Publications
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Assessment of the Mars Helicopter Thermal Design Sensitivities Using the Veritrek Software
The Mars Helicopter will be a technology demonstration conducted during the Mars 2020 mission. The primary mission objective is to achieve several 90-second flights and capture visible light images via forward and nadir mounted cameras. These flights could possibly provide reconnaissance data for sampling site selection for other Mars surface missions. The helicopter is powered by a solar array, which stores energy in secondary batteries for flight operations, imaging, communications, and survival heating. The helicopter thermal design is driven by minimizing survival heater energy while maintaining compliance with allowable flight temperatures in a variable thermal environment. Due to the small size of the helicopter and its complex geometries, along with the fact that it operates with very low power and small margins, additional care had to be paid while planning thermal tests and designing the thermal system. A Thermal Desktop® model has been developed to predict the thermal system’s performance. A reduced-order model (ROM) created with the Veritrek software has been utilized to explore the sensitivities of the thermal system’s drivers, such as electronics dissipations, gas gaps, heat transfer coefficients, etc., as well as to assess and verify the final thermal design. This paper presents the performance of the Veritrek software products and the details of the ROM creation process. The results produced by Veritrek were utilized to study the effect of the major thermal design drivers and Mars environment on the Mars Helicopter in as little as 10 days, an effort that would have taken over 4 months using traditional thermal analysis techniques.
Publication: 2018-assessmentofthemarshelicopterthermaldesignsensitivitiesusingtheveritreksoftware.pdf
Source: TFAWS 2018
Author: Stefano Cappucci, Michael T. Pauken, Jacob A. Moulton, Derek W. Hengeveld
Year: 2018
Content Tags: third-party software, heater, emissivity, absortivity, conduction, heat loads, convection heat transfer, sweep, design space scanning, output, robust engineering, validation, design optimization
Integrated Analysis of Thermal/Structural/Optical Systems
Productivity bottlenecks for integrated thermal, structural, and optical design activities were identified and systematically eliminated, making possible automated exchange of design information between different engineering specialties.
The problems with prior approaches are summarized, then the implementation of the corresponding solutions is documented. Although the goal of this project was the automated evaluation of coupled thermal/optical/structural designs, significant process improvements were achieved for subset activities such as stand-alone thermal, thermal/ structural, and structural/optical design analysis.
Publication: optiOpt-ICES2002a.pdf
Source: Semi-Therm
Author: B. Cullimore, T. Panczak, J. Baumann, Dr. Victor Genberg, Mark Kahan
Year: 2002
Content Tags: finite element, finite elements, finite difference, parametric, conductance, contact conductance, design optimization, robust design, optical, registers, radiation, dynamic SINDA, dynamic mode
Automated Multidisciplinary Optimization of a Space-based Telescope
Automated design space exploration was implemented and demonstrated in the form of the multidisciplinary optimization of the design of a space-based telescope.
Off-the-shelf software representing the industry standards for thermal, structural, and optical analysis were employed. The integrated thermal/structural/optical models were collected and tasked with finding an optimum design using yet another off-the-shelf program. Using this integrated tool, the minimum mass thermal/structural design was found that directly satisfied optical performance requirements without relying on derived requirements such as isothermality and mechanical stability. Overdesign was therefore avoided, and engineering productivity was greatly improved.
This ambitious project was intended to be a pathfinder for integrated design activities. Therefore, difficulties and lessons learned are presented, along with recommendations for future investigations.
