Development of a comprehensive mathematical model of the dimensional and mass characteristics of a solid propellant missile

Heading: 
Space-Rocket Complexes
1Bondarenko, MO, 1Vorobei, MM
1Oles Honchar Dnipro National University, Dnipro, Ukraine
Space Sci. & Technol. 2025, 31 ;(6):003-013
https://doi.org/10.15407/knit2025.06.003
Publication Language: English
Abstract: 
This paper presents a modular mathematical model for preliminary assessment of the dimensional and mass characteristics of a tactical solid-propellant rocket. The model determines overall length and initial mass from key design parameters (propellant load, fill factor, maximum casing diameter) and structural/geometric constraints, and covers metallic, hybrid, and filament-wound composite casings as well as alternative igniter mounting options. Dimensional limits (notably overall length) produce a transcendental relation requiring iterative solution; the method incorporates input uncertainties and enables rapid comparison of multiple design configurations for preliminary optimization and early design decisions.
Keywords: Composite casing, Dimensional and mass characteristics, Igniter system, mathematical modeling, Preliminary missile design, Solid-propellant rocket motor, Structural optimization, Tactical missile
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