The NASA Risk Informed Decision Making process is used to assess a trade space of three dimension... more The NASA Risk Informed Decision Making process is used to assess a trade space of three dimensionally woven thermal protection systems for application to the Mars Sample Return Earth Entry Vehicle. Candidate architectures are assessed based on mission assurance, technical development, cost, and schedule risk. Assessment methodology differed between the architectures, utilizing a four-point quantitative scale for mission assurance and technical development and highly tailored PERT techniques for cost and schedule. Risk results are presented, in addition to a review of RIDM effectiveness for this application.
45th AIAA Aerospace Sciences Meeting and Exhibit, Jan 11, 2007
ComGeom2, a tool developed to generate Common Geometry representation for multidisciplinary analy... more ComGeom2, a tool developed to generate Common Geometry representation for multidisciplinary analysis, has been used to create a large set of geometries for use in a design study requiring analysis by two computational codes. This paper describes the process used to generate the large number of configurations and suggests ways to further automate the process and make it more efficient for future studies. The design geometry for this study is the launch abort system of the NASA Crew Launch Vehicle.
The Ice Giants represent a distinct class of planets within our solar system, and appear to be si... more The Ice Giants represent a distinct class of planets within our solar system, and appear to be similar to most exoplanets that have been detected thus far. Exploring Ice Giants in our Solar System would allow us to better understand their formation and evolution processes, and thus help establish scientific links to exoplanets. In situ exploration using probes similar to Galileo, along with an orbiter or a relay spacecraft, will require entry followed by deployment of the descent probe containing science instruments into Uranus or Neptune atmosphere. The challenge is not in the deployment of the probe, but in the atmospheric entry prior to deployment. The entry system has to have a capable, robust and efficient ablative thermal protection system (TPS) designed to protect the descent probe from the thermal and mechanical entry loads. Although entries into Ice Giants may not be as demanding as the Galileo entry at Jupiter, the entry environments will be more severe than environments for Mars, Sample Return missions, and Venus, and will therefore require robust TPS. While Galileo Probe's success, nearly 25 years ago, should give us confidence, the recession data from the Galileo entry informs us that the entry environment was underpredicted and the design thickness was barely adequate. The lesson learned from Galileo probe for future Ice Giant missions will require us to be cautious and demand a more robust design. The TPS technology used on Galileo entry system no longer exists due to atrophy of manufacturing processes. Instead of attempting to revive Galileo-legacy TPS technology, NASA invested in a new and innovative TPS called HEEET (Heat-shield for Extreme Entry Environment Technology). HEEET has been matured, and is now ready to support future missions not only to the Ice Giants but also for Venus, high-speed sample return, and Saturn probe missions. This lead talk, intended for the technology section of the workshop, will cover entry, descent, and deployment (EDD), with an emphasis on entry. A brief history of the TPS challenges for extreme entry missions will be given along with a quick overview of the concept of operations for EDD. The development and maturation of HEEET system capability will be described. Data gathered in ground-test facilities in the US will be highlighted to show that the technology is mature and ready for Ice Giant missions. All thermal protection systems carry some risk as a result of ground test limitations and Ice Giant missions present some unique challenges. These challenges are not only technical, but also due to limitations in the currently established manufacturing and integration. In addition, the concerns that arise due to potential for atrophy for future Ice Giant mission a decade or more from now will be analyzed. Plausible avenues for mitigation will be presented. There are two companion planned presentations by Dr. Prabhu and Dr. Hwang will dive deeper in the challenges and opportunities. This intended talk will set the stage for their presentations.
Entry, Descent and Deployment (EDD) of aerial platforms at Venus with rigid aero-shell is no mo... more Entry, Descent and Deployment (EDD) of aerial platforms at Venus with rigid aero-shell is no more challenging than at other destinations. • Limited only by the availability of efficient heat-shield/TPS technology. • NASA is investing in the maturation of "Heat-shield for Extreme Entry Environment Technology (HEEET)" to TRL 6 and is incentivizing its use for New Frontiers -4 missions • Future Venus Aerial Platform missions can use HEEET in place of Carbon Phenolic, which is not currently available HEEET is more mass efficient and permits lower-deceleration entry profile Lower ballistic coefficient concepts, ADEPT and HIAD, may offer additional opportunities
NASA's Space Technology Mission Directorate (STMD) and the Game Changing Development Program (GCD... more NASA's Space Technology Mission Directorate (STMD) and the Game Changing Development Program (GCDP) were created to develop new technologies. This paper describes four entry system technologies that are funded by the GCDP and summarizes the lessons learned during the development. The investments are already beginning to show success, mission infusion pathways after five years of existence. It is hoped that our experience and observations, drawn from projects supported by the GCD program/STMD, Orion and SMD can help current and future technology development projects. Observations on fostering a culture of success and on constraints that limit greater success are also provided.
Aerospace Vehicle Trajectory Design and Optimization Within a Multi-Disciplinary Environment
A trajectory design and optimization tool named Mission is developed to operate within a multi-di... more A trajectory design and optimization tool named Mission is developed to operate within a multi-disciplinary analysis tool environment for conceptual design of aerospace vehicles. Mission possesses several features designed to facilitate its set-up and operation within the ...
ComGeom2: A Geometry Tool for Multidisciplinary Analysis and Data Sharing
ComGeom2, a new geometry tool for multidisciplinary data analysis and data sharing, was developed... more ComGeom2, a new geometry tool for multidisciplinary data analysis and data sharing, was developed. Serving common computational geometry, including boundary regions, ComGeom2 helps ensure greater geometric consistency during the analysis of complex systems, such as aerospace vehicles. ComGeom2 implements a combination of technologies that together enhance the management of parametric geometry: ComGeom2 automates geometry through CAPRI, a programming interface for controlling CAD geometry; it makes use of an extensible component template library, permitting one to model systems of unlimited variety; and it employs the Launch Vehicle Language (LVL), a subsystem database that simplifies and standardizes system configuration and parameter specification. ComGeom2’s end product is an accurate, watertight surface discretization of the overall geometry for use in computational analysis. The surface mesh contains, in each element, boundary region and component labels for use in boundary condition tagging. ComGeom2 is presented in the context of launch vehicle systems.
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Papers by Peter Gage