Channel - Thermal Control and Protection
Thermal control and protection aims to maintain vehicle and component temperatures within acceptable limits. Thermal control is a broad discipline including internal and external systems, component and integrated thermal model development and analysis and correlation, attitude timeline analysis, and purge, vent, and drain analysis for vehicle cavities and compartments, thermal-vacuum testing. Thermal protection focuses on reusable high temperature thermal protection insulations such as tiles and high temperature blankets, the thermal aspects of hot structure, seals and barriers, ablative materials, thermo-mechanical analysis for induced stress, and arc jet and radiant heat testing.
1/29/2025 5:11:18 PM
Channel Videos
Aerotherm Chemical Equilibrium (Ace) and Charring Material Thermal Response and Ablation Programs (Cma) Tutorial
Discipline: Thermal Control & Protection
Abstract:
The main thermal design considerations in a solid rocket motor (SRM) nozzle are erosion and char of the insulation liner and the bondline temperature between the liner and overwrap. The bondline between the liner and overwrap usually has a temperature limit it must not exceed by end of burn (EOB). The ACE/CMA code calculates the thermal erosion and char of the carbon phenolic in the nozzle exit cone at each station and the heat conduction into the aft exit cone which provides bondline temperatures used for requirement validation. The ACE/CMA model results can be validated by data obtained from a static motor test. With the validated model, bondline temperature predictions can be made using 3σ erosion and char.
This presentation will illustrate the various steps involved in creating this analysis. Included will be a description of the various codes, inputs required and how the various outputs from codes are used as inputs for other codes to arrive at a solution. The process used to match data and validate the model will be discussed. The results will demonstrate what looked like an issue, the bondline exceeding the required temperature, is not because the predicted bondline temperature transient shows the exceedance occurs significantly after EOB.
About the Presenter:
Mr. O’Malley received his B.S. in Chemical engineering from Arizona State University in 1979 and his M.S. in Mechanical engineering from University of Iowa in 1985. He was employed by Thiokol Corporation at Promontory, Utah for 13 years in the thermal group specializing in SRM motor joint flow/thermal analysis and nozzle ablation analysis. Significant experience was gained while involved in the redesigned solid rocket motor effort after the Challenger accident. Presently employed by NASA, supporting the LSP program for the last 20 years. LSP specializes in integration of spacecraft to launch vehicles, qualification of spacecraft components and entire launch vehicles, thermal analysis, anomaly resolution and launch console support. Supported from its inception, the qualification effort for the GEM63 and GEM63XL SRM program for the Atlas V and Vulcan programs.
Michael O'Malley
9/8/2023 6:00:00 PM
Arc Jet Testing Overview
Discipline: Passive Thermal
Walt Bruce
1/11/2016 5:00:00 PM
Assessing Risk for Tailoring Cycles in Vehicle Thermal Vacuum Test
About the speaker:
John Welch is a Principal Engineer at The Aerospace Corporation in El Segundo, CA. His expertise includes thermal testing and spacecraft thermal design development. He is the author of thermal testing requirements in SMC-S-016 and MIL-STD-1540, and is the author of the Thermal Testing chapter in the Spacecraft Thermal Control Handbook and the Satellite Thermal Control Handbook. He received his bachelor’s and master’s degree in mechanical engineering from the University of Washington in Seattle.
John W Welch
9/29/2023 8:26:00 PM
Bottle Blow-Down Analysis
Discipline: Passive Thermal
Keywords:
thermodynamics
vessel
blow-down
gas
flow
isentropic
isothermal
bottle
Richard Wear
3/26/2013 5:26:00 PM
Building Your First SINDA Model
In this lesson, we’ll discuss thermal modeling using the Systems Improved Numerical Differencing Analyzer, or SINDA analysis software. This tool has existed in one form or another for more than 50 years and has undergone major improvements over time. Presently, different versions of SINDA are offered by a number of vendors. For this lesson, we are using a SINDA format offered by Cullimore and Ring Technologies, Incorporated. With minor modification, the models developed during this lesson can be adapted to other versions of SINDA. The use of this particular format during this lesson should not be construed as an endorsement of any product.
