ADVANCED FLIGHT VEHICLE SELF-ADAPTIVE FLIGHT CONTROL SYSTEM. PART 3. SUPPORT EQUIPMENT STUDY.
ADVANCED FLIGHT VEHICLE SELF-ADAPTIVE FLIGHT CONTROL SYSTEM. PART 3. SUPPORT EQUIPMENT STUDY.

Author:

Publisher:

Published: 1961

Total Pages: 77

ISBN-13:

DOWNLOAD EBOOK

Results are presented of the design study to develop the ground support equipment for the MH-96 Adaptive Flight Control System to be tested in the X-15 aircraft. Design solutions are presented which reflect the problem areas that became apparent as the designs of the ground support equipment progressed. Since the final flight control system design changes have not yet been made, the GSE solutions have also not been finalized. However, this report presents a summary of the design practices being followed in the development of the ground support equipment for the MH-96 Adaptive Flight Control System.

APPLICATION AND EVALUATION OF CERTAIN ADAPTIVE CONTROL TECHNIQUES IN ADVANCED FLIGHT VEHICLES. VOLUME I.G.E. SELF-ADAPTIVE FLIGHT CONTROL SYSTEM.
APPLICATION AND EVALUATION OF CERTAIN ADAPTIVE CONTROL TECHNIQUES IN ADVANCED FLIGHT VEHICLES. VOLUME I.G.E. SELF-ADAPTIVE FLIGHT CONTROL SYSTEM.

Author:

Publisher:

Published: 1961

Total Pages: 171

ISBN-13:

DOWNLOAD EBOOK

The application and evaluation of certain adaptive control techniques were studied as applied to advanced vehicles of the X-15 and Dyna-Soar type. The general concept of adaptive control through the use of reference models is discussed, and particular models are evaluated based on the present status of airplane handling qualities research. The G.E. System is applied to the problem of controlling the longitudinal short-period motions of the X-15 airplane during re-entry. The first treatment of the problem is rather general, and uses essentially linear techniques to investigate the reference model concepts, selection of system parameters, responses to command inputs and gusts, effect of basic airplane static and dynamic instability, effect of sensor dynamics, and dynamics of the adaptive loop. Then a more detailed study is made of certain problem areas, including the response to inputs at the actuator valve, effect of actuator non-linearities, frequency sensor characteristics, and the effect of noise in the primary sensor, in this case a rate gyro.

Advances in Flight Control Systems
Advances in Flight Control Systems

Author: Maria Agneta Balint

Publisher: BoD – Books on Demand

Published: 2011-04-11

Total Pages: 314

ISBN-13: 9533072180

DOWNLOAD EBOOK

Nonlinear problems in flight control have stimulated cooperation among engineers and scientists from a range of disciplines. Developments in computer technology allowed for numerical solutions of nonlinear control problems, while industrial recognition and applications of nonlinear mathematical models in solving technological problems is increasing. The aim of the book Advances in Flight Control Systems is to bring together reputable researchers from different countries in order to provide a comprehensive coverage of advanced and modern topics in flight control not yet reflected by other books. This product comprises 14 contributions submitted by 38 authors from 11 different countries and areas. It covers most of the currents main streams of flight control researches, ranging from adaptive flight control mechanism, fault tolerant flight control, acceleration based flight control, helicopter flight control, comparison of flight control systems and fundamentals. According to these themes the contributions are grouped in six categories, corresponding to six parts of the book.

A Feasibility Study of Self-learning Adaptive Flight Control for High Performance Aircraft
A Feasibility Study of Self-learning Adaptive Flight Control for High Performance Aircraft

Author: Stephen G. Hoppe

Publisher:

Published: 1967

Total Pages: 258

ISBN-13:

DOWNLOAD EBOOK

A study of the feasibility of a self-learning adaptive system for the flight control of high performance aircraft has been performed. A flight control system was developed for the investigation of the stability augmentation of the longitudinal axis of the F101B aircraft using self-learning adaptive control. The learning adaptive controller developed employs a three-loop concept. The innermost loop comprises a linear feedback control system in which a set of control gains is adjusted by a second (adaptive) loop employing a parameter identifier and a trainable function generator (automation). The automation provides the correct values of feedback gain in response to patterns derived from the identified aircraft parameters. The third loop (the learning loop) measures control system performance, and continually retrains the automation to improve the performance. Experiments were performed with a digital simulation of the aircraft and the learning adaptive control system. Results of the experiments indicate that learning adaptive control is feasible. However, a number of significant technical problems must be overcome prior to the use of such a control system in tactical aircraft. Studies of sensitivity must be performed to assess the effect of small perturbations in the identification parameters on system performance. Extended studies of property extraction from the identified parameters is required, and means for further simplifying the control structure is of importance in a real system. (Author).