Determination of losses in an air system of liquid fuel missile

مقدم أطروحة جامعية

Abbas, Muhammad

الجامعة

الجامعة التكنولوجية

الكلية

-

القسم الأكاديمي

قسم الهندسة الكهروميكانيكية

دولة الجامعة

العراق

الدرجة العلمية

ماجستير

تاريخ الدرجة العلمية

2004

الملخص الإنجليزي

The air system in missile forms one of the most important parts of Fuel feeding system which is consist of iron ball opens to group of divided Pipes provided with different control valves and fittings ended to oxidizer and fuel tanks and servomotor units.

This research has been applied to air system of surface to surface missile to calculate the losses during (low of air through the above System.

The equations of flow of gases through pipes had been derived and arranged in suitable forms for numerical calculation.

The solution of the derived equations was obtained using Unite difference techniques.

The governing equations are approximated over small time steps and small increment distances.

The distribution of velocity inside the system were determined by a- Constant friction factor and Stanton number b- Assumed friction factor as function of Reynolds number and Stanton number as function of Reynolds and Prandtl ! numbers.

The obtained results give good agreement with experimental results in existing literature.

The losses in bends 45°, 60° and 90" have been calculated and it was found those minimum losses in 45 bend.

The losses in elbow type 60° and 90° were determined and it was found those minimum losses in elbow 60 Three types of pipes were used through the calculation (20.9, 15.8 and 9.2) mm and it was found that the losses in (15.8) mm pipe is minimum and it is preferable from point of view of aerodynamic characteristics of missile.

التخصصات الرئيسية

الهندسة الميكانيكية

الموضوعات

• الديناميكا الهوائية
• الوقود السائل
• تدفق الهواء

• APA
• MLA
• AMA

لغة النص

الإنجليزية

نوع البيانات

رسائل جامعية

رقم السجل

BIM-305886