Steven L. Rickman
4/25/2019 12:33:00 PM
Building Your Third SINDA Model
This third lesson in the SINDA modeling series introduces viewers to the concept of a submodel, shows how SINDA model input and output may be customized, and demonstrates how multiple analysis cases may be performed within a single SINDA run. A sample model is developed to demonstrate these capabilities.
Steve Rickman
9/27/2022 12:45:00 PM
Combustion of Metal Powders for Power and Heat Generation in Space Missions
Abstract:
Power systems based on combustion reactions between solid or liquid reactants could provide heat and electric power in space missions where the use of sunlight and nuclear energy is impossible or impractical. Some combustible mixtures have very high energy densities compared to the best batteries. Recently, combustion of lithium with sulfur hexafluoride (SF6) and carbon dioxide has been studied for this application, but there are some problems with using these systems in space. Our approach is based on the use of lithium and magnesium powders as the fuel and chemically generated oxygen as the oxidizer. In situ CO2 could also be used as the oxidizer in missions to Mars and Venus. In this talk, we will present (1) a conceptual design of a power system for lunar night survival that uses Li or Mg powders and commercially available chemical oxygen generators, (2) kinetic studies on the oxidation of Li and Mg powders in O2 and CO2, and (3) experiments on the combustion of these powders with infiltrating O2 and CO2. This work was supported by an Early-Stage Innovations Grant from NASA’s Space Technology Research Grants Program (Grant No. 80NSSC20K0293) with Steven L. Rickman serving as a NASA Collaborator.
About the Speaker:
Dr. Evgeny Shafirovich is a Professor of Aerospace and Mechanical Engineering at the University of Texas at El Paso (UTEP). He received his PhD from the Russian Academy of Sciences in 1988. Prior to joining UTEP in 2008, he conducted research at the Russian Academy of Sciences, the French National Center for Scientific Research, the University of Notre Dame, and Purdue University. His research interests include combustion of metals, propellants, and gas-generating materials as well as combustion synthesis of advanced materials for clean energy and aerospace applications.
Dr. Evgeny Shafirovich
11/16/2023 7:00:00 PM
Common Thermal Modeling Mistakes, Part 2
Discipline: Passive Thermal
This presentation was recorded at the Thermal & Fluids Analysis Workshop (TFAWS) on August 3rd, 2016.
This course will cover the some of the common mistakes made in thermal modeling, and how to avoid them. Thermal Desktop will be used as a platform to demonstrate many of the common errors by both new analysts as well as experienced engineers in building a thermal model. Other non-software-associated errors will also be covered. Topics covered will include common errors in assumptions, materials, configurations, radiation, orbital analysis, and common faults in problem setup, analysis case runs and record-keeping. The course should help you as an engineer to watch for these common errors in the future, and help you avoid them.
Ruth Amundsen
10/6/2016 5:40:00 PM
Computational Fluid Dynamics (CFD) For Capsule Design
Dinesh Prabhu
5/4/2023 3:42:00 PM
Development of a Parabolic Reflector Radiator (PRR) for the LuSEE-Night Mission
Discipline: Thermal Control & Protection
Abstract:
This presentation will cover the work needed to supply 12 flight PRR reflectors to the LuSEE-Night mission on a NASA GCD project known as PALETTE PRR for LuSEE-Night. LuSEE-Night is a 2026 CLPS mission to a 20 degree S latitude lunar site, and after landing there on a Firefly Aerospace lander, its intent is to make 21 cm cosmology measurements using a monopole antenna system. In early June 2024, JPL delivered 12 flight PRR reflectors to LuSEE-Night and this presentation will cover the design, build, test, and delivery of those 12 flight PRR reflectors. LuSEE-Night needs a PRR to provide it with a low sink temperature so it can survive the high IR flux emanating from the 385 K surface temperatures expected at its low latitude landing site. LuSEE-Night utilizes a JPL-inspired thermal architecture to survive lunar night and it intends to operate at its landing site for 24 lunar day/night cycles (2 Earth years). LuSEE-Night is jointly funded by NASA SMD and the DoE Office of Science. The FY23-24 PALETTE PRR for LuSEE-Night project is funded by NASA STMD/GCD. This project is a follow-on to the highly successful PALETTE NASA STMD/GCD project, which spanned from FY20-FY23. David is the PI for the PALETTE PRR for LuSEE-Night project and was also the PI for PALETTE.
