Patent
Configuration-varying aircraft model iterative design method based on protection mapping
TLDR
In this article, a configuration-varying aircraft model iterative design method based on protection mapping is presented, which mainly comprises the steps of describing criterion configuration of an aircraft, analyzing the matching relation between configuration variations and flight conditions, discovering the internal relation between the configurations and model dynamic characteristics, obtaining a simplified design model of the aircraft, and obtaining optimal model parameters to realize optimal matching between the aircraft configuration and operating conditions.Abstract:
The invention discloses a configuration-varying aircraft model iterative design method based on protection mapping. The method mainly comprises the steps of describing criterion configuration of an aircraft, analyzing the matching relation between configuration variations and flight conditions, discovering the internal relation between the configuration variations and model dynamic characteristics, obtaining a simplified design model of the aircraft, analyzing model performance under the criterion configuration and obtaining optimal model parameters to realize optimal matching between the aircraft configuration and operating conditions. The method is beneficial for realizing model parameter setting in configuration-varying aircraft design; under complicated flight conditions, feasible model parameters are obtained adaptively based on the protection mapping theory according to expected open-loop and closed-loop performance requirements; through switching of the parameters, the designed model is made to cover a whole motion area, and meanwhile the stability of the configuration-varying aircraft can be ensured.read more
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References
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Patent
System and method for adaptive control of uncertain nonlinear processes
Anthony J. Calise,Byoung Soo Kim +1 more
TL;DR: In this paper, a linear controller and a neural network are used to control a nonlinear physical process, where the linear controller generates a control signal based on the command signal, a measured output signal, and a fixed linear model for the process.
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Flight control system self-adaption parameter adjustment method
TL;DR: In this paper, a self-adaptive parameter adjustment method for a flight control system is presented, which is characterized by, during the design process, to begin with, performing corresponding performance constraint based on flight qualities, such as bandwidth frequency, time delay, magnitude margin and phase margin, of an aircraft model, and establishing an area meeting flight performance requirements; and then obtaining design parameters, meeting area stabilization requirements, of the flight control systems by utilizing the protection mapping theory, meanwhile, automatically generating a controller set meeting the requirements, and thus self-adaption parameter adjustment of the