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  • 1
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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
  • 2
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    Filtering technique based on high-frequency plant modeling for high-gain control (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This invention was an improvement in aircraft control systems that utilized feedback motion sensors to generate a signal to control the aircraft. The improvement consisted essentially of a complementary filter comprising a simplified model of the aircraft, a high pass filter, a low pass filter and a summing amplifier. The control signal was applied to the simplified model of the aircraft which attempted to compute the vehicle response to the signal. This computed response was then fed into the high pass filter to eliminate long term errors in the calculated response, with the result that a good estimate of the high frequency content of the aircraft motion was obtained. In order to obtain a good estimate of the low frequency content of the motion, a rate gyro signal was fed through the low pass filter that eliminates all of the offending noise.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Flight investigation of a vertical-velocity command system for VTOL aircraft (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was undertaken to assess the potential benefits afforded by a vertical-velocity command system (VVCS) for VTOL (vertical take-off and landing) aircraft. This augmentation system was conceived primarily as a means of lowering pilot workload during decelerating approaches to a hover and/or landing under category III instrument meteorological conditions. The scope of the investigation included a determination of acceptable system parameters, a visual flight evaluation, and an instrument flight evaluation which employed a 10 deg, decelerating, simulated instrument approach task. The results indicated that the VVCS, which decouples the pitch and vertical degrees of freedom, provides more accurate glide-path tracking and a lower pilot workload than does the unaugmented system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TN-D-8480 , L-11454
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The effect of variations in controls and displays on helicopter instrument approach capability (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was conducted with a variable stability helicopter to determine the effects of variations in controls and displays on helicopter instrument approach capabilities. The baseline instrument approach task was a decelerating approach to a hover along a 6 deg glide slope. Pilot evaluations were obtained for both the constant speed part of the task and the deceleration and hover part of the task. The attitude stability augmentation system (SAS) was strongly preferred over the rate SAS because the aircraft had a divergent pitch response. From a display variation standpoint, it was not possible to decelerate to a hover in a consistent manner, regardless of the control system employed, with situation information only. In particular, the deceleration and hover part of the task was unacceptable without flight director command information.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TN-D-8385 , L-10982
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Description of the VTOL Approach and Landing Technology (VALT) CH-47 research system (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Langley Research Center modified a CH-47B helicopter to provide a general-purpose variable-stability capability for the VTOL approach and landing technology (VALT) program. The functional aspects and capabilities of the overall system are described. Automatic decelerating approach data are presented to illustrate the performance of the overall system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1436 , L-12781
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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