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  • 1
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    Flight test experience with pilot-induced-oscillation suppressor filters (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Digital flight control systems are popular for their flexibility, reliability, and power; however, their use sometimes results in deficient handling qualities, including pilot-induced oscillation (PIO), which can require extensive redesign of the control system. When redesign is not immediately possible, temporary solutions, such as the PIO suppression (PIOS) filter developed for the Space Shuttle, have been proposed. To determine the effectiveness of such PIOS filters on more conventional, high-performance aircraft, three experiments were performed using the NASA F-8 digital fly-by-wire and USAF/Calspan NT-33 variable-stability aircraft. Two types of PIOS filters were evaluated, using high-gain, precision tasks (close formation, probe-and-drogue refueling, and precision touch-and-go landing) with a time delay or a first-order lag added to make the aircraft prone to PIO. Various configurations of the PIOS filter were evaluated in the flight programs, and most of the PIOS filter configurations reduced the occurrence of PIOs and improved the handling qualities of the PIO-prone aircraft. These experiments also confirmed the influence of high-gain tasks and excessive control system time delay in evoking pilot-induced oscillations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-2107
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight-test results using nonlinear control with the F-8C digital fly-by-wire aircraft (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The design and operation of the cooperative advanced digital research experiment (CADRE) to develop nonlinear pitch flight control algorithms is described, and the results of an in-flight evaluation using the F-8C digital fly-by-wire (DFBW) research aircraft are presented. The CADRE controller is described, including the initial filter, linear command prefilter, nonlinear command prefilter, and gain scheduling. The variable-integral control-to-optimize response of the controller is considered, and CADRE parameter combinations are addressed. The remotely-augmented-vehicle interface used in the DFBW aircraft experiment is discussed. The distanct-tracking and close-formation tracking evaluation tasks for the aircraft are described along with evaluation configurations, and the test results are presented and discussed. The latter indicate that a nonlinear adaptive controller is a feasible control system technique for the fighter tracking task.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-2174 , Guidance and Control Conference; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    An in-flight investigation of pilot-induced oscillation suppression filters during the fighter approach and landing task (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An investigation of pilot-induced oscillation suppression (PIOS) filters was performed using the USAF/Flight Dynamics Laboratory variable stability NT-33 aircraft, modified and operated by Calspan. This program examined the effects of PIOS filtering on the longitudinal flying qualities of fighter aircraft during the visual approach and landing task. Forty evaluations were flown to test the effects of different PIOS filters. Although detailed analyses were not undertaken, the results indicate that PIOS filtering can improve the flying qualities of an otherwise unacceptable aircraft configuration (Level 3 flying qualities). However, the ability of the filters to suppress pilot-induced oscillations appears to be dependent upon the aircraft configuration characteristics. Further, the data show that the filters can adversely affect landing flying qualities if improperly designed. The data provide an excellent foundation from which detail analyses can be performed.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    An in-flight investigation of pilot-induced oscillation suppression filters during the fighter approach and landing task (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of pilot-induced oscillation suppression (PIOS) filters was performed using the USAF/Flight Dynamics Laboratory variable stability NT-33 aircraft, modified and operated by Calspan. This program examined the effects of PIOS filtering on the longitudinal flying qualities of fighter aircraft during the visual approach and landing task. Forty evaluations were flown to test the effects of different PIOS filters. Although detailed analyses were not undertaken, the results indicate that PIOS filtering can improve the flying qualities of an otherwise unacceptable aircraft configuration (Level 3 flying qualities). However, the ability of the filters to suppress pilot-induced oscillations appears to be dependent upon the aircraft configuration characteristics. Further, the data show that the filters can adversely affect landing flying qualities if improperly designed. The data provide an excellent foundation from which detail analyses can be performed.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-163116 , NAS 1.26:163116 , REPT-6645-F-9
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    Flight test experience with pilot-induced-oscillation suppression filters (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Digital flight control systems are popular for their flexibility, reliability, and power; however, their use sometimes results in deficient handling qualities, including pilot-induced oscillation (PIO), which can require extensive redesign of the control system. When redesign is not immediately possible, temporary solutions, such as the PIO suppression (PIOS) filter developed for the Space Shuttle, have been proposed. To determine the effectiveness of such PIOS filters on more conventional, high-performance aircraft, three experiments were performed using the NASA F-8 digital fly-by-wire and USAF/Calspan NT-33 variable-stability aircraft. Two types of PIOS filters were evaluated, using high-gain, precision tasks (close formation, probe-and-drogue refueling, and precision touch-and-go landing) with a time delay or a first-order lag added to make the aircraft prone to PIO. Various configurations of the PIOS filter were evaluated in the flight programs, and most of the PIOS filter configurations reduced the occurrence of PIOs and improved the handling qualities of the PIO-prone aircraft. These experiments also confirmed the influence of high-gain tasks and excessive control system time delay in evoking pilot-induced oscillations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-86028 , H-1216 , NAS 1.15:86028 , AIAA PAPER 83-2107 , AIAA Atmospheric Flight Mech. Conf.; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Unknown
    Analysis of augmented aircraft flying qualities through application of the Neal-Smith criterion (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Neal-Smith criterion is examined for possible applications in the evaluation of augmented fighter aircraft flying qualities. Longitudinal and lateral flying qualities are addressed. Based on the application of several longitudinal flying qualities data bases, revisions are proposed to the original criterion. Examples are given which show the revised criterion to be a good discriminator of pitch flying qualities. Initial results of lateral flying qualities evaluation through application of the Neal-Smith criterion are poor. Lateral aircraft configurations whose flying qualities are degraded by roll ratcheting effects map into the Level 1 region of the criterion. A third dimension of the criterion for flying qualities specification is evident. Additional criteria are proposed to incorporate this dimension into the criterion structure for flying qualities analysis.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 81-1776 , Guidance and Control Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
    Format: text
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    NASA TECHNICAL REPORTS
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