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Mathematical Modelling and Analysis of Nonlinear Aeroservoelastic framework for Light Aircraft / MARIYAM NASEER

By: NASEER, MARIYAM Contributor(s): Supervisor : Dr Muhammad Safdar Material type: Text

TextIslamabad : SMME- NUST; 2023Description: 116p. ; Soft Copy 30cmSubject(s): MS Mechanical EngineeringDDC classification: 621 Online resources: Click here to access online Summary: In this research, an aeroelastic model of light aircraft is developed with the help of structural mesh from PATRAN and aero model in ZAERO. Flutter analysis of this aeoelastic model is performed in ZAERO and lowest flutter speed is identified along with critical mode shapes. The effect of freeplay motion of different control surfaces of aircraft are modeled and isintegrated with the flight control algorithm in MATLAB to obtain the aeroservoelastic model. The model thus developed is solved for numerous flight conditions and different freeplay angles of the control surfaces. Analysis for aileron, rudder and elevator are conducted independently and simultaneous analysis for aileron and elevator freeplay is also studied. It is observed that the aeroservoelastic response of light aircraft is most senstive to elevator while rudder has negligible effect on aeroservoelastic response of light aircraft. Moreover the simultaneous motion of two control surfaces reduce the lowest flutter speed of aircraft. Hence the effect of simultaneous motion of control surfaces need to be addressed during design of light aircraft.

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Item type	Current location	Home library	Shelving location	Call number	Status	Date due	Barcode	Item holds
Thesis	School of Mechanical & Manufacturing Engineering (SMME)	School of Mechanical & Manufacturing Engineering (SMME)	E-Books	621 (Browse shelf)	Available		SMME-TH-865

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In this research, an aeroelastic model of light aircraft is developed with the help of structural mesh
from PATRAN and aero model in ZAERO. Flutter analysis of this aeoelastic model is performed in
ZAERO and lowest flutter speed is identified along with critical mode shapes. The effect of freeplay
motion of different control surfaces of aircraft are modeled and isintegrated with the flight control
algorithm in MATLAB to obtain the aeroservoelastic model. The model thus developed is solved for
numerous flight conditions and different freeplay angles of the control surfaces. Analysis for aileron,
rudder and elevator are conducted independently and simultaneous analysis for aileron and elevator
freeplay is also studied. It is observed that the aeroservoelastic response of light aircraft is most
senstive to elevator while rudder has negligible effect on aeroservoelastic response of light aircraft.
Moreover the simultaneous motion of two control surfaces reduce the lowest flutter speed of aircraft.
Hence the effect of simultaneous motion of control surfaces need to be addressed during design of
light aircraft.

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