David Bugby
7/31/2024 6:00:00 PM
Dragonfly: Pushing The Boundary Of Spacecraft Thermal Design, Analysis, and Testing
Discipline: Thermal Control & Protection
Abstract:
Dragonfly, a NASA New Frontiers mission that will send a rotorcraft to fly through the dense, cryogenic Titan atmosphere, uses a novel TCS designed for a non-traditional convective environment to maintain internal temperatures. The lander uses internal fans to circulate Titan atmosphere, distribute heat from its MMRTG power source, and warm all internal components. It also leverages a unique external foam design to maintain comfortable internal temperatures in a cryogenic convective environment. To analyze the system, novel CFD methods were developed and used in conjunction with traditional Thermal Desktop analysis. To test the system, a custom built chamber known the TITAN chamber was constructed with the capability of simulating Titan-equivalent natural convection. This presentation dives into the many unique thermal design, analysis, and ground testing challenges for the Dragonfly mission.
About the Speaker(s):
Jane (Zhaojuan) He is currently the Dragonfly Lander Thermal Lead and Section Supervisor for the Spacecraft Thermal Engineering section at the Johns Hopkins Applied Physics Laboratory (APL). Prior to joining APL, she had over 20 years of experience in thermal design and analysis across nuclear energy, lithium-ion battery and electronics cooling industries. Jane holds three patents and multiple publications in various journals and conferences. She received her Master’s degree in Mechanical Engineering from Arizona State University and a Bachelor’s degree in Thermal Engineering from Tsinghua University.
Kurt Gonter received his B.S. in Aerospace Engineering from the University of Maryland, College Park in 2014, and his M.S. in Aeronautical Engineering from USC in 2021. He is currently the Assistant Section Supervisor for the Spacecraft Thermal Engineering section at JHU APL, and the Deputy Lander Thermal Lead for the Dragonfly mission. Prior to that, he spent 8 years at NASA JPL, where he worked on Mars and Lunar missions including Mars Science Laboratory, Mars 2020, Far-side Seismic Suite, and ISRU Pilot Excavator. His thermal engineering experience spans mission phases from project formulation through launch and prime mission operations.
Jane He
5/7/2025 6:00:00 PM
Engineering Materials and Metrology Tools for Thermal Management
Abstract:
As researchers develop new materials and systems, thermal transport is often key to performance, safety, and reliability. For instance, in battery cells, interfaces and low conductivity pathways can lead to high temperatures that can lead to thermal runaway. In portable and wearable electronics, limited heat dissipation pathways lead either to temperatures that require throttling device performance or that degrade the system. The Marconnet Thermal & Energy Conversion (MTEC) Lab focuses on (1) the design, development, and validation of novel experimental metrology tools for characterizing multi-functional properties of materials across length and temperature scales; (2) enhanced understanding and control of fundamental transport and energy conversion mechanisms through multi-scale computational modeling; and (3) strategic, physics-based design and development of materials with multi-functional capabilities.
This talk will describe several recent examples from my group of engineering materials to achieve targeted performance objectives, along with the development of new metrology tools for understanding thermal transport. We build from steady state to transient and high-powered heat dissipation systems for electronics cooling and other applications illustrating combined experimental and modeling approaches. These current and past projects provide a foundation for our new research directions related to thermal transport and energy storage.
Amy Marconnet
1/26/2023 7:30:00 PM
Form Factors, Grey Bodies and Radiation Conductances, Part 1
Discipline: Passive Thermal
Steve Rickman is the Technical Fellow for Passive Thermal discipline.
