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  • 1
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    Description of a dual fail operational redundant strapdown inertial measurement unit for integrated avionics systems research (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: An experimental redundant strapdown inertial measurement unit (RSDIMU) is developed as a link to satisfy safety and reliability considerations in the integrated avionics concept. The unit includes four two degree-of-freedom tuned rotor gyros, and four accelerometers in a skewed and separable semioctahedral array. These sensors are coupled to four microprocessors which compensate sensor errors. These microprocessors are interfaced with two flight computers which process failure detection, isolation, redundancy management, and general flight control/navigation algorithms. Since the RSDIMU is a developmental unit, it is imperative that the flight computers provide special visibility and facility in algorithm modification.
    Keywords: COMPUTER SYSTEMS
    Type: Ruggedized Minicomputer Hardware and Software Topics, 1981; p 209-217
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Unified analysis methods for a fault tolerant redundant strapdown inertial measurement unit (1983)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: The use of a redundant strapdown inertial measurement unit (RSDIMU) has been considered as a source of sensor information for future aircraft. It is pointed out that failure detection and isolation (FDI) should be accomplished at the sensor level to ensure the accurate transfer of information to elements of the integrated avionics system. The present investigation is concerned with the impact of the FDI algorithm on system reliability and vice versa. A description is given of a technique to identify and assess critical areas of reliability requirements for the RSDIMU. Attention is given to the development of an FDI algorithm to meet these requirements.
    Keywords: SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flight test configuration for verifying inertial sensor redundancy management techniques (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Redundant Strapdown Inertial Measurement Unit presently tested in flight configuration consists of a semioctahedral array of four dynamically tuned, two-degree-of-freedom (TDOF) gyros and four TDOF accelerometers which can provide dual, fail-operational performance for integrated avionics systems. Attention is given to the multilevel algorithm used for the detection and isolation of three ranges of sensor failure in an integrated avionics context. A technique for the generation of accelerometer and gyro error thresholds which is sensitive to dynamic sensor errors and separation effects is presented, together with simulation results. Emphasis is placed on the ensuring of highly reliable data for flight control/navigation functions, while minimizing false or missed alarms.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: AIAA PAPER 84-2496
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Design of a developmental dual fail operational redundant strapped down inertial measurement unit (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental redundant strap-down inertial measurement unit (RSDIMU) is being developed at NASA-Langley as a link to satisfy safety and reliability considerations in the integrated avionics concept. The unit consists of four two-degrees-of-freedom (TDOF) tuned-rotor gyros, and four TDOF pendulous accelerometers in a skewed and separable semi-octahedron array. The system will be used to examine failure detection and isolation techniques, redundancy management rules, and optimal threshold levels for various flight configurations. The major characteristics of the RSDIMU hardware and software design, and its use as a research tool are described.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: NAECON 1980; National Aerospace and Electronics Conference; May 20, 1980 - May 22, 1980; Dayton, OH
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Description of a dual fail-operational redundant strapdown inertial measurement unit for integrated avionics systems research (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Attention is given to a redundant strapdown inertial measurement unit for integrated avionics. The system consists of four two-degree-of-freedom turned rotor gyros and four two-degree-of-freedom accelerometers in a skewed and separable semi-octahedral array. The unit is coupled through instrument electronics to two flight computers which compensate sensor errors. The flight computers are interfaced to the microprocessors and process failure detection, isolation, redundancy management and flight control/navigation algorithms. The unit provides dual fail-operational performance and has data processing frequencies consistent with integrated avionics concepts presently planned.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: ROLM Computer Users Group Meeting; Feb 23, 1981 - Feb 25, 1981; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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