Modeling and analysis of 3d thrust vectoring nozzle to reduce heat signatures

Registration ID: IJNRD_186247

Published ID: IJNRD2301228

DOI: Click Here to Get

Dr NAGESH D , Samprutha A R , Meghashree M S

Heat signatures, Circular Nozzle, Elliptical Nozzle, Exit Temperature, Angles of tilt, ANSYS Fluent

In today’s time when whole world is looking for 5th generation combat aircraft, it has become necessary for us to go with the flow to save our country. With upcoming aircraft projects of HAL such as FGFA and AMCA, it is soul need to develop our own stealth technology to keep our upcoming aircrafts comparable to any other next-generation aircraft. Stealth technology is a sub-discipline of military tactics and passive electronic countermeasures, which cover a range of techniques used with personnel, aircraft, ships, submarines, missiles and satellites to make them less visible (ideally invisible) to radar, infrared, sonar and other detection methods. An aircraft exhaust nozzle contributes a significant heat signature. One means to reduce heat signature is to have a non-circular tail pipe (a slit shape) to minimize the exhaust cross-sectional volume and maximize the mixing of hot exhaust with cool ambient air. Thrust vectoring is the ability of an aircraft, rocket, or other vehicle to manipulate the direction of the thrust from its engine(s) or motor in order to control the attitude or angular velocity of the vehicle. In the extreme, deflection of the jets in yaw, pitch and roll creates desired forces and moments enabling complete directional control of the aircraft flight path without the implementation of the conventional aerodynamic flight controls. 3D thrust vectoring enables the aircraft to maneuver in all the three axis. Rectangular cross-section nozzle significantly reduces heat signatures of the aircraft but in turn it also reduces the performance of the aircraft and reduces the efficiency of the engine. These issues can be overcome by using a nozzle which can change its cross-section from circular to non-circular or near to it. This will enable the pilot to change the cross-section of the nozzle as per requirement depending on the war scenario. This is the first aircraft nozzle ever built which can change its cross-section to reduce heat signatures and can provide 3D thrust vectoring at the same time. This work includes the modeling of various shapes of the nozzles such as circular and elliptic at various vectoring angles and comparing the results with the conventional shape. The temperatures obtained at the exit of the elliptic nozzle is less when compared to the other types and hence heat signatures generated by this nozzle is comparatively low.

Published Paper   E-Certificate

Dr NAGESH D, Samprutha A R, & Meghashree M S (January-2023). Modeling and analysis of 3d thrust vectoring nozzle to reduce heat signatures. INTERNATIONAL JOURNAL OF NOVEL RESEARCH AND DEVELOPMENT, 8(1), c211-c214. https://ijnrd.org/papers/IJNRD2301228.pdf

Volume 8 Issue 1, January-2023

Pages : c211-c214

Paper Reg. ID: IJNRD_186247

Published Paper Id: IJNRD2301228

Downloads: 000122015

Research Area: Science & Technology

Country: Chickaballapur, karnataka, India

Published Paper PDF: https://ijnrd.org/papers/IJNRD2301228.pdf

Published Paper URL: https://ijnrd.org/viewpaperforall?paper=IJNRD2301228

Journal Name: INTERNATIONAL JOURNAL OF NOVEL RESEARCH AND DEVELOPMENT(IJNRD)

ISSN: 2456-4184 | IMPACT FACTOR: 8.76 Calculated By Google Scholar | ESTD YEAR: 2016

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