Publication: optiOpt-ICES2002b.pdf
Source: ICES
Author: B. Cullimore, T. Panczak, J. Baumann
Year: 2002
Content Tags: concurrent engineering, design optimization, parametric, robust design, design variables
Thermoelastic Analysis in Design
This study explores the capability of Thermal Desktop to map temperatures from a thermal model to a Nastran model to evalautate thermal stress and distortion
Publication: bell_thermoelastic.pps
Source: Aerospace Thermal Control Workshop
Author: William Bell & Paul-W. Young
Year: 2005
Content Tags: chilldown, thermal stress, third-party software, convection heat transfer, walls, heat flux, convergence, temperature map, temperature mapping, finite element, finite elements, material properties, heat pipe, heatpipe, pipes
JWST Testing Issues – Thermal & Structural
This study explores JWST thermal and structural testing issues and possible solutions, as presented to NASA in June 2004
Publication: bell_telescope.pps
Source: Aerospace Thermal Control Workshop 2005
Author: William Bell, Frank Kudirka, & Paul-W. Young
Year: 2005
Content Tags: chilldown, refrigeration cycle, convection heat transfer, insulation, radiation, flow regime mapping, radiation analysis groups
Free Molecular Heat Transfer Programs for Setup and Dynamic Updating the Conductors in Thermal Desktop
Thermal Desktop has the capability of modeling free molecular heat transfer (FMHT), but limitations are observed when working with large models during transient operation. To overcome this limitation, a MatLab program was developed that processes the Thermal Desktop free molecular conductors. It sets up the logic and arrays for the Thermal Desktop GUI used by SINDA/FLUINT. The theory of free molecular heating is presented along with the process required to setup the conductors, arrays, logic and Fortran subroutines for FMHT modeling in Thermal Desktop.
Publication: TFAWS07-1013.pdf
Source: TFAWS
Author: Eric T. Malroy
Year: 2007
Content Tags: transient, third-party software, user-defined Fortran array, radiation analysis groups, surface elements, radiation, radiation calculations, case set manager, user-defined Fortran arrays (UDFAs), submodels, radks
Thermal Model Development for Ares I-X
Publication: TFAWS-08-1018_presentation.pdf
Source: TFAWS
Author: Ruth M. Amundsen, Joe Del Corso
Year: 2008
Content Tags: third-party software, thermal stress, material properties, optical properties, conduction, convection heat transfer, radiation, submodels, radiation analysis groups, expression editor, symbol, symbols, symbol manager, logic manager, logic, user logic, boundary conditions, CFD
Crew Exploration Vehicle Composite Pressure Vessel Thermal Assessment
The Crew Exploration Vehicle (CEV) is the next generation space vehicle to follow the Space Shuttle. A design with the inclusion of a Composite Pressure Vessel (CPV) has been assessed for its thermal response. The temperature distribution on the CPV that results from the heat produced by internal spacecraft systems and external space environments was calculated as part of a project-level assessment to understand thermomechanical stresses. A finite element translation of the crew module CPV was integrated into an existing CEV Thermal Math Model (TMM) based on the 605 baseline configuration and analyzed for four orbital cases. Steady state temperature profiles were generated based on orbit average heating. Preliminary thermal analysis results suggest that the CPV requires less make-up energy when compared to the baseline aluminum pressure vessel. It is emphasized that only local make-up energy was considered in the study. The make-up energy did not include the zoning configuration that occurs with heaters. This document presents the approach and assumptions used for this thermal assessment.
Publication: TFAWS-08-1007_presentation.pdf
Source: TFAWS
Author: Laurie Y. Carrillo, Ángel R. Álvarez-Hernández, Steven L. Rickman
Year: 2008
Content Tags: finite element, finite elements, orbit, steady state, surface, optical properties, boundary conditions, temperature map, temperature mapping
Adaptive Thermal Modeling Architecture for Small Satellite Applications
The United States Air Force and commercial aerospace industry recognize the importance of moving towards smaller, better, and cheaper spacecraft to support the nation’s increasing dependence on space-based technologies. Whether large or small, all spacecraft will require the same basic bus systems and environmental protection, simply scaled to fit the mission. The varying thermal environment in space is particularly important to spacecraft design and operation because of its affect on hardware performance and survivability. The Adaptive Thermal Modeling Architecture (ATMA) discussed in this thesis is meant to bridge the gap between the commercially available thermal modeling tools used for larger, more expensive satellites, and the low-fidelity algorithms and techniques used for simple first order analysis.
The ATMA consists of the MATLAB based Adaptive Thermal Modeling Tool (ATMT) and its user’s manual, as well as the process by which an inexperienced engineer can quickly and accurately perform on-orbit thermal trades studies for a range of space applications. The ATMA tools and techniques have been validated with an industry standard thermal modeling program (Thermal Desktop) and correlated to thermal test data taken from MIT’s CASTOR nanosatellite. The concepts derived and evaluated within ATMA can be extended to a variety of aerospace modeling applications. The ATMT program and modeling architecture are currently being utilized by members of MIT’s Space Engineering Academy (SEA) and undergraduate satellite team as well as the U.S. Air Force Academy’s FalconSAT-6 program.
