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dc.contributor.authorSchreck, Keithen_US
dc.contributor.authorDjordjevich, Niken_US
dc.contributor.authorPapadopoulos, Periklisen_US
dc.date.accessioned2009-01-20T20:13:48Z
dc.date.available2009-01-20T20:13:48Z
dc.date.issued2008-06-24en_US
dc.identifier.urihttp://hdl.handle.net/1853/26412
dc.descriptionThis presentation was part of the session : Poster Sessionsen_US
dc.descriptionSixth International Planetary Probe Workshopen_US
dc.description.abstractDetermination of instrumentation for interplanetary science mission is an involved, complex procedure. A final design solution is achieved at the end of this often lengthy process. The analysis methodology performed within this work investigates mission requirements and generates a mission sensor package using design engineering relations. Given the broad science goals for an interplanetary science mission, the specific scientific measurements required can be determined. From the objectives the required measurements flow down, leading to an overall mission design. The mission design drives the instrumentation requirements and influences the selection of components for the mission. Components are chosen to meet mission requirements, creating an initial sensor package design. Trade studies are performed at component levels. Designs iterate on initial concepts and options are evaluated until a final design is determined. A tool for in-situ measurements is developed using systems engineering design relations to deliver a sensor payload configuration starting from the initial mission concept and the specific measurement objectives. Design of the sensor payload package for any mission is a combination of different aspects. The final design is a result of individual case studies at the component level and design engineering studies at a system level. Human decision elements are included in the design process, and final selection between competing components is made. The decision to use one flight hardware component over another can arise from many factors - functionality, heritage, Technology Readiness Level (TRL), compatibility, etc. The objective of this work is to combine selection techniques for mission hardware, based on optimization studies with engineering judgment, into a single tool that can be used to generate a preliminary sensor package configuration for planetary missions. A tool for in-situ measurements is developed using systems engineering design relations to deliver a sensor payload configuration starting from the initial mission objectives and the specific measurement types. The In-Situ Sensor Payload Optimization Tool (ISSPO) consists of a number of individual sensor modules, based on commercially available and space-rated components, and programs to determine the required components. Information on the desired mission location and types of science data to be returned, along with payload limits, are entered into the main program. For each sensor type available within the database, a corresponding module is executed and supplied information on the planetary location and additional sensor requirements. Selection of the final sensor is made based on operational ranges and required performance limits. Logic checks determine whether the sensor package meets or exceeds the mission limits, or if another combination of components would provide a viable solution with some requirement tradeoff. The resulting sensor package represents a preliminary sensor package capable of answering the mission's science requirements.en_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesIPPW08. Poster Sessionsen_US
dc.titleTool for Planetary Probe Payload Sensor System Integrationen_US
dc.typeProceedingsen_US
dc.contributor.corporatenameSan José State University. Dept. of Mechanical and Aerospace Engineeringen_US


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