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  • 1
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    Nonsingular Attitude Filtering Using Modified Rodrigues Parameters (2009)
    Springer
    Details
    Publication Date: 2009-10-01
    Print ISSN: 0021-9142
    Electronic ISSN: 2195-0571
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 2
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    Desensitized Optimal Filtering and Sensor Fusion Toolkit (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: Analytical Mechanics Associates, Inc., has developed a software toolkit that filters and processes navigational data from multiple sensor sources. A key component of the toolkit is a trajectory optimization technique that reduces the sensitivity of Kalman filters with respect to model parameter uncertainties. The sensor fusion toolkit also integrates recent advances in adaptive Kalman and sigma-point filters for non-Gaussian problems with error statistics. This Phase II effort provides new filtering and sensor fusion techniques in a convenient package that can be used as a stand-alone application for ground support and/or onboard use. Its modular architecture enables ready integration with existing tools. A suite of sensor models and noise distribution as well as Monte Carlo analysis capability are included to enable statistical performance evaluations.
    Keywords: Communications and Radar
    Type: An Overview of SBIR Phase 2 Communications Technology and Development; 8; NASA/TM-2015-218828
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Mars Phoenix EDL Trajectory and Atmosphere Reconstruction Using NewSTEP (2019)
    In:  CASI
    Details
    Publication Date: 2019-06-20
    Description: This document describes the trajectory and atmosphere reconstruction of the Mars Phoenix Entry, Descent, and Landing using the New Statistical Trajectory Estimation Program. The approach utilizes a Kalman filter to blend inertial measurement unit data with initial conditions and radar altimetry to obtain the inertial trajectory of the entry vehicle. The nominal aerodynamic database is then used in combination with the sensed accelerations to obtain estimates of the atmosphere-relative state. The reconstructed atmosphere pro le is then blended with pre-flight models to construct an estimate of the as-flown atmosphere.
    Keywords: Lunar and Planetary Science and Exploration
    Type: NASA/TM–2019–220282 , L-21028 , NF1676L-33202
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Trajectory Reconstruction of Orion Ground Test Article Water Impact Tests (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The Orion Crew Module is a component of NASAs Multi-Purpose Crew Vehicle that will be used for future missions to low Earth orbit and beyond. Ten water impact tests of the Orion Ground Test Article (GTA) were conducted at the Hydro Impact Basin at NASA Langley Research Center in 2016 and were designed to provide data for the validation of the LS-DYNA model used to determine the Crew Module structural loads during ocean splashdown, and the determination of an acceptable Model Uncertainty Factor to apply to simulation results used to drive the design. Post-test data obtained from the onboard sensors were used to reconstruct the GTA trajectories both before and after water impact. Results from one vertical test and two swing tests are presented and compared to videos taken for each test.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-27423 , AIAA SciTech 2018; Jan 08, 2018 - Jan 12, 2018; Kissimmee, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Hyper-X Post-Flight Trajectory Reconstruction (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses the formulation and development of a trajectory reconstruction tool for the NASA X{43A/Hyper{X high speed research vehicle, and its implementation for the reconstruction and analysis of ight test data. Extended Kalman ltering techniques are employed to reconstruct the trajectory of the vehicle, based upon numerical integration of inertial measurement data along with redundant measurements of the vehicle state. The equations of motion are formulated in order to include the effects of several systematic error sources, whose values may also be estimated by the ltering routines. Additionally, smoothing algorithms have been implemented in which the nal value of the state (or an augmented state that includes other systematic error parameters to be estimated) and covariance are propagated back to the initial time to generate the best-estimated trajectory, based upon all available data. The methods are applied to the problem of reconstructing the trajectory of the Hyper-X vehicle from ight data.