Publication: SM-2010-RichmondJohn.pdf
Source:
Author: 2Lt. John Anger Richmond, USAF, Colonel John Keesee, USAF Retired
Year: 2010
Content Tags: model correlation, orbit, third-party software, radiation, material properties, surface, meshing, validation, conductance
Improvements to a Response Surface Thermal Model for Orion
Publication: TFAWS2011-PT-006.pps
Source: TFAWS
Author: Stephen W. Miller, William Q. Walker
Year: 2011
Content Tags: statistical methods, radiator, CAD geometry, radiation, orbit, parameterize, ray tracing, radks, steady state, dynamic mode, dynamic SINDA
Analysis of Post-reentry Heating and Soak-back Affects in Unsealed Reentry Vehicles
Maintaining low temperature payloads through atmospheric reentry and ground recovery is becoming a larger focus in the space program as work in biology, cryogenic and other temperature dependent sciences becomes a higher goal on the International Space Station (ISS) and extraterrestrial surfaces. Paragon analyzes reentry system thermal control, particularly technology regarding small thermally controlled payloads anticipated for use in sample return from the International Space Station.
To minimize system mass and utilize the powerful insulative properties of a hard space vacuum the internal cavity of a small reentry vehicle can be left open. Thermally this causes concern during reentry, as even at very high altitudes there is enough pressure to cause a significant impact on insulation stratagems, such as MLI that rely on a high vacuum. At lower altitudes the vehicle is moving much slower, so the intense heat load of reentry is finished but soak-back from outer heated surfaces to the payload is a significant issue when air is present to facilitate heat transfer between layers. Initial assumptions that the cold temperatures of the upper atmosphere would cause a net cooling affect in the post-reentry times were overturned by a simple analysis set done in Thermal Desktop involving worst and best case scenarios as air starts to enter the vehicle. Additionally, CFD low pressure zones were shown to exist behind the vehicle where it is open to the atmosphere when the vehicle is travelling at extreme reentry speeds. These pressures are not so low however to prevent air from entering the vehicle. The impacts of this now apparent soak back, during the last phases of an atmospheric reentry were investigated leading to the conclusion that analyses of lower atmospheric portions of a reentry are critical to reentry studies and significantly changed the results.
An updated design is theorized using the knowledge gained from the preliminary studies called the Cryogenic Extended Duration and Reentry Thermal Control System (CEDR TCS) and the design is fully passive making it a low-complexity, zero-power system that does not necessitate the use of any consumables. The CEDR TCS uses a two-way pressure relief valve or “breather valve” that would allow the pressures inside and outside the vehicle to equilibrate once a great enough pressure differential is applied. This will allow air to leave while the unit is in space vacuum and prevent air from coming in until much later in the re-entry after much of the reentry heat has had a chance to convect to the upper atmosphere. Through further analysis CEDR is hoped to display a capability of near cryogenic temperatures through an atmospheric reentry and long durations on the ground.
Publication: TFAWS2011-AE-005.pdf
Source: TFAWS
Author: Erika T. Bannon, Jared Leidich, Alex Walker
Year: 2011
Content Tags: mli, multi-layer insulation, heat loads, design optimization, CFD, transient, insulation, model correlation, phase change material, PCM, radiation, sink temperature, heat flux, radks, radiation analysis group, material properties
Thermal Modeling of Nanosat
Advances in computer technologies and manufacturing processes allow creation of highly sophisticated components in compact platform. For example, a small scale satellite, such as the CubeSat, can now be used for scientific research in space rather than big scale project like the International Space Station (ISS). Recently a team of undergraduate and graduate students at SJSU has the opportunity to collaborate on designing and building a miniature size CubeSat with the dimension of 10x10x10 cm. Although the integration of compact electronics allows sophisticated scientific experiments and missions to be carried out in space, the thermal control options for such small spacecraft are limited. For example, because of its small size there is no room for dedicated radiator or insulation panels. To minimize mass of the thermal control system while keeping the electronics at safe operating conditions, this thesis aims at studying the external orbital radiation heat flux the CubeSat is expected to expose to and the steady state heat conduction of the internal electronics. If the operating temperature from these heating conditions causes issue, appropriate thermal control solutions will be presented.