Keywords: Steve Rickman, Technical Fellow, Passive Thermal
Thermal Radiation
Stefan-Boltzmann Law
Form Factor
Grey Body
Interchange Factor
Radiation Conductance
Radk
Monte Carlo
Nusselt Sphere
Double Area Summation
Gebhart’s Method
Steven L. Rickman
12/13/2010 9:14:00 PM
Form Factors, Grey Bodies and Radiation Conductances, Part 2
Discipline: Passive Thermal
Steve Rickman is the Technical Fellow for Passive Thermal discipline.
Keywords: Steve Rickman, Technical Fellow, Passive Thermal
Thermal Radiation
Stefan-Boltzmann Law
Form Factor
Grey Body
Interchange Factor
Radiation Conductance
Radk
Monte Carlo
Nusselt Sphere
Double Area Summation
Gebhart’s Method
Steven L. Rickman
10/31/2012 8:14:00 PM
Form Factors, Grey Bodies and Radiation Conductances, Part 3
Discipline: Passive Thermal
Steve Rickman is the Technical Fellow for Passive Thermal discipline.
Keywords: Steve Rickman, Technical Fellow, Passive Thermal
Thermal Radiation
Stefan-Boltzmann Law
Form Factor
Grey Body
Interchange Factor
Radiation Conductance
Radk
Monte Carlo
Nusselt Sphere
Double Area Summation
Gebhart’s Method
Steven L. Rickman
10/31/2012 8:14:00 PM
Form Factors, Grey Bodies and Radiation Conductances, Part 4
Discipline: Passive Thermal
Steve Rickman is the Technical Fellow for Passive Thermal discipline.
Keywords: Steve Rickman, Technical Fellow, Passive Thermal
Thermal Radiation
Stefan-Boltzmann Law
Form Factor
Grey Body
Interchange Factor
Radiation Conductance
Radk
Monte Carlo
Nusselt Sphere
Double Area Summation
Gebhart’s Method
Steven L. Rickman
10/31/2012 8:14:00 PM
Heat Pipe/Thermal Technologies at Glenn Research Center
Discipline: Thermal Control & Protection
Abstract:
This presentation will cover thermal management technologies developed in the Thermal Energy Conversion (LET) Branch at GRC. These technologies were mainly developed for fission based power generation projects where the goal is to generate power for users such as lunar or Martian habitats, rovers, science payloads. This presentation will largely focus on the various uses of heat pipes, but it will also briefly cover some of the other thermal technologies that were developed at GRC.
About the Speaker(s):
Greeta Thaikattil earned her Bachelor of Science in Mechanical Engineering from the University of Dayton in 2016. She then received her Master of Science in Mechanical Engineering, with a focus in Thermal and Fluid Sciences, from Cleveland State University in 2020. She has supported NASA Glenn Research Center since 2017. Her initial roles supported both aerospace and space application projects where major efforts and skills included thermal/structural modeling, assembly modeling, drawings, fabrication, assembly and testing. Since 2019, Ms. Thaikattil has focused on thermal management where she has supported projects such as the Commercial Lunar Payload Services (CLPS) as a thermal engineer. She then joined the Thermal Energy Conversion (LET) branch at Glenn Research Center in 2021. Here, she has supported the Fission Surface Power project as the thermal engineer for the Heat Transport and Heat Rejection Subsystems for technology development and testing.
Mr. James Sanzi his B.S. and M.S. in Engineering from Millersville University and Indiana University of Pennsylvania respectively. He has amassed 45 years of experience in the manufacturing and testing of both low and high temperature heat pipes. Mr. Sanzi joined Glenn Research Center (GRC) in 2005 to support fission power projects. His early projects included thermal testing of long heat pipes for SP-100, solar thermal Stirling energy conversion, life testing a variety of heat pipes, and manufacturing of sintered powder metal wicks. At GRC, Mr. Sanzi has life tested Titanium- water heat pipes for 50,000 hours, thermal vacuum tested the Radiator Demonstration Unit (RDU), thermal vacuum tested the Technology Demonstration Unit (TDU) with a NaK pumped loop, tested Titanium- water heat pipes in zero gravity, manufactured sodium heat pipes for the Kilopower Reactor Using Stirling Technology (KRUSTY) experiment, and tested several radiators from relevant SBIR efforts. Mr. James Sanzi is Subject Matter Expert in heat pipes, high temperature alkali metals, interfacing thermal materials, and testing of thermal management technologies.
