DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

High Fidelity Modelling for High Altitude Long Endurance Solar Powered Aircraft

Lee, Jongseok (2017) High Fidelity Modelling for High Altitude Long Endurance Solar Powered Aircraft. DLR-Interner Bericht. DLR-IB-RM-OP-2017-115. Master's. ETH Zürich. 84 S.

[img] PDF


High Altitude Long Endurance (HALE) platforms are the aerial platforms capable of flying in the stratosphere for long periods of time. This master thesis presents aircraft system identification procedures geared towards such fixed wing platforms where aerodynamic forces and moments are parametrically modelled with so-called stability and control derivatives. The first part of the thesis addresses local System identification procedures intended for controller synthesis at low altitude flights whereas the second part of the thesis deals with a preliminary study on a new global system identification method. The local system identification procedure is based on the two step method, which offers flexibility regarding the aerodynamic structure. Therefore, it is suitable for the development of a system identification tool chain for various fixed wing platforms. Various system identification experiments have been conducted to collect flight test data. The parameters for the estimation of aerodynamic forces and moments are then found through an optimization procedure. Such parameters have been validated using a validation set from flight test data and their applicability for controller synthesis has been demonstrated. Global system identification typically requires the collection of flight test data at multiple points in the flight envelope and often, is combined with extensive Computational Fluid Dynamics (CFD) solutions as well as wind-tunnel experiments. Such an approach is time consuming and costly. This thesis presents a new method to overcome the limitations of the current methodology by applying a Parameter search on VLM-based (Vortex Lattice Method) dynamic simulations of aircraft System identification manoeuvres and correcting the estimated models with available flight test data. The current study shows improvements in fidelity with decrease in Root Mean Squared Error (RMSE) by factor 0.2 and 0.5 for x-axis and z-axis forces in body frame respectively, while reducing the effort for obtaining a model with similar fidelity.

Item URL in elib:https://elib.dlr.de/113198/
Document Type:Monograph (DLR-Interner Bericht, Master's)
Title:High Fidelity Modelling for High Altitude Long Endurance Solar Powered Aircraft
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Date:June 2017
Refereed publication:No
Open Access:Yes
Number of Pages:84
Keywords:high altitude Long endurance aircraft, global System identification, flight experiments, uav
Institution:ETH Zürich
Department:Autonomous Systems Lab
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space System Technology
DLR - Research area:Raumfahrt
DLR - Program:R SY - Space System Technology
DLR - Research theme (Project):R - Terrestrial Assistance Robotics (old)
Location: Oberpfaffenhofen
Institutes and Institutions:Institute of Robotics and Mechatronics (since 2013) > Analysis and Control of Advanced Robotic Systems
Deposited By: Muskardin, Tin
Deposited On:17 Jul 2017 17:47
Last Modified:31 Jul 2019 20:10

Repository Staff Only: item control page

Help & Contact
electronic library is running on EPrints 3.3.12
Website and database design: Copyright © German Aerospace Center (DLR). All rights reserved.