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Author: Dante A. Di Franco Publisher: ISBN: Category : Fighter planes Languages : en Pages : 394
Book Description
The results of a flight test program to investigate the effects of higher-order control system dynamics on the handling qualities of a fighter airplane are presented and discussed. This research was undertaken using the variable stability T-33 airplane as an in-flight simulator. This in-flight investigation was based on a similar fixed-base ground simulator program. Higher-order response characteristics were obtained by altering the elevator stick feel system dynamics and elevator actuator dynamics in conjunction with four different sets of longitudinal short period airplane dynamics. In the investigation, the dynamics of any of the three elements (feel system, actuator, and airplane) could be changed independently of the others. Three of the set of four airplane characteristics were investigated as a fighter in 'up-and-away' flight, and the fourth was evaluated as a fighter during landing approach. Thirty-two different configurations were evaluated by one evaluation pilot (Pilot B) and 35 configurations were evaluated by a second evaluation pilot (Pilot H). Essentially the same configurations were evaluated by both pilots and rated using a new pilot rating scale. Pilot H also rated the configurations for their pilot-induced oscillation (PIO) tendencies using a PIO rating scale. Pilot comments were recorded in flight and the comments and ratings were related to various handling qualities parameters and response characteristics of the configurations. (Author).
Author: Dante A. Di Franco Publisher: ISBN: Category : Fighter planes Languages : en Pages : 394
Book Description
The results of a flight test program to investigate the effects of higher-order control system dynamics on the handling qualities of a fighter airplane are presented and discussed. This research was undertaken using the variable stability T-33 airplane as an in-flight simulator. This in-flight investigation was based on a similar fixed-base ground simulator program. Higher-order response characteristics were obtained by altering the elevator stick feel system dynamics and elevator actuator dynamics in conjunction with four different sets of longitudinal short period airplane dynamics. In the investigation, the dynamics of any of the three elements (feel system, actuator, and airplane) could be changed independently of the others. Three of the set of four airplane characteristics were investigated as a fighter in 'up-and-away' flight, and the fourth was evaluated as a fighter during landing approach. Thirty-two different configurations were evaluated by one evaluation pilot (Pilot B) and 35 configurations were evaluated by a second evaluation pilot (Pilot H). Essentially the same configurations were evaluated by both pilots and rated using a new pilot rating scale. Pilot H also rated the configurations for their pilot-induced oscillation (PIO) tendencies using a PIO rating scale. Pilot comments were recorded in flight and the comments and ratings were related to various handling qualities parameters and response characteristics of the configurations. (Author).
Author: H.A. Mooij Publisher: Springer Science & Business Media ISBN: 9401711933 Category : Technology & Engineering Languages : en Pages : 151
Book Description
In-fl ight simulation experiments performed in 1967 with a variable-stabil ity aircraft during the author's stay at Princeton University, motivated the study of handl ing characteristics of future transport aircraft with closed-loop fl ight control systems. In 1972, the first experiment took place at the National Aerospace Laboratory NLR, using one of its research aircraft. In anticipation of expected developments in (digital) fl ight control technology, the research programme following the first experiments was aimed at the establ ishment of quantitative handl ing qual ities criteria. An appreciable part of that programme has been sponsored by the Netherlands Agency for Aerospace Programs (Nederlands Instituut voor VI iegtuigontwikkel ing en Ruimtevaart) and the Department of Civil Aviation of the Netherlands (Rijksluchtvaartdienst). In 1981, a thorough review of the extensive and valuable data gathered was started. The result, presented in this book, was also included in the author's thesis for a Ph.D. degree of the Delft University of Technology. To introduce the reader to the multi-discipl inary field of handl ing qual ities research, introductory chapters are presented on longitudinal aircraft dynamics, closed-loop fl ight control systems using non-mechanical signal transmission, human pilot dynamics, hand I ing qual ities assessment techniques, and the present status of handl ing qual ity criteria.
