Tesis ini mengandungi kajian kestabilan simulasi penerbangan helikopter dan prosedur terperinci mengenai cara membina model matematik asas yang mewakili dinamik penerbangan helikopter longitudinal yang umum. Kaedah dalam mengkaji kestabilan difokuskan kepada struktur state space model bagi sesebuah helikopter. Prosedur dimulai dengan memahami idea mengenai bagaimana sesebuah helikopter telah dikendalikan dengan menggunakan beberapa set input kawalan. Input-input kawalan tersebut ialah sudut kolektif (θo), sudut longitudinal siklik (θls), dan sudut lateral siklik (θlc) yang mengendalikan kawalan rotor utama, serta sudut rotor ekor kolektif (θot), bagi rotor ekor. Keluaran dari helikopter dikenalpasti berdasarkan model helikopter. Persamaan pergerakkan asas untuk model linear bagi dinamik helicopter diterbitkan dari persamaan jasad tegar Newton-Euler. Persamaan Newton-Euler diterbitkan dari enam darjah kebebasan jasad tegar yang terdiri dari tiga sejajar (sepanjang tiga paksi tubuh) dan tiga putaran (pada paksi yang sama) pada helikopter. Persamaan ini diaplikasikan untuk mendapatkan model state space helikopter tersebut. Data input asas dari dua buah helikopter yang sedia ada digunakan dalam tesis ini untuk mensimulasikan keputusannya. Input data model helikopter DRA (RAE) Research Puma, SA330 dan R-50 Yamaha telah digunakan dalam projek ini. Perbezaan utama antara kedua-dua helikopter ini adalah bar pengimbang yang juga boleh dianggap sebagai rotor sekunder, yang berada pada aci rotor di atas rotor utama, melalui engsel tertatih tatih tak terkawal. Oleh itu, di dalam tesis ini juga kesan bar pengimbang juga siasat. Keputusan disimulasikan dengan menggunakan program MATLAB Simulink. Dalam simulasi ini, bentuk output dari helikopter diamati dan dianalisa.
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This thesis contains the research regarding on the stability of flight simulation of helicopter and detailed procedure of how to construct a basic mathematical model that represents general longitudinal helicopter flight dynamics. The method in studying the helicopter stability is focused on the state space model structure of the helicopter model. The procedure will beginning from understanding the idea of how a helicopter is been hovered by using several sets of control inputs. The control inputs are collective angle (θo), longitudinal cyclic angle (θls ), and lateral cyclic angle (θlc) which are control inputs for the main rotor, and tail rotor collective angle(θoT) , which is for the tail rotor. The outputs of the helicopter are recognized based on the helicopter model. The basic equations of motion for linear model of helicopter dynamics are derived from the Newton-Euler equations for a rigid body. The Newton-Euler equations is derived from the six rigid body degrees of freedom which are three translational (along the three body axes) and three rotational (about the same axes) of the helicopter . These equations are being applied to obtain the state space model of the helicopter. Besides that the additional stabilizer bar dynamics also being applied for certain helicopter model. The basic inputs data from two existing helicopter are used in this thesis in order to simulate the result. The DRA (RAE) Research Puma, SA330 and Yamaha R-50 helicopter model input data have been used in this project. The major difference between these two helicopters is the stabilizer bar that also can be regarded as a secondary rotor, attached to the rotor shaft above the main rotor, through an unrestrained teetering hinge. Therefore, in this thesis also the effect of stabilizer bar also studied. Lastly, the results are simulated using MATLAB Simulink program. In this simulation, the shape of the outputs of the helicopter is observed and analyzed.
Stability system for helicopter using matlab Simulink_Saiful Fadzil Bin Mohd Hamir_E3_2011_875004018_00003089574_NI