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  • Spacecraft Design, Testing and Performance  (6)
  • 2010-2014  (6)
  • 2000-2004
  • 1995-1999
  • 1960-1964
  • 2011  (6)
  • 1
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    A General Event Location Algorithm with Applications to Eclispe and Station Line-of-Sight (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A general-purpose algorithm for the detection and location of orbital events is developed. The proposed algorithm reduces the problem to a global root-finding problem by mapping events of interest (such as eclipses, station access events, etc.) to continuous, differentiable event functions. A stepping algorithm and a bracketing algorithm are used to detect and locate the roots. Examples of event functions and the stepping/bracketing algorithms are discussed, along with results indicating performance and accuracy in comparison to commercial tools across a variety of trajectories.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AAS 11-527 , GSFC.CP.4917.2011 , AAS/AIAA Astrodynamics Specialist Conference; Jul 31, 2011 - Aug 04, 2011; Girdwood, AK; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Impact of Vehicle Flexibility on IRVE-II Flight Dynamics (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Inflatable Re-entry Vehicle Experiment II (IRVE-II) successfully launched from Wallops Flight Facility (WFF) on August 17, 2009. The primary objectives of this flight test were to demonstrate inflation and re-entry survivability, assess the thermal and drag performance of the reentry vehicle, and to collect flight data for refining pre-flight design and analysis tools. Post-flight analysis including trajectory reconstruction outlined in O Keefe3 demonstrated that the IRVE-II Research Vehicle (RV) met mission objectives but also identified a few anomalies of interest to flight dynamics engineers. Most notable of these anomalies was high normal acceleration during the re-entry pressure pulse. Deflection of the inflatable aeroshell during the pressure pulse was evident in flight video and identified as the likely cause of the anomaly. This paper provides a summary of further post-flight analysis with particular attention to the impact of aeroshell flexibility on flight dynamics and the reconciliation of flight performance with pre-flight models. Independent methods for estimating the magnitude of the deflection of the aeroshell experienced on IRVE-II are discussed. The use of the results to refine models for pre-flight prediction of vehicle performance is then described.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-11508 , 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar; May 23, 2011 - May 26, 2011; Dublin; Ireland
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Modeling the Effects of Spacecraft Venting on Instrument Measurements of the Martian Atmosphere for an Elliptical Orbit (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Analysis has been performed for MAVEN mission. Due to the elliptical orbit, large pressure variations in orbit will be experienced, there is a need to understand how internal pressures change and the flux of gas from vents could potentially bias instrument measurements. Goal of this analysis is to predict the effect that atmospheric gases trapped and vented from spacecraft volumes could have on instrument measurements.
    Keywords: Spacecraft Design, Testing and Performance
    Type: GSFC.CPR.4746.2011 , 2011 Contamination, Coatings, and Materials Workshop; Jul 12, 2011 - Jul 14, 2011; Greenbelt, MD; United States
    Format: application/pdf
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  • 4
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    Advanced High-Temperature Flexible TPS for Inflatable Aerodynamic Decelerators (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Typical entry vehicle aeroshells are limited in size by the launch vehicle shroud. Inflatable aerodynamic decelerators allow larger aeroshell diameters for entry vehicles because they are not constrained to the launch vehicle shroud diameter. During launch, the hypersonic inflatable aerodynamic decelerator (HIAD) is packed in a stowed configuration. Prior to atmospheric entry, the HIAD is deployed to produce a drag device many times larger than the launch shroud diameter. The large surface area of the inflatable aeroshell provides deceleration of high-mass entry vehicles at relatively low ballistic coefficients. Even for these low ballistic coefficients there is still appreciable heating, requiring the HIAD to employ a thermal protection system (TPS). This TPS must be capable of surviving the heat pulse, and the rigors of fabrication handling, high density packing, deployment, and aerodynamic loading. This paper provides a comprehensive overview of flexible TPS tests and results, conducted over the last three years. This paper also includes an overview of each test facility, the general approach for testing flexible TPS, the thermal analysis methodology and results, and a comparison with 8-foot High Temperature Tunnel, Laser-Hardened Materials Evaluation Laboratory, and Panel Test Facility test data. Results are presented for a baseline TPS layup that can withstand a 20 W/cm2 heat flux, silicon carbide (SiC) based TPS layup, and polyimide insulator TPS layup. Recent work has focused on developing material layups expected to survive heat flux loads up to 50 W/cm2 (which is adequate for many potential applications), future work will consider concepts capable of withstanding more than 100 W/cm2 incident radiant heat flux. This paper provides an overview of the experimental setup, material layup configurations, facility conditions, and planned future flexible TPS activities.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-11425 , 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar; May 23, 2011 - May 26, 2011; Dublin; Ireland
    Format: application/pdf
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  • 5
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    A General Event Location Algorithm with Applications to Eclipse and Station Line-of-Sight (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A general-purpose algorithm for the detection and location of orbital events is developed. The proposed algorithm reduces the problem to a global root-finding problem by mapping events of interest (such as eclipses, station access events, etc.) to continuous, differentiable event functions. A stepping algorithm and a bracketing algorithm are used to detect and locate the roots. Examples of event functions and the stepping/bracketing algorithms are discussed, along with results indicating performance and accuracy in comparison to commercial tools across a variety of trajectories.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AAS-11-527 , LEGNEW-OLDGSFC-GSFC-LN-1152 , AAS/AIAA Astrodynamics Specialist Conference; Jul 31, 2011 - Aug 04, 2011; Girdwood, AK; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 6
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    Inflatable Re-entry Vehicle Experiment (IRVE-4) Overview (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The suite of Inflatable Re-Entry Vehicle Experiments (IRVE) is designed to further our knowledge and understanding of Hypersonic Inflatable Aerodynamic Decelerators (HIADs). Before infusion into a future mission, three challenges need to be addressed: surviving the heat pulse during re-entry, demonstrating system performance at relevant scales, and demonstrating controllability in the atmosphere. IRVE-4 will contribute to a better understanding of controllability by characterizing how a HIAD responds to a set of controlled inputs. The ability to control a HIAD is vital for missions that are g-limited, require precision targeting and guidance for aerocapture or entry, descent, and landing. The IRVE-4 flight test will focus on taking a first look into controlling a HIAD. This paper will give an overview of the IRVE-4 mission including the control response portion of the flight test sequence, and will provide a review of the mission s development.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-11478 , 21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar; May 23, 2011 - May 26, 2011; Dublin; Ireland
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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