A System-Level Spacecraft Thermal Model Reduction Method Applicable to Transient Analysis

dc.creatorShibukawa, Toshihiro
dc.creatorNakasuka, Shinichi
dc.date.accessioned2023-06-16T13:09:26Z
dc.date.available2023-06-16T13:09:26Z
dc.date.issued2023-07-16
dc.descriptionToshihiro Shibukawa, ArkEdge Space Inc., Japan
dc.descriptionShinichi Nakasuka, ArkEdge Space Inc., Japan
dc.descriptionICES207: Thermal and Environmental Control Engineering Analysis and Software
dc.descriptionThe 52nd International Conference on Environmental Systems was held in Calgary, Canada, on 16 July 2023 through 20 July 2023.
dc.description.abstractIn spacecraft thermal design, Thermal Mathematical Models (TMMs) play an essential role to evaluate thermal performance in-orbit. However, typical detailed TMMs have a high calculation cost, while many iterations running these TMMs are required in thermal design processes, such as uncertainty analysis, feedback from hardware design, and model correlation using thermal vacuum test data and in-orbit data. Therefore, shortening analysis time for TMMs is essential to reduce time and cost required for thermal design. Creating reduced models is one approach to deal with this problem. Generally, there are two approaches in creating reduced models: model-based and data-driven. Past studies on spacecraft thermal design reduction methods mainly focus on either component-level, model-based reduction or system-level, data-driven reduction. This study presents a model-based reduction method that is applicable to system-level thermal models, based on connected component decomposition algorithms. To make decision of which nodes to be fused in an automatic process, analysis results from the original model, under typical case sets, are used. By this approach, the reduced model preserves physical properties, allowing it to be used in both static and transient cases, and realize application to hardware design, thermal vacuum test correlation, and software-in-the-loop simulations for operation testing and planning. For evaluation of this reduction process, the actual thermal model used for ONGLAISAT, a 6U CubeSat developed by the University of Tokyo, was utilized. Even for CubeSat level models with only less than 1,000 nodes, this reduction process showed a reduction rate of around 0.6 to 0.7, shortening analysis time, while displaying a maximum of just several degrees celsius in temperature difference between the original model and the reduced model. This displayed that an effective system-level reduced model can be created using this method.
dc.format.mimetypeapplication/pdf
dc.identifier.otherICES-2023-162
dc.identifier.urihttps://hdl.handle.net/2346/94618
dc.language.isoeng
dc.publisher2023 International Conference on Environmental Systems
dc.subjectSpacecraft Thermal Design
dc.subjectThermal Modeling
dc.subjectModel Reduction
dc.titleA System-Level Spacecraft Thermal Model Reduction Method Applicable to Transient Analysisen_US
dc.typePresentations

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