• DocumentCode
    2179478
  • Title

    An exploration of PRA methodology used in spacecraft design

  • Author

    Mattenberger, C. ; Nejad, H.

  • Author_Institution
    Sci. & Technol. Corp., NASA Ames Res. Center, Moffett Field, CA, USA
  • fYear
    2013
  • fDate
    28-31 Jan. 2013
  • Firstpage
    1
  • Lastpage
    6
  • Abstract
    In order to achieve an optimal design of a complex space system that meets all constraints, the requirements placed upon the performance, mass, cost, and risk of the system must be considered, understood and traded against each other during the conceptual design of the system to avoid costly redesigns or project cancellation later in the development process. A design process that follows this tenet of risk-informed design will need detailed insight into the relative risks facing the system, as well as quantitative estimates that can be produced through probabilistic risk assessment (PRA), in order to evaluate design decisions based upon the impact to all requirements on a co-equal basis. In this study, four types of methodologies used to produce risk estimates for spacecraft and satellites are examined. These include two traditional PRA methodologies, an innovative approach, and a top-down approach, all of which are explored by using the propulsion subsystem of the Lunar Reconnaissance Orbiter (LRO) as a comparative basis for the methodologies considered. Similarities, differences, benefits, and drawbacks of various bottom-up, component-based PRA approaches and the top-down approach are elucidated in terms of the process of modeling a system, the actionable information produced for the design team, and the overall quantitative risk evaluation of the system as compared to similar heritage space systems. Results of the various PRA methodologies are examined at the level of component failure rates, single-component failure probabilities, single-function failure probabilities where redundancy exists in the design, as well as the subsystem failure probability for the nominal LRO mission. Ultimately, all of the bottom-up, component-based PRA methods capture only the risk of a mature system and miss the risk contribution of design defects, which have been shown to be key drivers of reliability in single-use developmental systems. Therefore, further steps must be taken to - ncorporate this contribution in future PRA methodologies.
  • Keywords
    aerospace propulsion; artificial satellites; failure analysis; probability; redundancy; risk management; LRO; PRA methodology; co-equal basis; complex space system; failure rates; heritage space systems; lunar reconnaissance orbiter; probabilistic risk assessment; propulsion subsystem; redundancy; reliability; risk evaluation; risk informed design; satellites; single-component failure probability; single-function failure probability; spacecraft design; subsystem failure probability; top-down approach; Analytical models; Moon; Orbits; Propulsion; Redundancy; Space vehicles; PRA; R&M Applications in Aerospace; Risk Analysis and Management; Risk Informed Design;
  • fLanguage
    English
  • Publisher
    ieee
  • Conference_Titel
    Reliability and Maintainability Symposium (RAMS), 2013 Proceedings - Annual
  • Conference_Location
    Orlando, FL
  • ISSN
    0149-144X
  • Print_ISBN
    978-1-4673-4709-9
  • Type

    conf

  • DOI
    10.1109/RAMS.2013.6517726
  • Filename
    6517726