Publication: Dihn.S12.pdf
Source: San José State University
Author: Dai Q. Dinh
Year: 2012
Content Tags: heat flux, orbital heating, steady state, conduction, wall, boundary condition, third-party software, radiation, albedo, material properties, optical properties, parametric
Thermo-electrochemical analysis of lithium ion batteries for space applications using Thermal Desktop
Lithium-ion batteries (LIBs) are replacing the Nickel–Hydrogen batteries used on the International Space Station (ISS). Knowing that LIB efficiency and survivability are greatly influenced by temperature, this study focuses on the thermo-electrochemical analysis of LIBs in space orbit. Current finite element modeling software allows for advanced simulation of the thermo-electrochemical processes; however the heat transfer simulation capabilities of said software suites do not allow for the extreme complexities of orbital-space environments like those experienced by the ISS. In this study, we have coupled the existing thermo-electrochemical models representing heat generation in LIBs during discharge cycles with specialized orbital-thermal software, Thermal Desktop (TD). Our model's parameters were obtained from a previous thermo-electrochemical model of a 185 Amp-Hour (Ah) LIB with 1–3 C (C) discharge cycles for both forced and natural convection environments at 300 K. Our TD model successfully simulates the temperature vs. depth-of-discharge (DOD) profiles and temperature ranges for all discharge and convection variations with minimal deviation through the programming of FORTRAN logic representing each variable as a function of relationship to DOD. Multiple parametrics were considered in a second and third set of cases whose results display vital data in advancing our understanding of accurate thermal modeling of LIBs.
Publication: TD_Application.pdf
Source: Science Direct (Journal of Power Sources)
Author: W. Walker, H. Ardebili
Year: 2014
Content Tags: batteries, orbital heating, orbit, finite element, parametric, thermoelectric, convection heat transfer, variable, user-defined Fortran array, user-defined Fortran arrays (UDFAs)
Optimization and Automated Data Correlation in the NASA Standard Thermal/Fluid System Analyzer
SINDA/FLUINT (Ref 1-7) is the NASA-standard heat transfer and fluid flow analyzer for thermal control systems. Because of its general formulation, it is also used in other aerospace specialties such as environmental control (ECLSS) and liquid propulsion, and in terrestrial industries such as electronics packaging, refrigeration, power generation, and transportation industries.
SINDA/FLUINT is used to design and simulate thermal/fluid systems that can be represented in networks corresponding to finite difference, finite element, and/or lumped parameter equations. In addition to conduction, convection, and radiation heat transfer, the program can model steady or unsteady single- and two-phase flow networks.
C&R’s SinapsPlus® is a complete graphical user interface (preand postprocessor) and interactive model debugging environment for SINDA/FLUINT (Ref 8, 9). SinapsPlus also supports the C language in addition to the traditional choice of Fortran for concurrently executed user logic.
This paper describes revolutionary advances in SINDA/FLUINT, the NASA-standard heat transfer and fluid flow analyzer, changing it from a traditional point-design simulator into a tool that can help shape preliminary designs, rapidly perform parametrics and sensitivity studies, and even correlate modeling uncertainties using available test data.
Innovations include the incorporation of a complete spreadsheet-like module that allows users to centralize and automate model changes, even while thermal/fluid solutions are in progress. This feature reduces training time by eliminating many archaic options, and encourages the performance of parametrics and other what-if analyses that help engineers develop an intuitive understanding of their designs and how they are modeled.
The more revolutionary enhancement, though, is the complete integration of a nonlinear programming module that enables users to perform formal design optimization tasks such as weight minimization or performance maximization. The user can select any number of design variables and may apply any number of arbitrarily complex constraints to the optimization. This capability also can be used to find the best fit to available test data, automating a laborious but important task: the correlation of modeling uncertainties such as optical properties, contact conductances, as-built insulation performance, natural convection coefficients, etc.
Finally, this paper presents an overview of related developments that, coupled with the optimization capabilities, further enhance the power of the whole package.
