Session
Technical Session X: Delivery Systems
Abstract
Rapid advancements in nano-technology have led to numerous improvements in microsatellite design. In the past twenty years, this class of satellites (10-100 kg mass) has repeatedly demonstrated their worth as vehicles for space science, technology demonstration, communications, remote sensing, education and information transfer. Within the past decade, the dramatic transition from experimentation to significant applications has prompted the implementation of numerous new launch methodologies. However, none have adequately met all the requirements stipulated by the small satellite market. The STARSAT launch vehicle has been tailored to specifically address the needs of the micro-satellite mission at a fraction of the cost of conventional launch systems. In addition, the predefined orbital parameters of these historically secondary payloads are no longer adequate for these mature and significant satellite missions. The implementation of the STARSAT design will enable low earth orbital insertion at any inclination without a corresponding increase in consumer cost. STARSAT will permit a wide array of scientific organizations, engineering corporations, universities, and even individuals, economically realistic access to space. The STARSAT launch system utilizes high altitude space balloons coupled with an optimized propulsion platform to initiate a high performance LEO (Low Earth Orbit) transfer maneuver from a stratospheric altitude of 20 to 25 kilometers. Lack of drag, near earth gravity, and high atmospheric pressures coupled with a heavy focus on reducing overall payload mass enables STARSAT to achieve high orbital altitudes with minimal propulsion requirements. Phase 1 of the STARSAT design, fabrication and launch underway at the Kennedy Space Center in Florida is led by the development teams of STARHUNTER Corporation in conjunction with the National Aeronautics and Space Administration, The Florida Space Institute and the Central Florida Remote Sensing Labs. This conceptual report details the STARSAT orbital insertion profile, as well as subsystem design with a focus on propulsion and guidance techniques. Telemetry from the maiden launch of STARSAT will be discussed, in addition to future design goals. Overall, STARSAT has resulted in a cost effective mission profile for use throughout the small satellite industry.
New Launch Methodologies for the Micro-Millennia
Rapid advancements in nano-technology have led to numerous improvements in microsatellite design. In the past twenty years, this class of satellites (10-100 kg mass) has repeatedly demonstrated their worth as vehicles for space science, technology demonstration, communications, remote sensing, education and information transfer. Within the past decade, the dramatic transition from experimentation to significant applications has prompted the implementation of numerous new launch methodologies. However, none have adequately met all the requirements stipulated by the small satellite market. The STARSAT launch vehicle has been tailored to specifically address the needs of the micro-satellite mission at a fraction of the cost of conventional launch systems. In addition, the predefined orbital parameters of these historically secondary payloads are no longer adequate for these mature and significant satellite missions. The implementation of the STARSAT design will enable low earth orbital insertion at any inclination without a corresponding increase in consumer cost. STARSAT will permit a wide array of scientific organizations, engineering corporations, universities, and even individuals, economically realistic access to space. The STARSAT launch system utilizes high altitude space balloons coupled with an optimized propulsion platform to initiate a high performance LEO (Low Earth Orbit) transfer maneuver from a stratospheric altitude of 20 to 25 kilometers. Lack of drag, near earth gravity, and high atmospheric pressures coupled with a heavy focus on reducing overall payload mass enables STARSAT to achieve high orbital altitudes with minimal propulsion requirements. Phase 1 of the STARSAT design, fabrication and launch underway at the Kennedy Space Center in Florida is led by the development teams of STARHUNTER Corporation in conjunction with the National Aeronautics and Space Administration, The Florida Space Institute and the Central Florida Remote Sensing Labs. This conceptual report details the STARSAT orbital insertion profile, as well as subsystem design with a focus on propulsion and guidance techniques. Telemetry from the maiden launch of STARSAT will be discussed, in addition to future design goals. Overall, STARSAT has resulted in a cost effective mission profile for use throughout the small satellite industry.
