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A Perspective Analysis on Effects of Varying Inputs on UAV Model Estimation

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Abstract

The aviation use of Unmanned Aerial Vehicles (UAVs) necessitates a strong control design. The key to designing a durable control system is a well-developed flight dynamics model. System-based model identification techniques provide a useful means for estimating UAV modal parameters thereby saving time and money. Although considerable research is performed on UAV flight dynamics analysis utilizing system identification techniques, limited work exists that compares various techniques of system identification for UAVs in an exhaustive manner. Moreover, the research contributions toward performance evaluation and comparison of system identification methods outputs are even more scarce, especially under varying environmental conditions. In this study, a comprehensive framework utilizing various linear and nonlinear estimation techniques estimates unknown UAV model dynamics. To analyze the effects of varying flight conditions, a detailed analysis is performed which includes a parametric sweep of environmental elements as input arguments to the estimation process. The comparison involves the estimation of key performance parameters such as residual analysis, final prediction error, and fit percentages. Through rigorous analysis, it is demonstrated that the proposed framework predicts system parameters under a variety of conditions, thereby confirming its validity. It has also been demonstrated that a parametric sweep of environmental conditions, can be utilized to improve the authenticity of models’ data learning ranges, and their response to the prediction parameters. This paper, to the best of our knowledge, provides an elaborate platform for researchers to carry out comprehensive model prediction under a wide range of environmental conditions.

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Data Availability

The authors of this paper, for the best interest of the community, are willing to upload complete data-set in the repository, in case the research article is accepted for publication in the Journal. Moreover, the data-sets generated during the current study are also available from the corresponding author on reasonable request.

Abbreviations

\(\bar{c}\) :

Mean aerodynamic chord (m)

\(C_D\) :

Drag Coefficient

\(C_Y\) :

Side force Coefficient

C \(C_L\) :

Lift Coefficient

\(C_l\) :

Roll moment coefficient

\(C_m\) :

Pitch moment coefficient

\(C_n\) :

Yaw moment coefficient

D:

Drag (N)

g:

Gravitational acceleration (\(ms^{-2}\))

GCM:

Guidance and Control Module

h:

Altitude (m)

UAV:

Unmanned Aerial Vehicle

\(J_x,J_y,J_z\) :

Inertia matrix components in body frame

\(V_t\) :

Free-stream velocity (m/s)

L:

Lift (N)

m:

Vehicle mass (kg)

n,m,l:

Aerodynamic moment components for yaw, pitch and roll moments respectively, defined in body frame (Nm)

\(P_e,P_n\) :

Position coordinates along the inertial east and north directions (m)

p:

Roll rate in body frame (deg/sec)

q:

Pitch rate in body frame (deg/sec)

r:

Yaw rate in body frame (deg/sec)

\(q_{\infty }\) :

Free stream dynamic pressure \((N/m^2)\)

\(S_{Ref}\) :

Reference area \((m^2)\)

\(X_A,Y_A,Z_A\) :

Aerodynamic force components (axial, side and tangential force respectively) in the body frame (N)

T:

Engine thrust (N)

U:

Linear velocity along body x-axis (m/s)

V:

Linear velocity along body y-axis (m/s)

W:

Linear velocity along body z-axis (m/s)

W:

Weight (N)

ARX:

Automatic Regression eXogenous

ARMAX:

Automatic Regression Moving Average eXogenous

BJ:

Box Jenkin’s

OE:

Output Error

SS:

State Space

TP:

Tree Partition

WL:

WaveLet Network

NN:

Neural Network

FPE:

Final Prediction Error

MSE:

Mean Squared Error

n:

Model order for state space model

\(N_a\) :

Order of Polynomial A(q)

\(N_b\) :

Order of Polynomial B(q)

\(N_c\) :

Order of Polynomial C(q)

\(N_d\) :

Order of Polynomial D(q)

\(N_f\) :

Order of Polynomial F(q)

\(\rho \) :

Air density \((kg/m^3)\)

\(\beta \) :

Side slip angle (deg)

\(\alpha \) :

Aerodynamic angle of attack (deg)

\(\phi , \theta , \psi \) :

Roll, pitch and azimuth angles describing body frame w.r.t inertial frame (deg)

\(\gamma \) :

Flight path angle (deg)

\(\delta _a\) :

Aileron control

\(\delta _e\) :

Elevator control

\(\delta _f\) :

Flap control

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The first author (S Kounpal Fatima) and second author (Syed Manzar Abbas) performed the research. The third, fourth, and fifth authors (Imran Mir, Suleman Mir, and Faiza Gul) directed and conducted the framework of the research.

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Correspondence to Imran Mir.

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Fatima, S.K., Abbas, M., Mir, I. et al. A Perspective Analysis on Effects of Varying Inputs on UAV Model Estimation. J Intell Robot Syst 108, 71 (2023). https://doi.org/10.1007/s10846-023-01889-0

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