DOTNET Framework Design Environment for System Integration of Planetary Probe Payload Sensors and Interplanetary Trajectory Optimization
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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.