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The TPS Advanced Development Project for CEVThe CEV TPS Advanced Development Project (ADP) is a NASA in-house activity for providing two heatshield preliminary designs (a Lunar direct return as well as a LEO only return) for the CEV, including the TPS, the carrier structure, the interfaces and the attachments. The project s primary objective is the development of a single heatshield preliminary design that meets both Lunar direct return and LEO return requirements. The effort to develop the Lunar direct return capable heatshield is considered a high risk item for the NASA CEV development effort due to the low TRL (approx. 4) of the candidate TPS materials. By initiating the TPS ADP early in the development cycle, the intent is to use materials analysis and testing in combination with manufacturing demonstrations to reduce the programmatic risk of using advanced TPS technologies in the critical path for CEV. Due to the technical and schedule risks associated a Lunar return heatshield, the ADP will pursue a parallel path design approach, whereby a back-up TPS/heatshield design that only meets LEO return requirements is also developed. The TPS materials and carrier structure design concept selections will be based on testing, analysis, design and evaluation of scalability and manufacturing performed under the ADP. At the TPS PDR, the preferred programmatic strategy is to transfer the continued (detailed) design, development, testing and evaluation (DDT&E) of both the Lunar direct and LEO return designs to a government/prime contractor coordinated sub-system design team. The CEV prime contractor would have responsibility for the continued heatshield sub-system development. Continued government participation would include analysis, testing and evaluation as well as decision authority at TPS Final System Decision (FSD) (choosing between the primary and back-up heatshields) occurring between TPS PDR and TPS Critical Design Review (CDR). After TPS FSD the prime CEV contractor will complete the detailed design, certification testing, procurement, and integration of the CEV TPS.
Document ID
20060016363
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Reuther, James
(NASA Ames Research Center Moffett Field, CA, United States)
Wercinski, Paul
(NASA Ames Research Center Moffett Field, CA, United States)
Venkatapathy, Ethiraj
(NASA Ames Research Center Moffett Field, CA, United States)
Ellerby, Don
(NASA Ames Research Center Moffett Field, CA, United States)
Raiche, George
(NASA Ames Research Center Moffett Field, CA, United States)
Bowman, Lynn
(NASA Langley Research Center Hampton, VA, United States)
Jones, Craig
(NASA Langley Research Center Hampton, VA, United States)
Kowal, John
(NASA Johnson Space Center Houston, TX, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2006
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: National Space and Missile Materials Symposium
Location: Orlando, FL
Country: United States
Start Date: June 26, 2006
End Date: June 30, 2006
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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