Thermal Desktop

CRTech Thermal Desktop

Complete CAD-based Thermal Engineering Tool Suite

C&R Thermal Desktop® enables thermal engineers to create models that range from small components to complete systems. It is general-purpose, which means it is suitable for everything from commercial submarine components to planetary exploration systems. Finite difference and finite element objects are combined with environment definitions in AutoCAD’s 3D design environment. Thermal Desktop creates the node and conduction network, launches SINDA/FLUINT for the solution, and provides post-processing results. Thermal Desktop clearly shows our dedication to giving users the very best in thermal and fluids analysis. It allows you to handle the engineering judgment while it takes care of the grunt work.

Product Information

Thermo-electrochemical analysis of lithium ion batteries for space applications using Thermal Desktop, W. Walker, H. Ardebili (2014)

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Thermal Modeling of Nanosat, Dai Q. Dinh (2012)

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Improvements to a Response Surface Thermal Model for Orion, Stephen W. Miller – NASA JSC William Q. Walker – West Texas A&M(2011)

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FASTSAT-HSV01 Thermal Math Model Correlation, Callie McKelvey, NASA Marshall Space Flight Center(2011)

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Adaptive Thermal Modeling Architecture for Small Satellite Applications, 2Lt. John Anger Richmond, USAF, Colonel John Keesee, USAF Retired (2010)

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Collaborative design and analysis of Electro-Optical sensors, Jason Geis, Jeff Lang, Leslie Peterson, Francisco Roybal, David Thomas(2009)

Crew Exploration Vehicle Composite Pressure Vessel Thermal Assessment, Laurie Y. Carrillo, Ángel R. Álvarez-Hernández, Steven L. Rickman - NASA Johnson Space Center(TFAWS 2008)

Associated paper can be download here

Ground Plane and Near-Surface Thermal Analysis for NASA’s Constellation Programs, Joseph F. Gasbarre, Ruth M. Amundsen, Salvatore Scola - NASA Langley Research Center, Frank B. Leahy and John R. Sharp - NASA Marshall Space Flight Center (TFAWS 2008)

Thermal Model Development for Ares I-X, Ruth M. Amundsen, Joe Del Corso - NASA Langley Research Center (TFAWS 2008)

ATROMOS Mars Polar Lander Thermal Model, Elsie Hartman, Hingloi Leung, Freddy Ngo, Syed Shah, Nelson Fernandez, Kenny Boronowsky, Ramon Martinez, Nick Pham, Ed Iskander, Marcus Murbach, Erin Tegnerud, Dr. Periklis Papadopoulos (TFAWS 2008)

Free Molecular Heat Transfer Programs for Setup and Dynamic Updating the Conductors in Thermal Desktop, Eric T. Malroy, Johnson Space Center (TFAWS 2007)

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Thermal Analysis on Plume Heating of the Main Engine on the Crew Exploration Vehicle Service Module, Xiao-Yen J. Wang and James R.Yuko, NASA Glenn Research Center (TFAWS 2007)

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Implementation of STEP-TAS Thermal
Model Exchange Standard in Thermal
Desktop, Tim Panczak and Georg Siebes (TFAWS 2007)

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Modeling Transient Operation of Loop Heat Pipes using Thermal Desktop, Dmitry Khrustalev, ATK Space(TFAWS 2007)

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WPI Nanosat-3 Final Report, PANSAT - Powder Metallurgy and Navigation Satellite, , Fred J Looft, Electrical and Computer Engineering, Worcester Polytechnic Institute (2006)

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Modeling and Sizing a Thermoelectric Cooler within a Thermal Analyzer, J. Baumann (Aerospace Thermal Control Workshop 2006)

Non-grey Radiation Modeling using Thermal Desktop/SINDAWORKS, Dr. Kevin R. Anderson, Dr. Chris Paine, Jet Propulsion Laboratory(TFAWS 2006)

Analysis and Design of the Mechanical Systems Onboard a Microsatellite in Low-Earth Orbit: an Assessment Study, Dylan Raymond Solomon (2005)

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Thermo-elastic wavefront and polarization error analysis of a telecommunication optical circulator, K. Doyle and B. Bell (2005)

Emittance & Absorptance for Cryo Testing, D. Green (2005)

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JWST Testing Issues – Thermal & Structural (William Bell, Frank Kudirka, & Paul-W. Young, Aerospace Thermal Control Workshop 2005)

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Thermoelastic Analysis in Design (William Bell & Paul-W. Young, Aerospace Thermal Control Workshop 2005)

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Parametric Models and Optimization for Rapid Thermal Design, D. Martin (2004)

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Margin Determination in the Design and Development of a
Thermal Control System (D. Thunnissen and G. Tsuyuki, ICES 2004)

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Automated Multidisciplinary Optimization of a Space-based Telescope (ICES 2002)

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Integrated Analysis of Thermal/Structural/
Optical Systems (ICES 2002)

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A CAD-based Tool for FDM and FEM Radiation and Conduction Modeling

Thermal engineering has long been left out of the concurrent engineering environment dominated by CAD (computer aided design) and FEM (finite element method) software.  Current tools attempt to force the thermal design process into an environment primarily created to support structural analysis, which results in inappropriate thermal models. As a result, many thermal engineers either build models “by hand” or use geometric user interfaces that are separate from and have little useful connection, if any, to CAD and FEM systems.

This paper describes the development of a new thermal design environment called the Thermal Desktop. This system, while fully integrated into a neutral, low-cost CAD system, and which utilizes both FEM and FD methods, does not compromise the needs of the thermal engineer. Rather, the features needed for concurrent thermal analysis are specifically addressed by combining traditional parametric surface-based radiation and FD based conduction modeling with CAD and FEM methods. The use of flexible and familiar temperature solvers such as SINDA/FLUINT is retained.

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Source: 
ASME Conference 1997
Author: 
Tim Pancak, Steve Ring, Mark Welch

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

Source: 
TFAWS 2018
Author: 
Stefano Cappucci, Michael T. Pauken, Jacob A. Moulton, Derek W. Hengeveld