Greeta Thaikattil
2/5/2025 7:00:00 PM
Heat Pipes for Space Applications Part 1: Axially Grooved Heat Pipes
About the Speaker:
~ 20+ years of experience in the heat and mass transfer area
~ Ph.D. in Mechanical Engineering (Energy and Thermal Sciences)
~ In-depth knowledge of single-phase and two-phase thermal systems
~ Numerical and analytical modeling skills (STAR CCM+, SolidWorks Simulation, etc.)
~ Hands-on experience in all HP and LHP fabrication operations (except welding)
~ Familiarity with thermal management standards (space, military, etc.)
~ Performed creative work which has advanced state of the art in two phase heat transfer area
Dr. Sergey Semenov
10/31/2023 3:25:00 PM
Integrated Modeling
Dr. Alice Liu
8/23/2023 6:54:00 PM
Introduction to FilePlottingTools
Discipline: Thermal Control & Protection
Abstract:
Overview of the FilePlottingTools plugin for processing Thermal Desktop analysis results including a description of key features, detailed walkthrough of examples, and explanation of how to access the tool.
About the Speaker:
Kaitlin Liles has over 18 years of space flight hardware development and leadership experience at NASA Langley and has contributed to Agency-level project success during all mission phases including design, integration, testing, and operations. As the Thermal Discipline Lead for the Structural and Thermal Systems Branch (STSB) she is a center resource for thermal systems analysis, design, and testing and has been the Lead Thermal Engineer for the Mars Science Laboratory Entry Descent and Landing Instrumentation (MEDLI), Stratospheric Aerosol and Gas Experiment (SAGE) III on International Space Station (ISS), and Navigation Doppler Lidar (NDL) on Intuitive Machines (IM-1) projects. Kaitlin currently serves as the Chief Engineer for the Climate Absolute Radiance and Refractivity Observatory (CLARREO) Pathfinder and SAGE III on ISS projects and previously served as the Deputy Chief Engineer for the MEDLI2 project.
Kaitlin Liles
12/11/2024 7:00:00 PM
Introduction to Numerical Methods in Heat Transfer, Part 2
Discipline: Passive Thermal
Keywords:
Thermal Radiation
Numerical Methods
Heat Equation
Heat Transfer
Finite Difference
Euler-Lagrange Equation
Variational Formulation
Finite Element
Steven L. Rickman
7/2/2013 3:00:00 PM
Introduction to Numerical Methods in Heat Transfer, Part 3
Discipline: Passive Thermal
Keywords:
Thermal Radiation
Numerical Methods
Heat Equation
Heat Transfer
Finite Difference
Euler-Lagrange Equation
Variational Formulation
Finite Element
Steven L. Rickman
7/2/2013 2:04:00 PM
Introduction to Numerical Methods in Heat Transfer, Part 4
Discipline: Passive Thermal
Keywords:
Thermal Radiation
Numerical Methods
Heat Equation
Heat Transfer
Finite Difference
Euler-Lagrange Equation
Variational Formulation
Finite Element
Steven L. Rickman
7/2/2013 2:04:00 PM
Inverse Estimation of Mars 2020 Entry Aeroheating Environments Using MEDLI2 Flight Data
Hannah Alpert
5/16/2023 6:24:00 PM
JWST OTIS Cryogenic Vacuum Test, Part 1: Thermal Architecture
This series discusses the cryogenic vacuum testing of the James Webb Space Telescope’s Optical Telescope Element and Integrated Science Instrument Module, or OTIS. This test required multiple years of planning and was executed from July-October of 2017 at NASA’s Johnson Space Center in Houston. There are four parts to this series: Part I will introduce the major components of James Webb and specifically the thermal architecture of the OTIS cryogenic vacuum or CV test. Part II will encompass the extensive thermal analysis performed to prepare for the test. Part III will talk about the preparations for off-nominal events: what analysis was done, and how steps were taken pre-test to anticipate unexpected circumstances and mitigate their impacts to hardware and test timeline. Part IV is a recap of the lessons learned from the thermal test conductor perspective for both the payload team and the ground support equipment or GSE team.
