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Paraffin-based ramjet missile preliminary design

  • Rogerio L.V. Cruz (Mechanical Engineering Department, University of Brasilia, Campus Darcy Ribeiro) ;
  • Carlos A.G. Veras (Mechanical Engineering Department, University of Brasilia, Campus Darcy Ribeiro) ;
  • Olexiy Shynkarenko (Department of Aerospace Engineering, University of Brasilia)
  • Received : 2023.02.15
  • Accepted : 2023.07.12
  • Published : 2023.07.25
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Abstract

This paper presents a basic methodology and a set of numerical tools for the preliminary design of solid-fueled ramjet missiles. An elementary code determines the baseline system configuration comprised of warhead, guidance-control, and propulsion masses and geometries from specific correlations found in the literature. Then, the system is refined with the help of external and internal ballistics codes. Equations of motion are solved for the flight's ascending, cruising, and descending stages and the internal ballistic set of equations designs the ramjet engine based on liquefying fuels. The combined tools sized the booster and the ramjet sustainer engines for a long-range missile, intended to transport 200 kg of payload for more than 300 km range flying near 14,000 m altitude at Mach 3.0. The refined system configuration had 600 mm in diameter and 8,500 mm in length with overall mass of 2,128 kg and 890 kg/m3 density. Ramjet engine propellant mass fraction was estimated as 74%. Increased missile range can be attained with paraffin-polyethylene blend burning at near constant regression rate through primary air mass flow rate control and lateral 2-D air intakes.

Keywords

Acknowledgement

The authors are grateful for the technical support of collaborators of the Chemical Propulsion Laboratory of the University of Brasilia. Also, this study was financed in part by the Coordenacao de Aperfeicoamento de Pessoal de Nivel Superior-Brasil (CAPES)-Finance Code 001.

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