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CFD investigation of thrust vectoring in rocket nozzle via jet tab / Adel Mamdouh Abdelaziz Mohamed ; Supervised Essam Eldin Khalil , Gamal Elhariri , Eslam Said Abdelghany

By: Contributor(s): Material type: TextTextLanguage: English Publication details: Cairo : Adel Mamdouh Abdelaziz Mohamed , 2018Description: 165 P. : charts , facsimiles ; 30cmOther title:
  • دراسه عدديه لانحراف الدفع فى فوهه صاروخ عن طريق عائق نفاث [Added title page title]
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Dissertation note: Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Mechanical Power Engineering Summary: Thrust Vector Control is a method used to change a flight path or trajectory of a missile by using mechanical systems or secondary injection systems. Jet tab is a one type of mechanical systems. This thesis presents a numerical investigation of the effects of obstacle on a maneuverability of missile. Three nozzle shadow area (10% , 20% and 30%) and obstacle angles changing from 70{u00B0} to 110{u00B0} by a step of 20{u00B0} are investigated and with a variable of obstacle-nozzle gap ratio (0%, 1%,3% and 5%). All cases all have the same initial conditions. Inserting a tab as an obstacle in a supersonic stream generates an oblique shock wave upstream and a high-pressure recirculation zone below the wave. The supersonic flow downstream the oblique shock wave shapes the recirculation zone in a form of a liquid wedge between the separation point and the top of the tab profile. The results ensure that the highest side force to thrust losses ratio at minimum obstacle angle 70{u00B0}, highest nozzle shadow area 30% and without obstacle-nozzle gap ratio
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Thesis Thesis قاعة الرسائل الجامعية - الدور الاول المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.11.M.Sc.2018.Ad.C (Browse shelf(Opens below)) Not for loan 01010110076438000
CD - Rom CD - Rom مخـــزن الرســائل الجـــامعية - البدروم المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.11.M.Sc.2018.Ad.C (Browse shelf(Opens below)) 76438.CD Not for loan 01020110076438000

Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Mechanical Power Engineering

Thrust Vector Control is a method used to change a flight path or trajectory of a missile by using mechanical systems or secondary injection systems. Jet tab is a one type of mechanical systems. This thesis presents a numerical investigation of the effects of obstacle on a maneuverability of missile. Three nozzle shadow area (10% , 20% and 30%) and obstacle angles changing from 70{u00B0} to 110{u00B0} by a step of 20{u00B0} are investigated and with a variable of obstacle-nozzle gap ratio (0%, 1%,3% and 5%). All cases all have the same initial conditions. Inserting a tab as an obstacle in a supersonic stream generates an oblique shock wave upstream and a high-pressure recirculation zone below the wave. The supersonic flow downstream the oblique shock wave shapes the recirculation zone in a form of a liquid wedge between the separation point and the top of the tab profile. The results ensure that the highest side force to thrust losses ratio at minimum obstacle angle 70{u00B0}, highest nozzle shadow area 30% and without obstacle-nozzle gap ratio

Issued also as CD

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