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Parametric model identification of delta wing UAVs using filter error method augmented with particle swarm optimisationopen access

Authors
Samuel, J. J. P.Kumar, N.Saderla, S.Kim, Y.
Issue Date
Jun-2023
Publisher
Royal Aeronautical Society
Keywords
Aerodynamic characterisation; Particle swarm optimisation; Filter error method; Unmanned aerial vehicle; Flight test method
Citation
Aeronautical Journal, v.127, no.1312, pp 982 - 1008
Pages
27
Indexed
SCIE
SCOPUS
Journal Title
Aeronautical Journal
Volume
127
Number
1312
Start Page
982
End Page
1008
URI
https://scholarworks.gnu.ac.kr/handle/sw.gnu/30487
DOI
10.1017/aer.2022.100
ISSN
0001-9240
2059-6464
Abstract
From arsenal delivery to rescue missions, unmanned aerial vehicles (UAVs) are playing a crucial role in various fields, which brings the need for continuous evolution of system identification techniques to develop sophisticated mathematical models for effective flight control. In this paper, a novel parameter estimation technique based on filter error method (FEM) augmented with particle swarm optimisation (PSO) is developed and implemented to estimate the longitudinal and lateral-directional aerodynamic, stability and control derivatives of fixed-wing UAVs. The FEM used in the estimation technique is based on the steady-state extended Kalman filter, where the maximum likelihood cost function is minimised separately using a randomised solution search algorithm, PSO and the proposed method is termed FEM-PSO. A sufficient number of compatible flight data sets were generated using two cropped delta wing UAVs, namely CDFP and CDRW, which are used to analyse the applicability of the proposed estimation method. A comparison has been made between the parameter estimates obtained using the proposed method and the computationally intensive conventional FEM. It is observed that most of the FEM-PSO estimates are consistent with wind tunnel and conventional FEM estimates. It is also noticed that estimates of crucial aerodynamic derivatives CL alpha , Cm-alpha, CY beta, Cl-beta and Cn(beta) obtained using FEM-PSO are having relative offsets of 2.5%, 1.5%, 6.5%, 3.4% and 7.6% w.r.t. wind tunnel values for CDFP, and 1.4%, 1.9%, 0.1%, 9.6% and 7.5% w.r.t. wind tunnel values for CDRW. Despite having slightly higher Cramer-Rao Lower Bounds of estimated aerodynamic derivatives using the FEM-PSO method, the simulated responses have a relative error of less than 0.10% w.r.t. measured flight data. A proof-of-match exercise is also conducted to ascertain the efficacy of the estimates obtained using the proposed method. The degree of effectiveness of the FEM-PSO method is comparable with conventional FEM.
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대학원 (기계항공우주공학부)
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