger les faisceaux, éviter les courts circuits aggravés et diminuer la masse de câblage : The experience of the visit and construction of knowledge : the case of science museums and scientific cultural centers. [Internet] [Doctoral dissertation]. Université de Bordeaux I; 2013. [cited 2021 Mar 01]. Available from: http://www.theses.fr/2013BOR14776.

Council of Science Editors:

Nguyen HC. Modélisation électrothermique de système électrique électronique automobile et pilotage de mosfet intelligents pour protéger les faisceaux, éviter les courts circuits aggravés et diminuer la masse de câblage : The experience of the visit and construction of knowledge : the case of science museums and scientific cultural centers. [Doctoral Dissertation]. Université de Bordeaux I; 2013. Available from: http://www.theses.fr/2013BOR14776

Brno University of Technology

27. Konečná, Petra. Domov pro seniory v Telnici: Pension for the Elderly in Telnice.

Degree: 2019, Brno University of Technology

URL: http://hdl.handle.net/11012/29735

► Topic of this master’s thesis is a retirement house in village Telnice. The project was designed directly for village Telnice according to their requirements. It… (more)

Subjects/Keywords: Domov pro seniory; Sedlová střecha; Plochá střecha; Zděný systém; Kontaktní zateplovací systém; Tepelná technika; Požární ochrana budovy; Betonové konstrukce; Kanalizace; Retirement house; Saddle roof; Flat roof; Brick masonry; Thermal insulation system; Thermal protection of building; Fire safety of building; Concrete constructions; Sewerage

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

APA (6^th Edition):

Konečná, P. (2019). Domov pro seniory v Telnici: Pension for the Elderly in Telnice. (Thesis). Brno University of Technology. Retrieved from http://hdl.handle.net/11012/29735

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):

Konečná, Petra. “Domov pro seniory v Telnici: Pension for the Elderly in Telnice.” 2019. Thesis, Brno University of Technology. Accessed March 01, 2021. http://hdl.handle.net/11012/29735.

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

MLA Handbook (7^th Edition):

Konečná, Petra. “Domov pro seniory v Telnici: Pension for the Elderly in Telnice.” 2019. Web. 01 Mar 2021.

Vancouver:

Konečná P. Domov pro seniory v Telnici: Pension for the Elderly in Telnice. [Internet] [Thesis]. Brno University of Technology; 2019. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/11012/29735.

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

Council of Science Editors:

Konečná P. Domov pro seniory v Telnici: Pension for the Elderly in Telnice. [Thesis]. Brno University of Technology; 2019. Available from: http://hdl.handle.net/11012/29735

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

28. Zinner, Evan J. Assessment of aerocapture-entry trajectories for human Mars exploration.

Degree: MS, Aerospace Engineering, 2019, University of Illinois – Urbana-Champaign

URL: http://hdl.handle.net/2142/104938

► Using aerocapture to insert into an elliptic parking orbit prior to entry, descent, and landing is being explored for human Mars missions. These aerocapture-entry trajectories… (more)

Subjects/Keywords: Mars Entry Descent Landing Human Exploration Aerocapture Aerocapture-entry TPS Thermal Protection System Parking Orbit

…Mars. [7] Figure. 3: Illustration of ablative thermal protection system [10… …component of the lift vector. 11 The thermal protection system (TPS) material on the… …is the most important criterion for thermal protection system thickness. This correlation… …determine the required thickness of the forebody thermal protection system for aerocapture and EDL… …using an insulating thermal protection system. The same approach is taken to determining the…

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

APA (6^th Edition):

Zinner, E. J. (2019). Assessment of aerocapture-entry trajectories for human Mars exploration. (Thesis). University of Illinois – Urbana-Champaign. Retrieved from http://hdl.handle.net/2142/104938

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):

Zinner, Evan J. “Assessment of aerocapture-entry trajectories for human Mars exploration.” 2019. Thesis, University of Illinois – Urbana-Champaign. Accessed March 01, 2021. http://hdl.handle.net/2142/104938.

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

MLA Handbook (7^th Edition):

Zinner, Evan J. “Assessment of aerocapture-entry trajectories for human Mars exploration.” 2019. Web. 01 Mar 2021.

Vancouver:

Zinner EJ. Assessment of aerocapture-entry trajectories for human Mars exploration. [Internet] [Thesis]. University of Illinois – Urbana-Champaign; 2019. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/2142/104938.

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

Council of Science Editors:

Zinner EJ. Assessment of aerocapture-entry trajectories for human Mars exploration. [Thesis]. University of Illinois – Urbana-Champaign; 2019. Available from: http://hdl.handle.net/2142/104938

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

Delft University of Technology

29. Clar, Thibault (author). Development and application of a Multidisciplinary Design Optimisation sizing platform for the conceptual design of hypersonic long-range transport aircraft.

