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  • 1
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    Small Body Landings Using Autonomous Onboard Optical Navigation (2011)
    Springer
    Details
    Publication Date: 2011-07-01
    Print ISSN: 0021-9142
    Electronic ISSN: 2195-0571
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 2
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    Spin State Estimation of Tumbling Small Bodies (2016)
    Springer
    Details
    Publication Date: 2016-02-03
    Print ISSN: 0021-9142
    Electronic ISSN: 2195-0571
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 3
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    Sensitivity of Magnetospheric Multi-Scale (MMS) Mission Navigation Accuracy to Major Error Sources (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: The Magnetospheric Multiscale (MMS) mission consists of four satellites flying in formation in highly elliptical orbits about the Earth, with a primary objective of studying magnetic reconnection. The baseline navigation concept is independent estimation of each spacecraft state using GPS pseudorange measurements referenced to an Ultra Stable Oscillator (USO) with accelerometer measurements included during maneuvers. MMS state estimation is performed onboard each spacecraft using the Goddard Enhanced Onboard Navigation System (GEONS), which is embedded in the Navigator GPS receiver. This paper describes the sensitivity of MMS navigation performance to two major error sources: USO clock errors and thrust acceleration knowledge errors.
    Keywords: Instrumentation and Photography
    Type: AAS 11-207 , 21st AAS/AISS Space Flight Mechanics Meeting; 13-17 Feb. 201l; New Orleans, LA; United States
    Format: application/pdf
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  • 4
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    Expected Navigation Flight Performance for the Magnetospheric Multiscale (MMS) Mission (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Magnetospheric Multiscale (MMS) mission consists of four formation-flying spacecraft placed in highly eccentric elliptical orbits about the Earth. The primary scientific mission objective is to study magnetic reconnection within the Earth s magnetosphere. The baseline navigation concept is the independent estimation of each spacecraft state using GPS pseudorange measurements (referenced to an onboard Ultra Stable Oscillator) and accelerometer measurements during maneuvers. State estimation for the MMS spacecraft is performed onboard each vehicle using the Goddard Enhanced Onboard Navigation System, which is embedded in the Navigator GPS receiver. This paper describes the latest efforts to characterize expected navigation flight performance using upgraded simulation models derived from recent analyses.
    Keywords: Spacecraft Design, Testing and Performance
    Type: GSFC.CPR.6014.2012 , 2012 Space Flight Mechanics Conference; Jan 29, 2012 - Feb 02, 2012; Charleston, SC; United States
    Format: application/pdf
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  • 5
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    Magnetospheric Multiscale (MMS) Mission Navigation Concept (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Astrodynamics
    Type: GSFC.CPR.5479.2011 , Young Professional, Student, and Education Conference (YPSE-11); Nov 04, 2011; MD; United States
    Format: application/pdf
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  • 6
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    Small Body Landing Accuracy Using In-Situ Navigation (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft landings on small bodies (asteroids and comets) can require target accuracies too stringent to be met using ground-based navigation alone, especially if specific landing site requirements must be met for safety or to meet science goals. In-situ optical observations coupled with onboard navigation processing can meet the tighter accuracy requirements to enable such missions. Recent developments in deep space navigation capability include a self-contained autonomous navigation system (used in flight on three missions) and a landmark tracking system (used experimentally on the Japanese Hayabusa mission). The merging of these two technologies forms a methodology to perform autonomous onboard navigation around small bodies. This paper presents an overview of these systems, as well as the results from Monte Carlo studies to quantify the achievable landing accuracies by using these methods. Sensitivity of the results to variations in spacecraft maneuver execution error, attitude control accuracy and unmodeled forces are examined. Cases for two bodies, a small asteroid and on a mid-size comet, are presented.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AAS-11-056 , AAS Guidance, Navigation, and Control Meeting; Feb 04, 2011 - Feb 09, 2011; Breckenridge, CO; United States
    Format: text
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  • 7
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    Precomputing Process Noise Covariance for Onboard Sequential Filters (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Process noise is often used in estimation filters to account for unmodeled and mismodeled accelerations in the dynamics. The process noise covariance acts to inflate the state covariance over propagation intervals, increasing the uncertainty in the state. In scenarios where the acceleration errors change significantly over time, the standard process noise covariance approach can fail to provide effective representation of the state and its uncertainty. Consider covariance analysis techniques provide a method to precompute a process noise covariance profile along a reference trajectory, using known model parameter uncertainties. The process noise covariance profile allows significantly improved state estimation and uncertainty representation over the traditional formulation. As a result, estimation performance on par with the consider filter is achieved for trajectories near the reference trajectory without the additional computational cost of the consider filter. The new formulation also has the potential to significantly reduce the trial-and-error tuning currently required of navigation analysts. A linear estimation problem as described in several previous consider covariance analysis publications is used to demonstrate the effectiveness of the precomputed process noise covariance, as well as a nonlinear descent scenario at the asteroid Bennu with optical navigation.
    Keywords: Numerical Analysis; Space Communications, Spacecraft Communications, Command and Tracking
    Type: GSFC-E-DAA-TN38754 , Journal of Guidance, Control, and Dynamics (ISSN 0731-5090) (e-ISSN 1533-3884); 40; 8; 2062-2075
    Format: application/pdf
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  • 8
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    Sensitivity of Magnetospheric Multi-Scale (MMS) Mission Naviation Accuracy to Major Error Sources (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Magnetospheric Multiscale (MMS) mission consists of four satellites flying in formation in highly elliptical orbits about the Earth, with a primary objective of studying magnetic reconnection. The baseline navigation concept is independent estimation of each spacecraft state using GPS pseudorange measurements referenced to an Ultra Stable Oscillator (USO) with accelerometer measurements included during maneuvers. MMS state estimation is performed onboard each spacecraft using the Goddard Enhanced Onboard Navigation System (GEONS), which is embedded in the Navigator GPS receiver. This paper describes the sensitivity of MMS navigation performance to two major error sources: USO clock errors and thrust acceleration knowledge errors.
    Keywords: Instrumentation and Photography
    Type: AAS 11-207 , LEGNEW-OLDGSFC-GSFC-LN-1049 , AAS/AIAA Space Flight Mechanics Meeting; Feb 13, 2011 - Feb 17, 2011; New Orleans, LA; United States
    Format: application/pdf
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  • 9
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    Precomputing Process Noise Covariance for Onboard Sequential Filters (2017)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Process noise is often used in estimation filters to account for unmodeled and mismodeled accelerations in the dynamics. The process noise covariance acts to inflate the state covariance over propagation intervals, increasing the uncertainty in the state. In scenarios where the acceleration errors change significantly over time, the standard process noise covariance approach can fail to provide effective representation of the state and its uncertainty. Consider covariance analysis techniques provide a method to precompute a process noise covariance profile along a reference trajectory using known model parameter uncertainties. The process noise covariance profile allows significantly improved state estimation and uncertainty representation over the traditional formulation. As a result, estimation performance on par with the consider filter is achieved for trajectories near the reference trajectory without the additional computational cost of the consider filter. The new formulation also has the potential to significantly reduce the trial-and-error tuning currently required of navigation analysts. A linear estimation problem as described in several previous consider covariance analysis studies is used to demonstrate the effectiveness of the precomputed process noise covariance, as well as a nonlinear descent scenario at the asteroid Bennu with optical navigation.
    Keywords: Engineering (General); Systems Analysis and Operations Research
    Type: GSFC-E-DAA-TN50808 , Journal of Guidance Control and Dynamics (ISSN 0731-5090) (e-ISSN 1533-3884); 40; 8; 2062-2075
    Format: text
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