Kan Yang
10/25/2019 6:36:00 PM
JWST OTIS Cryogenic Vacuum Test, Part 2: Thermal Analysis
In Part II, we will provide an overview of the OTIS CV test thermal model development. A description of some of the driving limits and constraints will be provided, as well as how these influenced our test planning and eventual execution. One significant aspect of our pre-test planning is the method by which we optimized the OTIS CV test cooldown and warmup profiles using the thermal model by incorporating a feedback loop for driving helium shroud temperature. We will spend some time introducing the logic for this feedback loop, which traded test time versus model safety to determine the most efficient way to cool and warm the payload. Finally, we will take a look at how our pre-test predictions compared with our actual performance in the OTIS CV test.
Kan Yang
7/6/2020 8:01:00 PM
JWST OTIS Cryogenic Vacuum Test, Part 3: Preparation for Off-Nominal Events
Welcome to the third lecture of the James Webb Space Telescope Optical Telescope Element and Integrated Science Instrument Model Cryogenic Vacuum Test lecture series. In this lecture, we will talk about preparation for off-nominal events. Before we begin, I’d like to acknowledge three co-contributors that were instrumental in the development of the content for this section: Stuart Glazer, who was the thermal lead for the OTIS CV test; Lee Feinberg, who is the Optical Telescope Element manager for the James Webb Space Telescope and played an integral role in the overall success of the OTIS test campaign; and Brian Comber, who was the lead thermal analyst for the ISIM CV tests, as well as the sole developer of the Fusion test monitoring software and the uncontrolled helium shroud warmup analysis methodology that will be discussed in this section
Kan Yang
3/11/2021 12:10:00 PM
JWST OTIS Cryogenic Vacuum Test, Part 4: Lessons Learned
Welcome to the fourth lecture of the James Webb Space Telescope Optical Telescope Element and Integrated Science Instrument Model Cryogenic Vacuum Test lecture series. In this lecture, we will talk about the lessons learned from the planning and execution of the OTIS CV test.
Kan Yang
3/11/2021 1:04:00 PM
Lunar Thermal Analysis Guidebook, Part 1
Carlos Gomez
5/4/2023 11:11:00 AM
Lunar Thermal Analysis Guidebook, Part 2
Carlos Gomez
5/4/2023 5:58:00 PM
Lunar Thermal Analysis Guidebook, Part 3
Carlos Gomez
5/4/2023 6:03:00 PM
Numerical Method to Calculate Spacecraft Environmental Heating From Celestial Bodies
This talk is about a numerical method to calculate the environmental heating of a spacecraft near a celestial body. This method was applied on MESSENGER, the first spacecraft to orbit Mercury, and helped to protect the spacecraft throughout its life and increase the amount of science data returned for the mission. The technique would be useful also for lunar missions, and for spacecraft that come in close proximity to comets and asteroids, and other scenarios besides those.
Allan Holtzman
7/19/2019 5:08:00 PM
Numerical Modeling of Cryogenic Fluid Management
Discipline: Passive Thermal
This lesson describes the basics of finite volume procedure in a fluid network and several applications of Cryogenic Fluid Management (CFM) using NASA’s Generalized Fluid System Simulation Program (GFSSP). GFSSP uses finite volume procedure to solve mass, momentum and energy conservation equations of fluid in conjunction with thermodynamic equation of state and energy conservation equation of solid. Four CFM applications considered in this lesson are: 1. Chilldown of a cryogenic transfer line, 2. No vent chill and fill of a cryogenic propellant tank, 3) Boil-off in a cryogenic propellant tank, 4) Self-pressurization of cryogenic propellant tank. Modeling of two phase flow, phase change and conjugate heat transfer are the highlights of these application problems.This lesson discusses recent progresses on numerical modeling of these applications and need for further research.
