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  • 1
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    A complementary filtering technique for deriving aircraft velocity and position information (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: An onboard navigation system which employed complementary filtering was developed to provide velocity and position information. The inputs to the mix filter included both acceleration inputs, which provided high-frequency position and velocity information, and radar position inputs, which provided the low-frequency position and velocity information. Onboard aircraft instrumentation, including attitude reference gyros and body-mounted accelerometers, was used to provide the acceleration information. An in-flight comparison of signal quality and accuracy showed good agreement between the complementary filtering system and an aided inertial navigation system. Furthermore, the complementary filtering system was proven to be satisfactory in control and display system applications for both automatic and pilot-in-the-loop instrument approaches and landings.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AGARD Methods for Aircraft State and Parameter Identification; 16 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Pilot assessment of two computer-generated display formats for helicopter instrument approach (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two computer generated display formats were evaluated as primary displays by six research pilots in a fixed base simulator. One of the computer generated display formats was an electronic attitude director indicator (EADI) which featured three cue flight director, command information, superimposed on true perspective runway symbology. The other computer generated display format featured separate horizontal and vertical situation information with vector predictors. A baseline display, consisting of an electromechanical attitude director indicator (ADI) with a three cue flight director and a moving map, was used as a reference for the pilot evaluations.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: NASA-TM-80151 , L-13136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Control theory analysis of a three-axis VTOL flight director (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A control theory analysis of a VTOL flight director and the results of a fixed-based simulator evaluation of the flight-director commands are discussed. The VTOL configuration selected for this study is a helicopter-type VTOL which controls the direction of the thrust vector by means of vehicle-attitude changes and, furthermore, employs high-gain attitude stabilization. This configuration is the same as one which was simulated in actual instrument flight tests with a variable stability helicopter. Stability analyses are made for each of the flight-director commands, assuming a single input-output, multi-loop system model for each control axis. The analyses proceed from the inner-loops to the outer-loops, using an analytical pilot model selected on the basis of the innermost-loop dynamics. The time response of the analytical model of the system is primarily used to adjust system gains, while root locus plots are used to identify dominant modes and mode interactions.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-69960
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flight investigation of manual and automatic VTOL decelerating instrument approaches and landings (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was undertaken to study the problems associated with manual and automatic control of steep, decelerating instrument approaches and landings under simulated instrument conditions. The study was conducted with a research helicopter equipped with a three-cue flight-director indicator. The scope of the investigation included variations in the flight-director control laws, glide-path angle, deceleration profile, and control response characteristics. Investigation of the automatic-control problem resulted in the first automated approach and landing to a predetermined spot ever accomplished with a helicopter. Although well-controlled approaches and landings could be performed manually with the flight-director concept, pilot comments indicated the need for a better display which would more effectively integrate command and situation information.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7524 , L-9311
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Application of a modified complementary filtering technique for increased aircraft control system frequency bandwidth in high vibration environment (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A modified complementary filtering technique for estimating aircraft roll rate was developed and flown in a research helicopter to determine whether higher gains could be achieved. Use of this technique did, in fact, permit a substantial increase in system frequency bandwidth because, in comparison with first-order filtering, it reduced both noise amplification and control limit-cycle tendencies.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-X-74004
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Higher gain for feedback control subject to vibrations (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Complementary filtering and simple electronic model greatly increase amount of useful gain achievable in feedback control system subjected to environmental vibration. Technique has increased useful gain from 2 to 4 and increased bandwidth from less than 0.5 Hz to over 1 Hz.
    Keywords: ELECTRONIC SYSTEMS
    Type: LAR-12215 , NASA Tech Briefs (ISSN 0145-319X); 4; 2; P. 185
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    A manual-control approach to development of VTOL automatic landing technology. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The operation of VTOL aircraft in the city-center environment will require complex landing-approach trajectories that insure adequate clearance from other traffic and obstructions and provide the most direct routing for efficient operations. As part of a larger program to develop the necessary technology base, a flight investigation was undertaken to study the problems associated with manual and automatic control of steep, decelerating instrument approaches and landings. The study employed a three-cue flight director driven by control laws developed and refined during manual-control studies and subsequently applied to the automatic approach problem. The validity of this approach was demonstrated by performing the first automatic approach and landings to a predetermined spot ever accomplished with a helicopter. The manual-control studies resulted in the development of a constant-attitude deceleration profile and a low-noise navigation system.
    Keywords: NAVIGATION
    Type: AHS PREPRINT 742 , Annual National Forum; May 09, 1973 - May 11, 1973; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Evaluation of a VTOL flight-director concept during constant-speed instrument approaches (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Evaluation of VTOL flight-director concept during constant-speed instrument approaches
    Keywords: AIRCRAFT
    Type: NASA-TN-D-5860 , L-7112
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Simultaneous usage of attitude control for VTOL maneuvering determined by in-flight simulation (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: In-flight simulation to evaluate simultaneous use of attitude control for jet VTOL maneuvering
    Keywords: AIRCRAFT
    Type: NASA-TN-D-5342
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A low-cost inertial smoothing system for landing approach guidance (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Accurate position and velocity information with low noise content for instrument approaches and landings is required for both control and display applications. In a current VTOL automatic instrument approach and landing research program, radar-derived landing guidance position reference signals, which are noisy, have been mixed with acceleration information derived from low-cost onboard sensors to provide high-quality position and velocity information. An in-flight comparison of signal quality and accuracy has shown good agreement between the low-cost inertial smoothing system and an aided inertial navigation system. Furthermore, the low-cost inertial smoothing system has been proven to be satisfactory in control and display system applications for both automatic and pilot-in-the-loop instrument approaches and landings.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7271 , L-8763
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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