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This study mainly deals with the design and structural analysis of missile motor body. This is to design three missile motor bodies with different dimensions and analyze them by applying three different materials for the corresponding loads, which act when two types of propellants are used and find the material with less deformation and better load bearing capability. The main aim of this study is structural analysis performed on the antitank guided missile MILAN 2T motor body, which was designed in NX for varying dimensions and thickness of three motor body designs and analyzed in the NX simulation by applying the loads imposed by two different propellants, namely double base and triple base propellants.
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Pomiary Automatyka Robotyka
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The advent of the modern cruise missile, with less radar detection and the ability to fly at low altitudes in sub sonic speeds with precise navigation, placed an extensive liability on all weapon systems in defence.The purpose of this project is to present a preliminary analysis and design of a cruise missile which fulfill the mission requirements. This design project comprises the concept exploration and development stages of the full design process. While designing we should take dimensions as per our requirements and should have tolerances to design parts. CATIA V5 is used as design tool. The inlet temperature, pressure, density and altitude are the parameters to analyze the flow properties. The analysis done in the ANSYS WORKBENCH 14.5.This paper discuss the flow of the designed model. In this paper we are going to discuss key aspects in aerodynamics of wing and fin.
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A Missile is a self-propelled guided weapon system that travels through air or space. A powered, guided munitions that travels through the air or space is known as a missile (or guided missile). The Missile is defined as a space transversing unmanned vehicle that contains the means for controlling its flight path. The aerodynamic characteristics of a missile components such as body, wing and tail are calculated by using analytical methods to predict the drag and the normal forces of the missile. The total drag of the body is computed by using the parasite drag, wave drag, skin friction drag and base drag. The wing surface normal force coefficient (C N) Wing is a function of Mach number, local angle of attack, aspect ratio, and the wing surface plan form area (C N) Wing , based on the missile reference area, decreases with increasing supersonic Mach number and increases with angle of attack and the wing surface area. When the wing surface area is reduced the total weight of the missile and drag are reduced thereby increasing the lift and achieve excessive stability.
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The order of this article is as follows. Firstly, we will address the issue of the ballistic missiles because their properties obviously reflect on the missile defence – thus we will define and describe the threat. Secondly, we will discuss the missile defence as such – specifically pointing out at its inherent limitations. And finally, we will shortly present the missile defence arsenals of the world with particular reference to the United States.
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International Journal of Engineering Research and Technology (IJERT)
https://www.ijert.org/aerodynamic-configuration-design-of-a-missile https://www.ijert.org/research/aerodynamic-configuration-design-of-a-missile-IJERTV4IS030060.pdf In this proposed paper the aerodynamic characteristics of various sections such as body, wing and tail of an anti-aircraft missile were computed using analytical methods. Generally predicting the aerodynamic characteristics is mandatory in case of performance analysis. Drag characterization is carried out at different Mach number varying from subsonic to supersonic for different altitudes. It is found that at 15km the drag is reduced to about 23% of that on 5km while considering supersonic Mach numbers. To predict the normal force coefficient values linear wing theory, Newtonian impact theory and slender wing theory is used. Normal force coefficients were calculated at different angle of attacks (1, 5 & 10). This paper also includes predicting of centre of pressure and sizing the tail, which helps in maintaining the missile at static neutral stability. The predicted aerodynamic characteristics were in good agreement with the results in the literature.
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