Simulation of aircraft control using bondoraph technique and matlab stimulant software

Dissertant

al-Shammari, Usamah Sattar Kazim

University

University of Technology

Faculty

-

Department

Department of Electromechanical Engineering

University Country

Iraq

Degree

Master

Degree Date

2007

English Abstract

The present work presents a study and analysis of aircraft dynamics.

The equations of motion of the aircraft are covered both, forces and moments equations by using Newton's second law with the assumption that each equation is of a rigid body.

The matrix for the vectors and differentia! equations for each force and moment applied on the aircraft were found.

When the six equations for the aircraft are completed and using the assumptions for longitudinal and lateral motion, the six equations were classified in three equations for the longitudinal motion and three equations for the lateral motion.

The matrix for longitudinal and lateral motion were then found.

These equations for longitudinal and lateral were transferred to Laplas form to study the control of the aircraft.

Analysis was done using the modern analysis method in mechanical, hydraulic, chemical and electrical systems as applied by new softwares i.

e.

(symbols 2000 and CAMP-G).

in order to use one of the new softwares, the dynamics of the aircraft need to be modeled.

This is a achieved by modeling of all mechanical system, taking the effect of all variables including flow and power variables. These equations are used for the bond pad area [CAMP-G] software to produce the Bond Graph.

Symbols 2000, is used as a software to plot forces and moments affecting the aircraft in one graph. To complete the analysis Symbols 2000 may be connected to Matlab program by use Matlab / Simulink Aerospace Block set, by input of the six equations of motion of aircraft in to this Software in both longitudinal and lateral motion.

The data for L39 and F14 aircrafts were used to be analyzed by this software Matlab gave as the results including the response and performance in both body and inertia axes for L39 and G-Force, angle of attack for F14 airerafts to its control and performance by using Simulink / Aerospace Blocks technique.

Main Subjects

Mechanical Engineering

Topics

• Airplanes
• Computing
• Mathematical models
• Control systems

• APA
• MLA
• AMA

Language

English

Data Type

Arab Theses

Record ID

BIM-305511