• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.3
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• pp.81-88
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• 2021

An airbreathing propulsion system of a subsonic cruise missile is mainly composed of a small gas turbine engine, air intake and vehicle's fuel tank. The propulsion system integration work started from engine acceptance test is finally closed by ground functional test of the missile's propulsion section, after some modifications of engine's sub-components, development of engine-related onboard systems, interface analyses, and tests. The whole process and stepwise technologies of this system integration work are described herein.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.479-488
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• 2019

A cruise missile uses wings and a jet engine like an airplane to reach the target after cruising a considerable distance. An integrated design of a cruise missile based on radar cross section (RCS) reduction and enhanced aerodynamic performance is indispensable, since it must be able to fly long-distance at subsonic speed without being detected by enemy radar. In this study, we designed a Taurus-type cruise missile and analyzed its RCS and aerodynamic characteristics using the physical optics (PO) technique and the Navier-Stokes CFD code. As a result, we obtained the optimal shape of cruise missile with improved aerodynamic performance and reduced RCS.