Organizational Unit:
Daniel Guggenheim School of Aerospace Engineering

Permanent Link
https://hdl.handle.net/1853/70742
Research Organization Registry ID
Description
Previous Names
Parent Organization
Parent Organization
Organizational Unit
Includes Organization(s)
ArchiveSpace Name Record
https://finding-aids.library.gatech.edu/agents/corporate_entities/106

Filters

2008 2
2
2
2
2
Reset filters

Settings
Author: Papadopoulos, Periklis × Author: Schreck, Keith ×

Publication Search Results

Now showing 1 - 2 of 2
  • Thumbnail Image
    Item
    DOTNET Framework Design Environment for System Integration of Planetary Probe Payload Sensors and Interplanetary Trajectory Optimization
    (Georgia Institute of Technology, 2008-06-24) Schreck, Keith ; Papadopoulos, Periklis ; Subrahmanyam, Prabhakar
    An engineering level system analysis based on the mission requirements and a web based design environment has been developed specifically for planetary in-situ instrumentation. The software architecture is linked to a comprehensive instrumentation database via a middleware component that services the designer's requests through the framework. The framework also develops parametric trade studies at component architecture level for probes. The whole design process is iterative and made transparent to the designer and accepts criteria from the user making it an interactive tool. Interactivity is a key factor for any design environment and hence critical design decision factors come from the database and alerts the user to rectify flawed engineering decisions that might otherwise prove expensive at the final design phase. This engineering level "intelligent" design tool will catch common errors and alert the designer of such fundamental flawed assumptions that can be rectified and applied in the design mode. Once the design is done for the payload sensors, the software applies it against the selection criteria review process model which is based on operational ranges and required performance limits. After the final design, the probe can be flown and linked to an interplanetary trajectory optimization where several test cases are run. A Mars Sample return test case is analyzed in this framework and presented in this publication. This software architecture is a successful attempt in fusing the payload sensor system integration with an interplanetary trajectory optimization package all developed in Java language since java is platform independent.
  • Thumbnail Image
    Item
    Tool for Planetary Probe Payload Sensor System Integration
    (Georgia Institute of Technology, 2008-06-24) Schreck, Keith ; Djordjevich, Nik ; Papadopoulos, Periklis
    Determination 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.