Author: Publisher:
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Category :
Languages : en
Pages :
Book Description
Digital adaptive Flight Controller Development
Author: Digital Adaptive Flight Controller Development
Author: Howard KaufmanPublisher:
ISBN:
Category : Adaptive control systems
Languages : en
Pages : 132
Book Description
A design study of adaptive control logic suitable for implementation in modern airborne digital flight computers was conducted. Two designs are described for an example aircraft. Each of these designs uses a weighted least squares procedure to identify parameters defining the dynamics of the aircraft. The two designs differ in the way in which control law parameters are determined. One uses the solution of an optimal linear regulator problem to determine these parameters while the other uses a procedure called single stage optimization. Extensive simulation results and analysis leading to the designs are presented.
Model Reference Single Stage Digital Adaptive Flight Controller Development
Author: Gurbux Singh AlagPublisher:
ISBN:
Category : Adaptive control systems
Languages : en
Pages : 136
Book Description
Digital Adaptive Flight Controller Development
Author: Publisher:
ISBN:
Category : Adaptive control systems
Languages : en
Pages : 130
Book Description
Research in Digital Adaptive Flight Controllers
Author: Howard KaufmanPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 106
Book Description
A Digital Adaptive Flight Controller
Author: William A. HansonDevelopment of an Advanced Digital Adaptive Flight Control System
Author: John ZaborszkyPublisher:
ISBN:
Category :
Languages : en
Pages : 161
Book Description
A new approach for a digital adaptive flight control system was developed. This approach consists of an explicit identification of the vehicle transfer function coefficients coupled with a control system parameter optimization to minimize an integral square error type criterion of performance. The investigation included theoretical studies which further developed the identification and parameter adjustment equations and established their effectiveness and the limits within which they are effective. These theoretical studies also established methods for the numerical integration which is needed in the identification and a search technique which is needed in the parameter adjustment process. Working equations which were used in the programming for the digital studies are included. The extensive all-digital and the hybrid simulation set up for this study is described. The all-digital simulation was useful in testing the sensitivity of the identification and parameter adjustment by taking numerous short runs under varying conditions. The hybrid simulation permitted testing the proposed methods in conjunction with realistic airframes in actual closed autopilot loops on realistic trajectories.
A Feasibility Study of Self-learning Adaptive Flight Control for High Performance Aircraft
Author: Stephen G. HoppePublisher:
ISBN:
Category : Automatic pilot (Airplanes)
Languages : en
Pages : 258
Book Description
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).
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