Publication: sfpaper.pdf
Source: IECEC
Author: Brent A. Cullimore
Year: 1998
Content Tags: design optimization, model correlation, parameterize, parametric, two-phase flow, two-phase, optical properties, submodels, registers, expression editor, user logic, concurrent engineering, concurrent design, dynamic mode, dynamic SINDA, specific heat, solver, constraint, slip flow, Phenomena, capillary systems, mixtures, working fluids, nonequilibrium, vapor compression, uncertainty, uncertainty analysis
Optimization, Data Correlation, and Parametric Analysis Features in SINDA/FLUINT Version 4.0
This paper describes revolutionary advances in SINDA/FLUINT, the NASA-standard heat transfer and fluid flow analyzer, changing it from a traditional point-design simulator into a tool that can help shape preliminary designs, rapidly perform parametrics and sensitivity studies, and even correlate modeling uncertainties using available test data.
Innovations include the incorporation of a complete spreadsheet-like module that allows users to centralize and automate model changes, even while thermal/fluid solutions are in progress. This feature reduces training time by eliminating many archaic options, and encourages the performance of parametrics and other what-if analyses that help engineers develop an intuitive understanding of their designs and how they are modeled.
The more revolutionary enhancement, though, is the complete integration of a nonlinear programming module that enables users to perform formal design optimization tasks such as weight minimization or performance maximization. The user can select any number of design variables and may apply any number of arbitrarily complex constraints to the optimization. This capability also can be used to find the best fit to available test data, automating a laborious but important task: the correlation of modeling uncertainties such as optical properties, contact conductances, as-built insulation performance, natural convection coefficients, etc.
Finally, this paper presents an overview of related developments that, coupled with the optimization capabilities, further enhance the power of the whole package.
Publication: sf981574.pdf
Source: ICES 1998
Author: Brent A. Cullimore
Year: 1998
Content Tags: design optimization, model correlation, parameterize, parametric, two-phase flow, two-phase, optical properties, submodels, registers, expression editor, user logic, concurrent engineering, concurrent design, dynamic mode, dynamic SINDA, specific heat, solver, constraint, slip flow, Phenomena, capillary systems, mixtures, working fluids, nonequilibrium, vapor compression, uncertainty, uncertainty analysis
Optimization and Automated Data Correlation
Optimization and Automated Data Correlation in the NASA Standard Thermal/Fluid System Analyzer
SINDA/FLUINT (Ref 1-7) is the NASA-standard heat transfer and fluid flow analyzer for thermal control systems. Because of its general formulation, it is also used in other aerospace specialties such as environmental control (ECLSS) and liquid propulsion, and in terrestrial industries such as electronics packaging, refrigeration, power generation, and transportation industries. SINDA/FLUINT is used to design and simulate thermal/fluid systems that can be represented in networks corresponding to finite difference, finite element, and/or lumped parameter equations. In addition to conduction, convection, and radiation heat transfer, the program can model steady or unsteady single- and two-phase flow networks. CRTech's SinapsPlus® is a complete graphical user interface (preand postprocessor) and interactive model debugging environment for SINDA/FLUINT (Ref 8, 9). SinapsPlus also supports the C language in addition to the traditional choice of Fortran for concurrently executed user logic. This paper describes revolutionary advances in SINDA/FLUINT, the NASA-standard heat transfer and fluid flow analyzer, changing it from a traditional point-design simulator into a tool that can help shape preliminary designs, rapidly perform parametrics and sensitivity studies, and even correlate modeling uncertainties using available test data. Innovations include the incorporation of a complete spreadsheet-like module that allows users to centralize and automate model changes, even while thermal/fluid solutions are in progress. This feature reduces training time by eliminating many archaic options, and encourages the performance of parametrics and other what-if analyses that help engineers develop an intuitive understanding of their designs and how they are modeled. The more revolutionary enhancement, though, is the complete integration of a nonlinear programming module that enables users to perform formal design optimization tasks such as weight minimization or performance maximization. The user can select any number of design variables and may apply any number of arbitrarily complex constraints to the optimization. This capability also can be used to find the best fit to available test data, automating a laborious but important task: the correlation of modeling uncertainties such as optical properties, contact conductances, as-built insulation performance, natural convection coefficients, etc. Finally, this paper presents an overview of related developments that, coupled with the optimization capabilities, further enhance the power of the whole package.
