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Modelling of an Impact Resistant Navigation System for Gun Projectiles Based on Low Cost Mems Sensors = = Dusuk Maliyetli Mems Sensorlu Top Mermileri Icin Darbe Dayanimli Navigasyon Sistemi Modellemesi.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Modelling of an Impact Resistant Navigation System for Gun Projectiles Based on Low Cost Mems Sensors =/
其他題名:	Dusuk Maliyetli Mems Sensorlu Top Mermileri Icin Darbe Dayanimli Navigasyon Sistemi Modellemesi.
作者:	Inel, Selahattin Can.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2021,
面頁冊數:	127 p.
附註:	Source: Masters Abstracts International, Volume: 83-11.
Contained By:	Masters Abstracts International83-11.
標題:	Aircraft. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29079234
ISBN:	9798426884397

Modelling of an Impact Resistant Navigation System for Gun Projectiles Based on Low Cost Mems Sensors = = Dusuk Maliyetli Mems Sensorlu Top Mermileri Icin Darbe Dayanimli Navigasyon Sistemi Modellemesi.
Inel, Selahattin Can.

Modelling of an Impact Resistant Navigation System for Gun Projectiles Based on Low Cost Mems Sensors =Dusuk Maliyetli Mems Sensorlu Top Mermileri Icin Darbe Dayanimli Navigasyon Sistemi Modellemesi. - Ann Arbor : ProQuest Dissertations & Theses, 2021 - 127 p.

Source: Masters Abstracts International, Volume: 83-11.

Thesis (M.Sc.)--Izmir Institute of Technology (Turkey), 2021.

This item must not be sold to any third party vendors.

In this thesis, guided projectiles are studied in three aspects: a navigation system design, CFD analysis of a guided projectile for low launch velocities and durability of electronic components under extreme firing conditions. During the thesis progress, MATLAB & Simulink, FlightGear and Ansys-Fluent software are used for simulations and 3D object modelling. Basic Finner Reference Projectile is chosen as a test bed for navigation simulation, since the dimensions and some of the flight parameters are already available as open source. However, a missile state-space model which is given by Raytheon is used for navigation simulations instead of a guided projectile model due to inaccessibility of some critical aerodynamic parameters for 6-DoF model.Navigation system is designed using preset guidance methodology which uses built-in inertial sensors to correct the course for given targets which location are loaded prior to launching. CFD calculations of the Basic Finner Reference Projectile are conducted for low launching velocities to light the way for the aerodynamic conditions of non-explosive firing equipments such as catapults and airguns. Furthermore, the durability of common electronic components under extreme projectile firing conditions are visualized up to 20,000g and the functionality of regular off the shelf microcontrollers and sensors are tested using Hopkinson Bar test equipment. A navigation model simulation of a guided munition is created combining FlightGear and MATLAB & Simulink satisfying the given different criteria for pole placement method, LQR controller and observer design.

ISBN: 9798426884397Subjects--Topical Terms:

832698
Aircraft.

Modelling of an Impact Resistant Navigation System for Gun Projectiles Based on Low Cost Mems Sensors = = Dusuk Maliyetli Mems Sensorlu Top Mermileri Icin Darbe Dayanimli Navigasyon Sistemi Modellemesi.
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245 1 0 $a Modelling of an Impact Resistant Navigation System for Gun Projectiles Based on Low Cost Mems Sensors = $b Dusuk Maliyetli Mems Sensorlu Top Mermileri Icin Darbe Dayanimli Navigasyon Sistemi Modellemesi.
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300 $a 127 p.
500 $a Source: Masters Abstracts International, Volume: 83-11.
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520 $a In this thesis, guided projectiles are studied in three aspects: a navigation system design, CFD analysis of a guided projectile for low launch velocities and durability of electronic components under extreme firing conditions. During the thesis progress, MATLAB & Simulink, FlightGear and Ansys-Fluent software are used for simulations and 3D object modelling. Basic Finner Reference Projectile is chosen as a test bed for navigation simulation, since the dimensions and some of the flight parameters are already available as open source. However, a missile state-space model which is given by Raytheon is used for navigation simulations instead of a guided projectile model due to inaccessibility of some critical aerodynamic parameters for 6-DoF model.Navigation system is designed using preset guidance methodology which uses built-in inertial sensors to correct the course for given targets which location are loaded prior to launching. CFD calculations of the Basic Finner Reference Projectile are conducted for low launching velocities to light the way for the aerodynamic conditions of non-explosive firing equipments such as catapults and airguns. Furthermore, the durability of common electronic components under extreme projectile firing conditions are visualized up to 20,000g and the functionality of regular off the shelf microcontrollers and sensors are tested using Hopkinson Bar test equipment. A navigation model simulation of a guided munition is created combining FlightGear and MATLAB & Simulink satisfying the given different criteria for pole placement method, LQR controller and observer design.
520 $a Bu tez calismasi; gudumlu bir top mermisi icin navigasyon sistemi tasarimi, dusuk firlatma hizlarinda CFD analizi ve elektronik devre elemanlarinin siddetli atesleme kosullari altindaki dayanimlari olmak olmak uzere uc ana baslik altinda toplanmistir. Tez calismalari suresince simulasyon ve 3 boyutlu modelleme icin MATLAB & Simulink, FlightGear ve Ansys Fluent yazilimlari kullanilmistir. Temel Kanatcik Referans Mermisi, olculerinin ve bazi ucus parametrelerinin acik kaynak olarak verilmis olmasi nedeniyle navigasyon simulasyonu icin test numunesi olarak secilmistir. Ancak son derece gelismis bir muhimmat olan gudumlu top mermilerinin 6 serbestlik dereceli model kapsaminda kullanilmasi gerekli olan bazi kritik aerodinamik parametrelere erisim imkani olmamasi nedeniyle ucus parametreleri gudumlu top mermisine yakin olan Raytheon firmasi tarafindan acik kaynak olarak sunulan bir gudumlu fuzenin durum-uzay modeli, gudumlu top mermisi modeli yerine simulasyon icin kullanilmistir.Navigasyon sistemi, atesleme oncesinde mevkisi yuklenen hedeflere karsi rota duzeltmek amaciyla dahili ataletsel sensorlerin kullanildigi onceden ayarlanmis gudum metodolojisi kullanilarak tasarlanmistir. Temel Kanatcik Referans Mermisinin CFD hesaplamalari, mancinik ve havali tufek gibi patlayici olmayan atesleme ekipmanlarinin aerodinamik kosullarina isik tutmasi amaciyla dusuk firlatma hizlari icin yapildi. Ayrica, elektronik devre elemanlarinin asiri mermi atesleme kosullari altinda dayanikliligi Hopkinson Bar test ekipmani kullanilarak 20.000g'ye kadar gorsellestirildi ve mikrodenetleyicilerin ve sensorlerin islevselligi test edildi. Gudumlu bir muhimmat icin FlightGear ve MATLAB & Simulink'i birlestirerek, direk yerlestirme yontemi, LQR kontrolor ve gozlemci tasarimi icin verilen farkli kriterleri karsilayan bir navigasyon model simulasyonu olusturuldu.
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