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  • 1
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    The Ultraviolet Imaging Telescope - Design and performance (1992)
    Institute of Physics
    Details
    Publication Date: 1992-08-01
    Print ISSN: 0004-637X
    Electronic ISSN: 1538-4357
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    Nano/Micro Satellite Constellations for Earth and Space Science (2003)
    Elsevier
    Details
    Publication Date: 2003-05-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    Fast Quaternion Attitude Estimation from Two Vector Measurements (2001)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Many spacecraft attitude determination methods use exactly two vector measurements. The two vectors are typically the unit vector to the Sun and the Earth's magnetic field vector for coarse "sun-mag" attitude determination or unit vectors to two stars tracked by two star trackers for fine attitude determination. Existing closed-form attitude estimates based on Wahba's optimality criterion for two arbitrarily weighted observations are somewhat slow to evaluate. This paper presents two new fast quaternion attitude estimation algorithms using two vector observations, one optimal and one suboptimal. The suboptimal method gives the same estimate as the TRIAD algorithm, at reduced computational cost. Simulations show that the TRIAD estimate is almost as accurate as the optimal estimate in representative test scenarios.
    Keywords: Spacecraft Instrumentation and Astrionics
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    NASA TECHNICAL REPORTS
  • 4
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    Attitude Error Representations for Kalman Filtering (2002)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The quaternion has the lowest dimensionality possible for a globally nonsingular attitude representation. The quaternion must obey a unit norm constraint, though, which has led to the development of an extended Kalman filter using a quaternion for the global attitude estimate and a three-component representation for attitude errors. We consider various attitude error representations for this Multiplicative Extended Kalman Filter and its second-order extension.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
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    NASA TECHNICAL REPORTS
  • 5
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    MEMS-Based Satellite Micropropulsion Via Catalyzed Hydrogen Peroxide Decomposition (2001)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Micro-electromechanical systems (MEMS) techniques offer great potential in satisfying the mission requirements for the next generation of "micro-scale" satellites being designed by NASA and Department of Defense agencies. More commonly referred to as "nanosats", these miniature satellites feature masses in the range of 10-100 kg and therefore have unique propulsion requirements. The propulsion systems must be capable of providing extremely low levels of thrust and impulse while also satisfying stringent demands on size, mass, power consumption and cost. We begin with an overview of micropropulsion requirements and some current MEMS-based strategies being developed to meet these needs. The remainder of the article focuses the progress being made at NASA Goddard Space Flight Center towards the development of a prototype monopropellant MEMS thruster which uses the catalyzed chemical decomposition of high concentration hydrogen peroxide as a propulsion mechanism. The products of decomposition are delivered to a micro-scale converging/diverging supersonic nozzle which produces the thrust vector; the targeted thrust level approximately 500 N with a specific impulse of 140-180 seconds. Macro-scale hydrogen peroxide thrusters have been used for satellite propulsion for decades; however, the implementation of traditional thruster designs on a MEMS scale has uncovered new challenges in fabrication, materials compatibility, and combustion and hydrodynamic modeling. A summary of the achievements of the project to date is given, as is a discussion of remaining challenges and future prospects.
    Keywords: Spacecraft Propulsion and Power
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  • 6
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    ASTEC: Controls analysis for personal computers (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ASTEC (Analysis and Simulation Tools for Engineering Controls) software is under development at Goddard Space Flight Center (GSFC). The design goal is to provide a wide selection of controls analysis tools at the personal computer level, as well as the capability to upload compute-intensive jobs to a mainframe or supercomputer. The project is a follow-on to the INCA (INteractive Controls Analysis) program that has been developed at GSFC over the past five years. While ASTEC makes use of the algorithms and expertise developed for the INCA program, the user interface was redesigned to take advantage of the capabilities of the personal computer. The design philosophy and the current capabilities of the ASTEC software are described.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: Jet Propulsion Lab., California Inst. of Tech., Proceedings of the 3rd Annual Conference on Aerospace Computational Control, Volume 2; p 600-605
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  • 7
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    New multivariable capabilities of the INCA program (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The INteractive Controls Analysis (INCA) program was developed at NASA's Goddard Space Flight Center to provide a user friendly, efficient environment for the design and analysis of control systems, specifically spacecraft control systems. Since its inception, INCA has found extensive use in the design, development, and analysis of control systems for spacecraft, instruments, robotics, and pointing systems. The (INCA) program was initially developed as a comprehensive classical design analysis tool for small and large order control systems. The latest version of INCA, expected to be released in February of 1990, was expanded to include the capability to perform multivariable controls analysis and design.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: Jet Propulsion Lab., California Inst. of Tech., Proceedings of the 3rd Annual Conference on Aerospace Computational Control, Volume 2; p 577-584
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  • 8
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    An application of the Observer/Kalman Filter Identification (OKID) technique to Hubble flight data (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of the current research is to identify vibration parameters, including frequencies, damping ratio and uncertainty characteristics, of the Hubble Space Telescope from flight data using an advanced system identification technique. The Observer/Kalman Filter Identification (OKID) technique is used to identify the vibration parameters. The OKID was recently developed by the researchers in the Spacecraft Dynamics Branch at NASA Langley Research Center.
    Keywords: ASTRONOMY
    Type: The Fifth NASA(DOD Controls-Structures Interaction Technology Conference, Part 1; p 97-112
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    NASA TECHNICAL REPORTS
  • 9
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    ASTEC and MODEL: Controls software development at Goddard Space Flight Center (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ASTEC (Analysis and Simulation Tools for Engineering Controls) software is under development at the Goddard Space Flight Center (GSFC). The design goal is to provide a wide selection of controls analysis tools at the personal computer level, as well as the capability to upload compute-intensive jobs to a mainframe or supercomputer. In the last three years the ASTEC (Analysis and Simulation Tools for Engineering Controls) software has been under development. ASTEC is meant to be an integrated collection of controls analysis tools for use at the desktop level. MODEL (Multi-Optimal Differential Equation Language) is a translator that converts programs written in the MODEL language to FORTRAN. An upgraded version of the MODEL program will be merged into ASTEC. MODEL has not been modified since 1981 and has not kept with changes in computers or user interface techniques. This paper describes the changes made to MODEL in order to make it useful in the 90's and how it relates to ASTEC.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: JPL, Proceedings of the Fifth NASA(NSF)DOD Workshop on Aerospace Computational Control; p 131-141
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  • 10
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    Generalization of the Euler Angles (2002)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: It is shown that the Euler angles can be generalized to axes other than members of an orthonormal triad. As first shown by Davenport, the three generalized Euler axes, hereafter: Davenport axes, must still satisfy the constraint that the first two and the last two axes be mutually perpendicular if these axes are to define a universal set of attitude parameters. Expressions are given which relate the generalized Euler angles, hereafter: Davenport angles, to the 3-1-3 Euler angles of an associated direction-cosine matrix. The computation of the Davenport angles from the attitude matrix and their kinematic equation are presented. The present work offers a more direct development of the Davenport angles than Davenport's original publication and offers additional results.
    Keywords: Theoretical Mathematics
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