Session
Technical Session I: The Future- Military Missions Under Development Or Proposed That Provide Measurable Utility To The Warfighter
Abstract
The Air Force Research Laboratory (AFRL) Space Vehicles Directorate has developed the Deployable Structures Experiment (DSX) to research technologies needed for large space structures and apertures, high-power generation, and survivability in the high radiation environment of a medium earth orbit (MEO). DSX is designed to perform five basic research experiments that coupled together provides DoD with the technological understanding needed to achieve transformational capability in space surveillance, microsats with large aperture and power, active space capability protection from enhanced radiation belts, and radiation-survivability design criteria for satellite systems planned for the highly desirable medium Earth orbit (MEO) regime. The five DSX experiments are fundamental research on large deployable space structures, on-orbit dynamics identification and adaptive control of large deployable structures, very low frequency (VLF) wave physics in the magnetosphere, thin-film photovoltaics (TF-PV), and space radiation measurement in the MEO environment. DSX is baselined to launch in 2008 to a 6000-km x 12000-km, 27 degree inclination MEO orbit for at least one year of mission operations. DSX will serve as a path-finder for future DoD rapid response missions, by developing and demonstrating both technologies and processes that enable low-cost and rapid integration of one-of a-kind R&D satellites and operational systems. DSX addresses the rapid integration problem through the use of an innovative network based infrastructure, the Planning System Incorporated (PSI) Network Data Acquisition System (NDAS), for implementation of Bus and Payload box connectivity, as well as distributed remote sensor payloads on large deployable structures. To address the space access aspect of the rapid−response problem, DSX will utilize an EELV Secondary Payload Adapter (ESPA) capability as a platform for highly−capable small and medium free−flying satellites (or ESPASats) that have plentiful and relatively inexpensive launch opportunities on EELV as secondary payloads. An overview of the DSX spacecraft design will be presented, and its host subsystems, payload designs and experiments will be described. The unique electrical and software interface accommodation of the payload support electronics and Network Data Acquisition System (NDAS) as well as the highly modular mechanical integration approach of a free-flyer dedicated ESPA-sat will be described in the context of their enabling features for both DSX and future responsive DoD missions.
Presentation Slides
The Deployable Structures Experiment: Design of a Low-Cost, Responsive R&D Space Mission
The Air Force Research Laboratory (AFRL) Space Vehicles Directorate has developed the Deployable Structures Experiment (DSX) to research technologies needed for large space structures and apertures, high-power generation, and survivability in the high radiation environment of a medium earth orbit (MEO). DSX is designed to perform five basic research experiments that coupled together provides DoD with the technological understanding needed to achieve transformational capability in space surveillance, microsats with large aperture and power, active space capability protection from enhanced radiation belts, and radiation-survivability design criteria for satellite systems planned for the highly desirable medium Earth orbit (MEO) regime. The five DSX experiments are fundamental research on large deployable space structures, on-orbit dynamics identification and adaptive control of large deployable structures, very low frequency (VLF) wave physics in the magnetosphere, thin-film photovoltaics (TF-PV), and space radiation measurement in the MEO environment. DSX is baselined to launch in 2008 to a 6000-km x 12000-km, 27 degree inclination MEO orbit for at least one year of mission operations. DSX will serve as a path-finder for future DoD rapid response missions, by developing and demonstrating both technologies and processes that enable low-cost and rapid integration of one-of a-kind R&D satellites and operational systems. DSX addresses the rapid integration problem through the use of an innovative network based infrastructure, the Planning System Incorporated (PSI) Network Data Acquisition System (NDAS), for implementation of Bus and Payload box connectivity, as well as distributed remote sensor payloads on large deployable structures. To address the space access aspect of the rapid−response problem, DSX will utilize an EELV Secondary Payload Adapter (ESPA) capability as a platform for highly−capable small and medium free−flying satellites (or ESPASats) that have plentiful and relatively inexpensive launch opportunities on EELV as secondary payloads. An overview of the DSX spacecraft design will be presented, and its host subsystems, payload designs and experiments will be described. The unique electrical and software interface accommodation of the payload support electronics and Network Data Acquisition System (NDAS) as well as the highly modular mechanical integration approach of a free-flyer dedicated ESPA-sat will be described in the context of their enabling features for both DSX and future responsive DoD missions.
