DEVELOPMENT OF SIMULATION PLATFORM AND STABILITY ANALYSIS OF AIRCRAFT WITH SYSTEM
Aircraft simulator has been develop since 1910 named Sanders Trainer, which is a replica of an aircraft on the ground that moves according to wind speed and direction, and control surface deflection. As computation technology began to develop, computing time for calculating solution of differential...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/34289 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | Aircraft simulator has been develop since 1910 named Sanders Trainer, which is a replica of an aircraft on the ground that moves according to wind speed and direction, and control surface deflection. As computation technology began to develop, computing time for calculating solution of differential equations become much faster. It affected aircraft simulator development as well. So there is so many flight simulator softwares right now. Flight Physics Research Group ITB is developing two types of aircraft simulator that played a role as engineering simulator. The first type is utilizing X-Plane as the main software to calculate aircraft dynamics as well as failure and environment effect. The second one is utilizing Matlab and Simulink as the main software. In this research, the writer focused on the certain part of the aircraft simulator. Those are aircraft mathematical model that accommodate failure and environment effect on its dynamics, observer station, and instructor station. Those components then integrated and the aircraft motion visualized in X-Plane. This simulation platform had been tested by performing several flight scenarios by manipulating engine and control devices operation status and manipulating environment wind as well. Based on the simulation result, this simulation platform is worked well. Moreover, this simulation platform can be used to analyze aircraft stability and its dynamic response either using ‘real-time’ simulation or using a linearized model. In this thesis, the aircraft model linearized to observe its dynamic characteristics. First, the open-loop system response was observed by looking at its time response, poles location, and damping ratio values. After that, the system is given a feedback to make it a closed-loop system and both open-loop and closed-loop system dynamic response and damping ratio are compared. |
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