Session
Technical Session X: Mission Enabling Technologies II
Abstract
Realization of Responsive Space (RS) program goals requires further progress in reducing the time required for spacecraft system design, analysis, fabrication, assembly, integration, testing, and deployment. Of particular need is an enabling technology that will reduce the design and integration-test time of the thermal subsystem. One such technology is the Thermal Control Panel (TCP) being developed by Thermal Management Technologies under SBIR contract to AFRL Space Vehicles Directorate (AFRL/RV). This technology provides isothermal structural panels and low thermal impedance joints for use in an isothermal spacecraft structure. Each light weight panel provides the spacecraft structure while simultaneously exhibiting an effective thermal conductivity/mass ratio much greater than traditional spacecraft materials. In various forms the TCP can be used to spread heat, create nearly isothermal spacecraft structures, and to provide highly efficient space radiators. The technology is applicable to spacecraft structures at all levels of size and complexity. The panels have an operating temperature range of -30 to +65 C. The technology development is on track to complete space qualification testing in early 2012.
Presentation Slides
Isothermal Structural Panels for Spacecraft Thermal Management
Realization of Responsive Space (RS) program goals requires further progress in reducing the time required for spacecraft system design, analysis, fabrication, assembly, integration, testing, and deployment. Of particular need is an enabling technology that will reduce the design and integration-test time of the thermal subsystem. One such technology is the Thermal Control Panel (TCP) being developed by Thermal Management Technologies under SBIR contract to AFRL Space Vehicles Directorate (AFRL/RV). This technology provides isothermal structural panels and low thermal impedance joints for use in an isothermal spacecraft structure. Each light weight panel provides the spacecraft structure while simultaneously exhibiting an effective thermal conductivity/mass ratio much greater than traditional spacecraft materials. In various forms the TCP can be used to spread heat, create nearly isothermal spacecraft structures, and to provide highly efficient space radiators. The technology is applicable to spacecraft structures at all levels of size and complexity. The panels have an operating temperature range of -30 to +65 C. The technology development is on track to complete space qualification testing in early 2012.