Degree: 2019, Delft University of Technology

URL: http://resolver.tudelft.nl/uuid:2ca126a0-b302-4190-b03d-a9bcf8bed8d4

►

With the global increase in passenger traffic and growing popularity of long-haul routes over the Asia Pacific region and Atlantic Ocean, the possibility for hypersonic… (more)

Subjects/Keywords: Hypersonic Transport; Multi-Disciplinary Optimisation; Thermal Protection System; Mass estimation; Liquid hydrogen; Hypersonic Engineering Methods; Parametric model; CAD; Automatic meshing; HASA; WAATs; Viscous empirical corrections; PANAIR; Shape Optimisation; Hypersonic engine model

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

APA (6^th Edition):

Clar, T. (. (2019). Development and application of a Multidisciplinary Design Optimisation sizing platform for the conceptual design of hypersonic long-range transport aircraft. (Masters Thesis). Delft University of Technology. Retrieved from http://resolver.tudelft.nl/uuid:2ca126a0-b302-4190-b03d-a9bcf8bed8d4

Chicago Manual of Style (16^th Edition):

Clar, Thibault (author). “Development and application of a Multidisciplinary Design Optimisation sizing platform for the conceptual design of hypersonic long-range transport aircraft.” 2019. Masters Thesis, Delft University of Technology. Accessed March 01, 2021. http://resolver.tudelft.nl/uuid:2ca126a0-b302-4190-b03d-a9bcf8bed8d4.

MLA Handbook (7^th Edition):

Clar, Thibault (author). “Development and application of a Multidisciplinary Design Optimisation sizing platform for the conceptual design of hypersonic long-range transport aircraft.” 2019. Web. 01 Mar 2021.

Vancouver:

Clar T(. Development and application of a Multidisciplinary Design Optimisation sizing platform for the conceptual design of hypersonic long-range transport aircraft. [Internet] [Masters thesis]. Delft University of Technology; 2019. [cited 2021 Mar 01]. Available from: http://resolver.tudelft.nl/uuid:2ca126a0-b302-4190-b03d-a9bcf8bed8d4.

Council of Science Editors:

Clar T(. Development and application of a Multidisciplinary Design Optimisation sizing platform for the conceptual design of hypersonic long-range transport aircraft. [Masters Thesis]. Delft University of Technology; 2019. Available from: http://resolver.tudelft.nl/uuid:2ca126a0-b302-4190-b03d-a9bcf8bed8d4

30. Sidor, Adam Thomas. Design and manufacturing of conformal ablative heatshields.

Degree: PhD, Aerospace Engineering, 2019, Georgia Tech

URL: http://hdl.handle.net/1853/61593

► Conformal ablators, first introduced in the early 2000s under the NASA Hypersonics Project, are a type of rigid ablative thermal protection system that uses flexible,… (more)

▼ Conformal ablators, first introduced in the early 2000s under the NASA Hypersonics Project, are a type of rigid ablative thermal protection system that uses flexible, rather than rigid, fibrous substrates. These materials are impregnated with resin in a mold to yield a part that is close to the final geometry and requires little post-process machining (a near net shape part). The lack of fiber connectivity through the thickness enables the TPS to tolerate larger strains than comparable rigid substrate ablators facilitating larger tiles and installation on most aeroshells without strain isolation. Reduced part count and simplified integration drive reductions in labor, cost and complexity –advancements which are enabling for planetary and human missions. Conformal ablators are currently fabricated using an open liquid impregnation process adapted from a technique developed for Lightweight Ceramic Ablators, such as Phenolic Impregnated Carbon Ablator, which leads to design and manufacturing inefficiencies. This work advanced a new manufacturing technique for conformal ablators, vacuum infusion processing, that reduces resin consumption and streamlines clean up. The closed process also eliminates an expensive atmosphere-controlled oven or vacuum chamber. A design methodology, centered around a simulation of the mold filling process, was developed to tailor a conformal ablative heatshield to vacuum infusion processing. A constitutive model, combining properties of individual components, was formulated to estimate the properties of the composite TPS material. The methodology leverages this model, integrated with material selection, tile layout, and the mold filling simulation, to automate a conceptual conformal heatshield design. The approach allows rapid iteration on TPS composition and manufacturing constraints. Advisors/Committee Members: Braun, Robert D. (advisor), Kennedy, Graeme J. (advisor), Rimoli, Julian J. (committee member), Beck, Robin A. (committee member), Stackpoole, Margaret M. (committee member).

Subjects/Keywords: Thermal protection system; Heatshield; Heat shield; Materials; Optimization; Manufacturing; Design; Vacuum infusion

…1.3 Classification of thermal protection system materials. . . . . . . . . . . . . 4 1.4… …STF Strain to failure TGA Thermogravimetric analysis TPS Thermal Protection System… …thermal protection system that use flexible, rather than rigid, fibrous substrates. These… …Figure 1.3: Classification of thermal protection system materials. Other classifications can… …protection system (TPS), or heat shield, forms the outermost layer of an entry system…

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

APA (6^th Edition):

Sidor, A. T. (2019). Design and manufacturing of conformal ablative heatshields. (Doctoral Dissertation). Georgia Tech. Retrieved from http://hdl.handle.net/1853/61593

Chicago Manual of Style (16^th Edition):

Sidor, Adam Thomas. “Design and manufacturing of conformal ablative heatshields.” 2019. Doctoral Dissertation, Georgia Tech. Accessed March 01, 2021. http://hdl.handle.net/1853/61593.

MLA Handbook (7^th Edition):

Sidor, Adam Thomas. “Design and manufacturing of conformal ablative heatshields.” 2019. Web. 01 Mar 2021.

Vancouver:

Sidor AT. Design and manufacturing of conformal ablative heatshields. [Internet] [Doctoral dissertation]. Georgia Tech; 2019. [cited 2021 Mar 01]. Available from: http://hdl.handle.net/1853/61593.

Council of Science Editors:

Sidor AT. Design and manufacturing of conformal ablative heatshields. [Doctoral Dissertation]. Georgia Tech; 2019. Available from: http://hdl.handle.net/1853/61593

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Open Access Theses and Dissertations