Author: Muhammad Anwar Pasha Publisher: ISBN: Category : Languages : en Pages : 236
Book Description
The approach and landing longitudinal flying qualities data generated by Calspan using variable stability NT-33 aircraft combined with significant control system dynamics was analyzed. Three different approaches were used to determine the relationship between pilot ratings and the pilot workload, system sensitivity, and the system performance. An open-loop frequency response analysis showed that for a particular cross over frequency and phase margin (fixed performance), the phase angle (pilot workload) and slope of the phase curve (system sensitivity) at the crossover frequency correlated well with the pilot ratings. An optimum pilot lead time for pitch tracking, flight path angle tracking, and both pitch and flight path angle tracking tasks is determined by a closed-loop analog simulation using integral error squared as a performance measure. A correlation is found between pilot ratings and performance. An attempt is made to explain the landing task as a closed-loop pitch and flight path angle tracking task. The open-loop impulse response of the pitch attitude showed that the initial delay and the transient behavior of the pitch response have a direct impact on the pilot ratings, pilot induced oscillations, and comments. (Author).
Author: Publisher: ISBN: Category : Languages : en Pages : 224
Book Description
A study of the handling qualities of large airplanes in the approach and landing flight phase was performed. An in-flight simulation experiment utilizing the USAF/Calspan Total In-Flight simulator was performed. A one-million pound statically-unstable delta-wing airplane model was used as a baseline about which variations were made. The primary variables were relative pilot position with respect to center of rotation, command path time delays and phase shifts, augmentation schemes and levels of augmentation. The experiment design, its conduct and analysis of the data are described. Results indicate that the approach and landing task with large airplanes is a low bandwidth task. Low equivalent short period frequencies and relatively long time delays can be tolerated only when the pilot is located a considerable distance forward of the center of rotation. As the pilot position is moved aft towards and then behind the center of rotation, as is the space shuttle, pilot ratings are degraded. A multi-loop analysis of pitch attitude and altitude control gave insight into this pilot position phenomenon. The control problem experienced by the pilots, when seated behind the center of rotation, tended to occur at low altitude when they were using visual cues of rate of sink and altitude. These configurations also lack the initial normal acceleration cue from pitch acceleration that conventional large airplane configurations possess. A direct lift controller improved final flight path control of these shuttle-like configurations.
Author: S. G. Fuller Publisher: ISBN: Category : Airplanes Languages : en Pages : 726
Book Description
Proceedings are reported of a symposium held in Dayton, sponsored by the Flight Dynamics Laboratory during 2-5 March 1982. The symposium was planned and ran by the Flight Control Division, specifically the Flying Qualities Group and the Control Techniques Group as part of an ongoing effort to revise and upgrade both MIL-F-8785C, Military Specification, Flying Qualities of Piloted Airplanes, and MIL-F-9490D, Flight Control System-Design, Installation and Test of Piloted Aircraft, General Specification For. Specialists from both the flying qualities and flight control system disciplines were gathered in Dayton from both industry and government agencies. Formal and informal presentations, plus workshop discussions, were structured around proposed draft versions of the new Flying Qualities MIL-Standard and Handbook and the new Flight Control Systems MIL-Specification and Handbook. This report contains a record of the presentations and discussions as submitted by the individual authors.
Author: Henry R. Jex Publisher: ISBN: Category : Adaptive control systems Languages : en Pages : 108
Book Description
The systems-analysis theory of handling qualities (which describes the pilot's adaptive behavior in closed-loop operation by servo techniques, and relates his opinion-ratings to his adapted characteristics and the system performance) is used to reveal some important parameters associated with the numerator terms in the airframe longitudinal transfer function. The predictions are verified by five experienced test pilots operating in a fixed-base aircraft simulator. Four possible numerator effects on handling qualities are analyzed theoretically: short-period lead effect on pitch attitude tracking, static-to-short-period gain effects on attitude tracking, short-period lead effects on the control of short-period divergence, and numerator frequency and damping effects on altitude tracking. The results are correlated with other test work, and the implications of these results on future handling qualities research and specifications are discussed.
Author: Dante A. Di Franco
Author: Dante A. Di Franco
Author: Melvin Sadoff
Author: H.A. Mooij
Author: Muhammad Anwar Pasha
Author: 
Author: 
Author: Dante A. DiFranco
Author: S. G. Fuller
Author: Henry R. Jex
Author: Roger H. Hoh