Publication: sfpaper.pdf
Source: IECEC 1998
Author: Brent A. Cullimore
Year: 1998
Content Tags:
Nonlinear Programming Applied to Calibrating Thermal and Fluid Models to Test Data (Semi-Therm 2002)
Nonlinear Programming Applied to Calibrating Thermal and Fluid Models to Test Data (Semi-Therm 2002)
Publication: calibrating.pdf
Source: Semi-Therm
Author: Jane Baumann, Brent Cullimore
Year: 2002
Content Tags: model calibration, model correlation, condenser, condensers, validation, design optimization, parametric
Customizable Multidiscipline Environments for Heat Transfer and Fluid Flow Modeling
Thankfully, the age of stand-alone fixed-input simulation tools is fading away in favor of more flexible and integrated solutions. “Concurrent engineering” once meant automating data translations between monolithic codes, but sophisticated users have demanded more native integration and more automated tools for designing, and not just evaluating point designs. Improvements in both interprocess communications technology and numerical solutions have gone a long way towards meeting those demands.
This paper describes a small slice of a larger on-going effort to satisfy current and future demands for integrated multidisciplinary tools that can be highly customized by end-users or by third parties. Specifically, the ability to integrate fully featured thermal/fluid simulations into Microsoft’s Excel™ and other software is detailed. Users are now able not only to prepare custom user interfaces, they can use these codes as portals that allow integration activities at a larger scale. Previous enabling technologies are first described, then examples and repercussions of current capabilities are presented, and finally in-progress and future technologies are listed.
Publication: COMAPI-ICES.pdf
Source: ICES
Author: B. Cullimore, S. G. Ring, J. Baumann
Year: 2004
Content Tags: parametric, parameterize, dynamic mode, dynamic SINDA, third-party software
A Methodology for Enveloping Reliable Start-up of LHPs
The loop heat pipe (LHP) is known to have a lower limit on input power. Below this limit the system may not start properly creating the potential for critical payload components to overheat. The LHP becomes especially susceptible to these low power start-up failures following diode operation, intentional shut-down of the device, or very cold conditions. These limits are affected by the presence of adverse tilt, mass on the evaporator, and noncondensible gas in the working fluid. Based on analytical modeling correlated to startup test data, this paper will describe the key parameters driving this low power limit and provide an overview of the methodology for predicting a “safe start” design envelope for a given system and loop design. The amount of incipient superheat was found to be key to the enveloping procedure. Superheat levels have been observed to vary significantly based on evaporator design and even from unit to unit of identical designs. Statistical studies of superheat levels and active measures for limiting superheat should be addressed by both the hardware vendors and the system integrators.
Publication: AIAA2000-2285.PDF
Source: AIAA Thermophysics
Author: Jane Baumann, Brent Cullimore, Jay Ambrose, Eva Buchan, Brois Yendler
Year: 2000
Content Tags: Loop Heat Pipe, LHP, noncondensable gas, start-up, evaporator, wicks, parametric, Phenomena, working fluid, model correlation, parameter, heat loads, compensation chamber, transient, capillary systems
Upper Stage Tank Thermodynamic Modeling Using SINDA/FLUINT
Modeling to predict the condition of cryogenic propellants in an upper stage of a launch vehicle is necessary for mission planning and successful execution. Traditionally, this effort was performed using custom, in-house proprietary codes, limiting accessibility and application. Phenomena responsible for influencing the thermodynamic state of the propellant have been characterized as distinct events whose sequence defines a mission. These events include thermal stratification, passive thermal control roll (rotation), slosh, and engine firing. This paper demonstrates the use of an off the shelf, commercially available, thermal/fluid-network code to predict the thermodynamic state of propellant during the coast phase between engine firings, i.e. the first three of the above identified events. Results of this effort will also be presented.
