On the development computer, code for determinig the root of equation for transient flight analysis
This thesis presents the governing equation of flight motions which can be used to describe the flight behavior of any type flying vehicles consist of 12 equations described 12 state – space variables involving the aircraft position and aircraft aptitude with respect to the inertial coordinate sy...
محفوظ في:
| المؤلف الرئيسي: | |
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| التنسيق: | أطروحة |
| اللغة: | English English English |
| منشور في: |
2013
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| الموضوعات: | |
| الوصول للمادة أونلاين: | http://eprints.uthm.edu.my/1991/1/24p%20MUWFIK%20FAIDI%20KHAIRE%20ELAROSI.pdf http://eprints.uthm.edu.my/1991/2/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20COPYRIGHT%20DECLARATION.pdf http://eprints.uthm.edu.my/1991/3/MUWFIK%20FAIDI%20KHAIRE%20ELAROSI%20WATERMARK.pdf |
| الوسوم: |
إضافة وسم
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| الملخص: | This thesis presents the governing equation of flight motions which can be used to
describe the flight behavior of any type flying vehicles consist of 12 equations
described 12 state – space variables involving the aircraft position and aircraft
aptitude with respect to the inertial coordinate system and also with respect to their
axis body system had been used. These twelve equations are coupling each to others
and in the forms highly non linear equation; the numerical approach is required for
solving such system equation. The coefficient of system equation can be said as a
result of the combination between aircraft’s mass and inertia, aircraft geometry
properties and also their aircraft aerodynamics derivatives. The present work is
focused in the development computer code which allows in manner of determining
the root of equation of the 12 equations which described the flight behavior for
particular airplane. Through determining the root of equation one will able to carry
out a non linear transient analysis such as aircraft at landing approaches gust
response and pilot initiated maneuvers. |
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