Dr. Alok Majumdar
6/8/2015 10:00:00 PM
Overview of Spacecraft Thermal Control, Part 2: Subsystem Design
About the speaker:
David G. Gilmore is a Senior Engineering Specialist in the Spacecraft Thermal Department at The Aerospace Corporation in El Segundo, California. Mr. Gilmore has acquired over 40 years of experience in the design, analysis, test, and flight operations of spacecraft thermal control systems. He has provided support to a wide range of scientific, commercial, and military spacecraft programs. In addition to his activities at The Aerospace Corporation, he is also the editor and a contributing author of the Spacecraft Thermal Control Handbook.
David Gilmore
12/8/2023 2:41:00 PM
Passive Cryogenic Fluid Management, Part 2
Matt Moran
5/2/2023 4:59:00 PM
Rapid Thermal Design, Modeling, and Analysis of Spaceflight Instruments, Part 2
This course provides a general overview of how to conduct rapid instrument thermal design, modeling, and analysis, as informed by the processes in NASA’s design labs.
Kan Yang
1/4/2023 5:21:00 PM
Rationale for Selected MIL-STD-1540E Thermal Test Requirements
Discipline: Passive Thermal
John W Welch
12/12/2012 4:49:00 PM
SHARE Heat Pipe Experiment Part I
Identify lessons learned related to the SHARE Heat Pipe Experiment. Analyze the testing issues and actions taken. Identify development, testing and analysis actions which could have resolved the issues more effectively.
Eugene Ungar
9/27/2023 2:11:00 PM
SHARE Heat Pipe Experiment Part II
Identify lessons learned related to the SHARE Heat Pipe Experiment. Analyze the testing issues and actions taken. Identify development, testing and analysis actions which could have resolved the issues more effectively.
Eugene Ungar
9/27/2023 6:19:00 PM
Thermal Hardware for Thermal Analysts
Discipline: Passive Thermal
David Steinfeld
8/4/2017 4:00:00 PM
Thermal Telemetry Data Processing Pipeline
Krithika Balakrishnan
9/27/2022 2:30:00 PM
Thermal Testing and Verification, Part 3 - Spacecraft Level Testing and Verification
Discipline: Passive Thermal
David Gilmore
12/20/2013 6:59:00 PM
Thermal Testing and Verification, Part 4 - Space Environment Simulation
Discipline: Passive Thermal
David Gilmore
12/19/2013 6:59:00 PM
Thermal Testing and Verification, Part 5 - Test Planning, Lessons Learned and Testing Checklist
Discipline: Passive Thermal
David Gilmore
12/19/2013 6:59:00 PM
Topology Optimization for Thermo-Mechanical Structures
Topology optimization is able to provide unintuitive and innovative design solutions and a performance improvement (e.g. weight savings): In excess of 50% is not uncommonly demonstrated in a range of engineering problems. With the advances in materials and additive manufacturing, topology optimization is attracting much attention in the recent years. This presentation will introduce some of the latest developments in topology optimization in the context of design problems that experience a wide temperature range during its operation. In addition to the conflicting nature of thermal and mechanical effects on a structure, the heat transfer characteristics themselves are a function of the design.
They present a unique set of challenges to the optimization algorithm and the topology optimization formulation can have a critical impact on the final design and the achievable performance. The seminar will review the latest developments in studying the optimal thermomechanical structures by multi-scale and large-scale topology optimization where novel and unintuitive designs are obtained from the largest design space.
Dr. H Alicia Kim
9/22/2022 6:00:00 PM
Two Phase Flows and Heat Transfer, Part 1
Discipline: Passive Thermal
Dr. Henry Nahra
12/7/2016 6:42:00 PM
Two Phase Flows and Heat Transfer, Part 2
Discipline: Passive Thermal
Dr. Henry Nahra
12/19/2016 6:42:00 PM
Understanding Radiative Thermometry, Part 1
Discipline: Passive Thermal
Tim Risch
2/29/2016 2:35:00 PM
Understanding Radiative Thermometry, Part 2
Discipline: Passive Thermal
Tim Risch
2/18/2016 3:15:00 PM
Wire and Wire Bundle Thermal Analysis
Steven L. Rickman
2/5/2018 7:25:00 PM
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