Kalman filter based modification on helicopter adaptive control

Date

2015-01-05

Author

Yavrucuk, İlkay

Metadata

Show full item record

Item Usage Stats

125
views

0
downloads

In this paper, a Kalman Filter based e-modification term is used in the update law of an online learning adaptive neural network controller for a helicopter application. The controller is applied to a high fidelity helicopter simulation model. The applications include both an example on a single-input single-output controller structure using a linear in the parameter neural network, but also a multi-input multi-output neural network structure to compensate uncertainties in the attitude control of a helicopter. It is observed that using a Kalman Filter based e-modification provides improved command following and requires less control effort compared to traditional e-modification.

URI

https://hdl.handle.net/11511/88139

Conference Name

AIAA Scitech Conference, (5 - 09 Ocak 2015)

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

KALMAN FILTER BASED MULTIMODE ATTITUDE DETERMINATION ALGORITHMS FOR A LEO SATELLITE Kutlu, Aykut; Tekinalp, Ozan (2009-02-12) This study presents the design of a Kalman filter based attitude determination algorithms for a hypothetical LEO satellite with a multimode structure that employs different sensor combinations and as well as online switching between these combinations depending on the sensor availability. The performance and effectiveness of these different attitude determination modes and the multimode structure are investigated through simulations. Especially the accuracy of the state estimation and the behavior of the sy...
Measurement correction of a set of analog sun sensors via neural network Sozen, Semsettin Numan; Gokce, Murat; Yavuzyilmaz, Cagatay; Gulmammadov, Farid; Söken, Halil Ersin (2021-06-23) A Neural Network (NN) based method to improve the accuracy of a set of analog Sun sensors is presented. Analog Sun Sensors are commonly used on satellites due to their reduced cost, small size and low power consumption. However, especially in Earth imaging satellites, they are prone to the Earth albedo effects. Magnitude and direction of albedo change depending on the reflection characteristics of the Earth's surface, position and attitude of the satellite and position of the Sun. The albedo may deteriorate...
An SRWNN-based approach on developing a self-learning and self-evolving adaptive control system for motion platforms Ari, Evrim Onur; Kocaoglan, Erol (2016-02-01) In this paper, a self-recurrent wavelet neural network (SRWNN)-based indirect adaptive control architecture is modified for performing speed control of a motion platform. The transient behaviour of the original learning algorithm has been improved by modifying the learning rate updates. The contribution of the proposed modification has been verified via both simulations and experiments. Moreover, the performance of the proposed architecture is compared with robust RST designs performed on a similar benchmar...
Kalman filter based applications for helicopters Okatan, Merve; Yavrucuk, İlkay; Department of Aerospace Engineering (2014) The study in this thesis comprises Kalman Filter based applications for helicopters. In the first part of this thesis, a Kalman filter for a helicopter is designed to integrate micro-electromechanical sensors with the Global Navigation Satellite Systems to achieve desired accuracy levels. It is implemented to a non-linear helicopter model and its performance is shown through simulations. In the second part of this thesis, Kalman Filter approach is adopted to neural network based adaptive controllers as a mo...
Impedance boundary conditions for time-domain computational aeroacoustics methods Özyörük, Yusuf (null; 1997-01-01) A time-domain impedance condition method has been developed for computational aeroacoustics applications. The basis for this method is the standard impedance condition stated in the frequency domain as the particle displacement continuity equation. The development of the time-domain impedance condition follows the relations among the frequency, z-, and discrete-time domains and a rational function representation of the impedance in the z-domain. The resultant impedance condition is finite, infinite-impulse-...

Citation Formats

İ. Yavrucuk, “Kalman filter based modification on helicopter adaptive control,” presented at the AIAA Scitech Conference, (5 - 09 Ocak 2015), 2015, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/88139.