Session

Technical Session 8: Advanced Technologies II

Location

Utah State University, Logan, UT

Abstract

MultiFunctional Structures (MFS) represent a paradigm shift over conventional spacecraft design methods resulting in a considerable reduction in mass, volume, and cost. It involves the integration of multiple subsystems into the structure, thereby providing space for high-performance payload options having higher weight. Thermal management of MFS is catered to by incorporating a high thermal conductivity composite sandwich panel. This is achieved by using high-thermal conductivity (HiK) face sheets made of pitch-based carbon fibers, and HiK core made of additively manufactured Aluminum truss grid. The conduction through the panel is enhanced using a core fill that acts as a thermal link between the face sheets. The bottom face sheet behaves like a radiator and dissipates heat to space. This paper focuses on optimizing the thermal control subsystem to achieve the best thermal performance whilst minimizing mass. Optimization is achieved by varying the geometry of the core fill, changing the type of thermal link between face sheets, and exploring the thermo-optical properties of the bottom face sheet. The best designs showed a mass reduction of 30% (volume extraction from core fill) and 78.9% (replacing core fill with copper heat pipe embedded in aluminum plates) respectively, as compared to the conventional core fill. The solution was arrived at by using Hierarchical Evolutionary Engineering Design System (HEEDS) Multi-disciplinary Design Optimization (MDO) in conjunction with NX Modelling for CAD and NX Space System Thermal for space thermal analysis.

Available for download on Saturday, August 07, 2021

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Aug 11th, 11:00 AM

Optimization of TCS for MFS on SmallSat

Utah State University, Logan, UT

MultiFunctional Structures (MFS) represent a paradigm shift over conventional spacecraft design methods resulting in a considerable reduction in mass, volume, and cost. It involves the integration of multiple subsystems into the structure, thereby providing space for high-performance payload options having higher weight. Thermal management of MFS is catered to by incorporating a high thermal conductivity composite sandwich panel. This is achieved by using high-thermal conductivity (HiK) face sheets made of pitch-based carbon fibers, and HiK core made of additively manufactured Aluminum truss grid. The conduction through the panel is enhanced using a core fill that acts as a thermal link between the face sheets. The bottom face sheet behaves like a radiator and dissipates heat to space. This paper focuses on optimizing the thermal control subsystem to achieve the best thermal performance whilst minimizing mass. Optimization is achieved by varying the geometry of the core fill, changing the type of thermal link between face sheets, and exploring the thermo-optical properties of the bottom face sheet. The best designs showed a mass reduction of 30% (volume extraction from core fill) and 78.9% (replacing core fill with copper heat pipe embedded in aluminum plates) respectively, as compared to the conventional core fill. The solution was arrived at by using Hierarchical Evolutionary Engineering Design System (HEEDS) Multi-disciplinary Design Optimization (MDO) in conjunction with NX Modelling for CAD and NX Space System Thermal for space thermal analysis.