    Keywords: Astrodynamics
    Type: AIAA Paper 2004-4829 , AIAA Atmospheric Flight Mechanics Conference and Exhibit; Aug 16, 2004 - Aug 19, 2004; Providence, RI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Integrated Power and Attitude Control for a Spacecraft with Flywheels and Control Moment Gyroscopes (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A law is designed for simultaneous control of the orientation of an Earth-pointing spacecraft, the energy stored by counter-rotating flywheels, and the angular momentum of the flywheels and control moment gyroscopes used together as all integrated set of actuators for attitude control. General. nonlinear equations of motion are presented in vector-dyadic form, and used to obtain approximate expressions which are then linearized in preparation for design of control laws that include feedback of flywheel kinetic energy error as it means of compensating for damping exerted by rotor bearings. Two flywheel 'steering laws' are developed such that torque commanded by all attitude control law is achieved while energy is stored or discharged at the required rate. Using the International Space Station as an example, numerical simulations are performed to demonstrate control about a torque equilibrium attitude and illustrate the benefits of kinetic energy error feedback.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: AAS Paper 03-124 , 13th AAS/AIAA Space Flight Mechanics Meeting; Feb 09, 2003 - Feb 13, 2003; Ponce; Puerto Rico
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Mars Science Laboratory Entry, Descent, and Landing Trajectory and Atmosphere Reconstruction (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: On August 5th 2012, The Mars Science Laboratory entry vehicle successfully entered Mars atmosphere and landed the Curiosity rover on its surface. A Kalman filter approach has been implemented to reconstruct the entry, descent, and landing trajectory based on all available data. The data sources considered in the Kalman filtering approach include the inertial measurement unit accelerations and angular rates, the terrain descent sensor, the measured landing site, orbit determination solutions for the initial conditions, and a new set of instrumentation for planetary entry reconstruction consisting of forebody pressure sensors, known as the Mars Entry Atmospheric Data System. These pressure measurements are unique for planetary entry, descent, and landing reconstruction as they enable a reconstruction of the freestream atmospheric conditions without any prior assumptions being made on the vehicle aerodynamics. Moreover, the processing of these pressure measurements in the Kalman filter approach enables the identification of atmospheric winds, which has not been accomplished in past planetary entry reconstructions. This separation of atmosphere and aerodynamics allows for aerodynamic model reconciliation and uncertainty quantification, which directly impacts future missions. This paper describes the mathematical formulation of the Kalman filtering approach, a summary of data sources and preprocessing activities, and results of the reconstruction.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: AAS 13-307 , NF1676L-15404 , 23rd AAS/AIAA Space Flight Mechanics Meeting; Feb 10, 2013 - Feb 14, 2013; Kauai, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Modeling Multibody Stage Separation Dynamics Using Constraint Force Equation Methodology (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses the application of the constraint force equation methodology and its implementation for multibody separation problems using three specially designed test cases. The first test case involves two rigid bodies connected by a fixed joint, the second case involves two rigid bodies connected with a universal joint, and the third test case is that of Mach 7 separation of the X-43A vehicle. For the first two cases, the solutions obtained using the constraint force equation method compare well with those obtained using industry- standard benchmark codes. For the X-43A case, the constraint force equation solutions show reasonable agreement with the flight-test data. Use of the constraint force equation method facilitates the analysis of stage separation in end-to-end simulations of launch vehicle trajectories
    Keywords: Spacecraft Design, Testing and Performance
    Type: NF1676L-11076 , AIAA Modeling and Simulation Technologies Conference and Exhibit; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Mars Entry Atmospheric Data System Trajectory Reconstruction Algorithms and Flight Results (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars Entry Atmospheric Data System is a part of the Mars Science Laboratory, Entry, Descent, and Landing Instrumentation project. These sensors are a system of seven pressure transducers linked to ports on the entry vehicle forebody to record the pressure distribution during atmospheric entry. These measured surface pressures are used to generate estimates of atmospheric quantities based on modeled surface pressure distributions. Specifically, angle of attack, angle of sideslip, dynamic pressure, Mach number, and freestream atmospheric properties are reconstructed from the measured pressures. Such data allows for the aerodynamics to become decoupled from the assumed atmospheric properties, allowing for enhanced trajectory reconstruction and performance analysis as well as an aerodynamic reconstruction, which has not been possible in past Mars entry reconstructions. This paper provides details of the data processing algorithms that are utilized for this purpose. The data processing algorithms include two approaches that have commonly been utilized in past planetary entry trajectory reconstruction, and a new approach for this application that makes use of the pressure measurements. The paper describes assessments of data quality and preprocessing, and results of the flight data reduction from atmospheric entry, which occurred on August 5th, 2012.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: AIAA Paper 2013-0028 , NF1676L-14793 , 51st AIAA Aerospace Sciences Meeting; Jan 07, 2013 - Jan 10, 2013; Grapevine, TX; United States
    Format: application/pdf
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  • 10
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    Ares I-X Best Estimated Trajectory and Comparison with Pre-Flight Predictions (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Ares I-X trajectory reconstruction produced best estimated trajectories of the flight test vehicle ascent through stage separation, and of the first and upper stage entries after separation. The trajectory reconstruction process combines on-board, ground-based, and atmospheric measurements to produce the trajectory estimates. The Ares I-X vehicle had a number of on-board and ground based sensors that were available, including inertial measurement units, radar, air- data, and weather balloons. However, due to problems with calibrations and/or data, not all of the sensor data were used. The trajectory estimate was generated using an Iterative Extended Kalman Filter algorithm, which is an industry standard processing algorithm for filtering and estimation applications. This paper describes the methodology and results of the trajectory reconstruction process, including flight data preprocessing and input uncertainties, trajectory estimation algorithms, output transformations, and comparisons with preflight predictions.
    Keywords: Avionics and Aircraft Instrumentation
    Type: NF1676L-11960 , AIAA Atmospheric Flight Mechanics Conference; Aug 08, 2011 - Aug 11, 2011; Portland, OR; United States
    Format: application/pdf
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