Simulator based evaluation of adaptive envelope protection algorithms for active sidestick controllers

Download
2019
Ünal, Zeynep
In this thesis, a simulator environment with an active control system is developed for testing different force feedback maps for flight envelope limit avoidance. Previously developed flight envelope protection algorithm; named direct adaptive limit margin estimation method is improved with Single Hidden Layer Neural Network. Neural network based adaptive models are developed online using concurrent learning algorithm for weight update laws. Concurrent learning method uses both current data and recorded past data for adaptation. In this study, a Linear Parameter Neural Network and a Single Hidden Layer Neural Network are utilized and compared. The performance of single hidden layer neural network estimates are found to be more accurate for model error compensation. Three different force feedback maps are designed for pilot cueing with active side stick. Proposed force maps are tested on simulator environment. Performance of different force maps found to be dependent on type of limit parameters. Simulator based tests are conducted for rotorcraft model load factor limit avoidance and fixed wing aircraft load factor and angle of attack limit avoidance.

Suggestions

Direct Adaptive Limit and Control Margin Estimation with Concurrent Learning
Gursoy, Gonenc; Yavrucuk, İlkay (American Institute of Aeronautics and Astronautics (AIAA), 2016-6)
In this paper, two vital signals to enable flight envelope protection, namely the onset to the flight envelope (limit margin) and the available control travel to reach the limit boundary (control margin), are estimated using improved noniterative adaptive neural-network-based approximate models. The adaptive elements use current and past information (concurrent learning) and have guaranteed signal bounds. Minimum singular value maximization is used to record data for concurrent learning. Results showed bett...
Automatic Landing Flare Control Design by Model-Following Control and Flight Test on X-Plane Flight Simulator
Cetin, Ender; Kutay, Ali Türker (2016-07-20)
The aim of this study is to design a landing control system and test it on X-Plane flight simulator. Model-Following control and H-Infinity output feedback control methods are used to design the controller. In the flare part of the automatic landing system, it is desired to reduce the rate of descent in order to make aircraft touch down softly. This is accomplished by exponential decay trajectory. The trajectory which is drawn by the referenced model is followed by the linearized aircraft model. The error b...
Online Dynamic Trim and Control Limit Estimation
Yavrucuk, İlkay (American Institute of Aeronautics and Astronautics (AIAA), 2012-9)
The online estimation of a maneuvering steady-state condition of an aircraft, called the dynamic trim, is used to estimate the allowable control travel during flight, a key information in pilot cueing for envelope limit protection. In this paper a new methodology is presented where adaptive models are used to estimate online local dynamic trim conditions, while requiring very limited a priori vehicle information. Adaptive neural networks are employed to enable online learning. The models are used to estimat...
GPS based altitude control of an unmanned air vehicle using digital terrain elevation data
Ataç, Selçuk; Platin, Bülent Emre; Department of Mechanical Engineering (2006)
In this thesis, an unmanned air vehicle (UAV) is used to develop a prototype base test platform for flight testing of new control algorithms and avionics for advanced UAV system development applications. A control system that holds the UAV at a fixed altitude above the ground is designed and flight tested. Only the longitudinal motion of the UAV is considered during the controller design, hence its lateral motions are controlled manually by a remote control unit from the ground. UAV’s altitude with respect ...
Flight flutter testing and aeroelastic stability of aircraft
Kayran, Altan (2007-01-01)
Purpose - This paper sets out to provide a general review of the flight flutter test techniques utilized in aeroelastic stability flight testing of aircraft, and to highlight the key items involved in flight flutter testing of aircraft, by emphasizing all the main information processed during the flutter stability verification based on flight test data.
Citation Formats
Z. Ünal, “Simulator based evaluation of adaptive envelope protection algorithms for active sidestick controllers,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.