Simulation and Control of Fixed Wing Aircraft After a Major Component Loss

Ozdemir, Ugur; Kavsaoğlu, Mehmet Şerif

doi:10.2514/6.2010-490

Cited by 2 publications

(4 citation statements)

References 1 publication

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“…To get aerodynamic force and moments, a new methodology is developed which is based on calculating the aerodynamic force and moments simultaneously for a specific state combination about each iteration of Newton Raphson and Runge-Kutta methods (Özdemir and Kurtulus 2021). This concept allows to use 6-DOF model at each phase of the design process of the aircraft.…”

Section: Aerodynamic Blockmentioning

confidence: 99%

Model based aircraft design and optimization: a case study with cessna 172N aircraft

Özdemir,

Kurtuluş

2023

Eng. Res. Express

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This study aims to create an interdisciplinary, multi-level design approach for fixed wing aircrafts. A case study is performed using Cessna 172N aircraft characteristics that is based on a mathematical model having six degrees of freedom (DOF). A Model Based Aircraft Design Software (MAD) is developed using a mathematical dynamic model in Python environment for use in the optimization phase of the Cessna 172N aircraft. The MAD environment is composed of analysis tools that communicate with each other by an automated process chain system. The model includes aerodynamics, engine, mass, control, atmosphere, and landing gear submodules. In addition, the model has trim and 6 DOF simulation analysis capabilities which provide a diversity of analyses that can be considered in early design phases. In order to get trimming and simulation capability, MAD software does not need any precalculated aerodynamic database. The force and moment calculations are performed instantly via DATCOM and AVL solvers for each iteration of simulation or trim. Thanks to this method, alternative aircraft geometries can be compared at the first phase of the design and optimization processes without creating an overall database. All methodologies of model submodules, performance, stability and control calculations, design, and optimization applications are implemented in the MAD environment.

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Section: Aerodynamic Blockmentioning

confidence: 99%

Model based aircraft design and optimization: a case study with cessna 172N aircraft

Özdemir,

Kurtuluş

2023

Eng. Res. Express

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“…FAULT DETECTION AND CONTROL Thrust force of turbofan engine depends on the sea level maximum thrust (T max,sl ), the density ratio (σ), the throttle setting (δ T i ), and the placement of the engine (ϕ T i , ψ T i ) [4,14]:…”

Section: Equations Of Motionmentioning

confidence: 99%

“…Other §ight parameters such as linear velocities, Then, by making initial guesses on the variables trim values, a search algorithm is employed to ¦nd the required amounts of control to achieve a balanced §ight. Details of the procedures of the trim analysis are explained in [4]. Table 1 shows these necessary amounts of controls.…”

Section: Trim Analysismentioning

confidence: 99%

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Flight dynamics analysis and control of transport aircraft subject to failure

Daskiran

Kavsaoğlu

2013

Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics

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After a structural damage or component failure during any §ight mode, aircraft dynamics are dramatically altered. A quick and adequate stabilization e¨ort is crucial. Flight dynamics for several failure scenarios are analyzed. Necessary amounts of control de §ections for postfailure trim are calculated. These trim values are used as control input in an open loop manner and validity of this approach is tested via §ight simulations. Alternatively, a closed loop §ight control system, which does not need the postfailure trim values, is also designed. This closed loop controller is based on a linearized aircraft model whereas §ight simulations are based on nonlinear aircraft dynamics.

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Simulation and Control of Fixed Wing Aircraft After a Major Component Loss

Cited by 2 publications

References 1 publication

Model based aircraft design and optimization: a case study with cessna 172N aircraft

Model based aircraft design and optimization: a case study with cessna 172N aircraft

Flight dynamics analysis and control of transport aircraft subject to failure

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