Design improvement of a disposable nozzle holder part used in missile systems through topology optimization

One of the most important considerations in the aviation industry is low-weight design. This is also an issue that is taken into consideration for missile/rocket systems. Missile/rocket systems are the most effective weapon systems used in today's defense industry. In particular, long-range missile systems are important force multipliers for countries. Missiles/rockets can be classified as solid fuel, liquid fuel, hybrid, ramjet, scramjet according to their propulsion systems. Ramjet jet engine, which is the subject of this study, is a type of air-breathing jet engine with air ducts to compress the oncoming air. In this study, it is aimed to reduce the weight of the disposable nozzle holder part used in the ramjet missile system by topology optimization. The nozzle system is the opening through which the high temperature and pressure gases formed in the combustion chamber are discharged. In this way, impulse is created. There are numerous studies on fixed nozzle designs in the literature, but studies on disposable nozzle designs are limited. Before starting with the design study, the loads on the nozzle system due to the pressure resulting from the combustion of the fuel in the missile combustion chamber were calculated, disposable nozzle designs and operating principles used in similar systems were examined and a suitable holder system was designed. The design of the retainer system was modeled in 3D on a computer and analyzed using ANSYS software. In the topology optimization study, the holder part system was optimized with a 30% mass reduction input. The designs obtained as a result of the analysis were manufactured, hydrostatic pressure tests were performed and design verifications were made.