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  • 1
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    Deflection Analysis of the Space Shuttle External Tank Door Drive Mechanism (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Upon observing an abnormal closure of the Space Shuttle s External Tank Doors (ETD), a dynamic model was created in MSC/ADAMS to conduct deflection analyses of the Door Drive Mechanism (DDM). For a similar analysis, the traditional approach would be to construct a full finite element model of the mechanism. The purpose of this paper is to describe an alternative approach that models the flexibility of the DDM using a lumped parameter approximation to capture the compliance of individual parts within the drive linkage. This approach allows for rapid construction of a dynamic model in a time-critical setting, while still retaining the appropriate equivalent stiffness of each linkage component. As a validation of these equivalent stiffnesses, finite element analysis (FEA) was used to iteratively update the model towards convergence. Following this analysis, deflections recovered from the dynamic model can be used to calculate stress and classify each component s deformation as either elastic or plastic. Based on the modeling assumptions used in this analysis and the maximum input forcing condition, two components in the DDM show a factor of safety less than or equal to 0.5. However, to accurately evaluate the induced stresses, additional mechanism rigging information would be necessary to characterize the input forcing conditions. This information would also allow for the classification of stresses as either elastic or plastic.
    Keywords: Mechanical Engineering
    Type: 39th Aerospace Mechanisms Symposium; 249-258; NASA/CP-2008-215252
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Space Shuttle Orbiter Structures and Mechanisms (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Space Shuttle Orbiter has performed exceptionally well over its 30 years of flight experience. Among the many factors behind this success were robust, yet carefully monitored, structural and mechanical systems. From highlighting key aspects of the design to illustrating lessons learned from the operation of this complex system, this paper will attempt to educate the reader on why some subsystems operated flawlessly and why specific vulnerabilities were exposed in others. Specific areas to be covered will be the following: high level configuration overview, primary and secondary structure, mechanical systems ranging from landing gear to the docking system, and windows.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-24473 , AIAA Space 2011 Conference and Convention: Shuttle Legacy Track; Oct 26, 2011 - Oct 29, 2011; Long Beach, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    ORION - Crew Module Side Hatch: Proof Pressure Test Anomaly Investigation (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Orion Multi-Purpose Crew Vehicle program was performing a proof pressure test on an engineering development unit (EDU) of the Orion Crew Module Side Hatch (CMSH) assembly. The purpose of the proof test was to demonstrate structural capability, with margin, at 1.5 times the maximum design pressure, before integrating the CMSH to the Orion Crew Module structural test article for subsequent pressure testing. The pressure test was performed at lower pressures of 3 psig, 10 psig and 15.75 psig with no apparent abnormal behavior or leaking. During pressurization to proof pressure of 23.32 psig, a loud 'pop' was heard at ~21.3 psig. Upon review into the test cell, it was noted that the hatch had prematurely separated from the proof test fixture, thus immediately ending the test. The proof pressure test was expected be a simple verification but has since evolved into a significant joint failure investigation from both Lockheed Martin and NASA.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-40662 , Aerospace Mechanisms Symposium; May 16, 2018 - May 18, 2018; Cleveland, OH; United States
    Format: application/pdf
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  • 4
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    Deflection Analysis of the Space Shuttle External Tank Door Drive Mechanism (2008)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Upon observing an abnormal closure of the Space Shuttle s External Tank Doors (ETD), a dynamic model was created in MSC/ADAMS to conduct deflection analyses for assessing whether the Door Drive Mechanism (DDM) was subjected to excessive additional stress, and more importantly, to evaluate the magnitude of the induced step or gap with respect to shuttle s body tiles. To model the flexibility of the DDM, a lumped parameter approximation was used to capture the compliance of individual parts within the drive linkage. These stiffness approximations were then validated using FEA and iteratively updated in the model to converge on the actual distributed parameter equivalent stiffnesses. The goal of the analyses is to determine the deflections in the mechanism and whether or not the deflections are in the region of elastic or plastic deformation. Plastic deformation may affect proper closure of the ETD and would impact aero-heating during re-entry.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 39th Aerospace Mechanisms Symposium; May 07, 2008 - May 09, 2008; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Solidifying Small Satellite Access to Orbit via the International Space Station (ISS): Cyclops' Deployment of the Lonestar SmallSat from the ISS (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: On January 29, 2016, the Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, deployed Lonestar from the ISS. The deployment of Lonestar, a collaboration between Texas A&M University and the University of Texas at Austin, continued to showcase the simplicity and reliability of the Cyclops deployment system. Cyclops, a NASA-developed, dedicated 10-100 kg class ISS SmallSat deployment system, utilizes the Japanese airlock and robotic systems to seamlessly insert SmallSats into orbit. This paper will illustrate Cyclops' successful deployment of Lonestar from the ISS as well as outline its concept of operations, interfaces, requirements, and processes.
    Keywords: Spacecraft Design, Testing and Performance
    Type: SSC16-II-04 , JSC-CN-36516 , AIAA Small Satellite Conference; Aug 06, 2016 - Aug 11, 2016; Logan, UT; United States
    Format: application/pdf
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