Publication: AIAA-2006-50513.pdf
Source: AIAA
Author: P. Schallhorn, D. Michael Campbell, Sukhdeep Chase, Jorge Piquero, Cindy Fortenberry, Xiaoyi Li, Lisa Grob
Year: 2006
Content Tags: Optimization, parametric, radiation, radiation analysis groups, conduction, evaporation, CFD, convergence, structural, heat flux, thermal stratification, register, two-phase, slosh, wall, splash
Upper Stage Tank Thermodynamic Modeling Using SINDA/FLUINT (Presentation)
Publication: TFAWS-08-1009_presentation.pdf
Source: TFAWS Short Course
Author: Paul Schallhorn, D. Michael Campbell, Sukhdeep Chase, Jorge Piquero, Cindy Fortenberry, Xiaoyi Li, Lisa Grob
Year: 2008
Content Tags: CFD, two-phase, slosh, thermal stratification, diffusion, boundary layer, twinned tanks, boiling
Integrating Thermal And Structural Analysis with Thermal Desktop
Structural and thermal engineers currently work independently of each other using unrelated tools, models, and methods. Without the ability to rapidly exchange design data and predicted performance, the achievement of the ideals of concurrent engineering is not possible.
Thermal codes have been unable to exploit the geometric information in structural models and the CAD design database, and do not facilitate transfer of temperature data to other discipline’s analysis models. This paper discusses the key features in Thermal Desktop for supporting integrated thermal/structural analysis. Approaches to thermal modeling in an integrated analysis environment are discussed along with Thermal Desktop's data mapping algorithm for exporting temperature data on to structural model grid points.
Publication: 99es-40.pdf
Source: ICES
Author: Tim Panczak, Mark J. Welch
Year: 1999
Content Tags: structural, finite elements, finite difference, structural mesh, temperature mapping, temperature map, concurrent engineering, concurrent design, radiation calculations, CAD geometry, postprocessing, orbit, orbital heating, radiation analysis groups, Monte Carlo, ray tracing, data mapper, solver
Automating Thermal Analysis with Thermal Desktop
Thermal analysis is typically executed with multiple tools in a series of separate steps for performing radiation analysis, generating conduction and capacitance data, and for solving temperatures. This multitude of programs often leads to many user files that become unmanageable with their multitude, and the user often looses track as to which files go with which cases. In addition to combining the output from multiple programs, current processes often involve the user inputting various hand calculations into the math model to account for MLI/Insulation and contact conductance between entities. These calculations are not only tedious to make, but users often forget to update them when the geometry is changed.
Several new features of Thermal Desktop are designed to automate some of the tedious tasks that thermal engineers now practice. To start with, Thermal Desktop is a single program that does radiation analysis, generates conduction/capacitance data and automates the building of a SINDA/FLUINT model to solve for temperatures. Some of these new features of Thermal Desktop are Radiation Analysis Groups, Property Aliases, MLI/Insulation Objects, Contact Conductance Objects, Model Browser, and the Case Set Manager.
This paper describes the application and benefits of Thermal Desktop along with other unique features used to automate the thermal analysis process.
Publication: tDesktop99.pdf
Source: ICES
Author: Mark J. Welch, Tim Panczak
Year: 1999
Content Tags: radiation analysis groups, property, alias, multi-layer insulation, mli, insulation, contact conductance, model browser, case set manager
Parametric Thermal Analysis and Optimization Using Thermal Desktop
Thermal analysis is typically performed using a point design approach, where a single model is analyzed one analysis case at a time. Changes to the system design are analyzed by updating the thermal radiation and conduction models by hand, which can become a bottleneck when attempting to adopt a concurrent engineering approach. This paper presents the parametric modeling features that have been added to Thermal DesktopTM to support concurrent engineering. The thermal model may now be characterized by a set of design variables that are easily modified to reflect system level design changes. Geometric features, optical and material properties, and orbital elements may all be specified using user-defined variables and expressions. Furthermore, these variables may be automatically modified by Thermal Desktop’s optimization capabilities in order to satisfy user-defined design goals, or for correlating thermal models to test data. By sharing the set of design variables among analysis models spanning multiple disciplines, further integrated analysis and design may be accomplished. The framework into which Thermal Desktop is embedded in order to support an integrated Thermal/Structural/Optical design, analysis, and optimization system is also presented.
Publication: 00ICES-266.pdf
Source: ICES
Author: Timothy D. Panczak, Brent A. Cullimore
Year: 2000
Content Tags: concurrent engineering, parametric, parameterize, register, registers, dynamic mode, dynamic SINDA, symbol manager, expression editor, expressions, design optimization, orbital heating, model correlation, solver, optical properties, heat pipes, symbol, variables, case set manager, properties, structural