Abstract
The article examines the influence of the configuration of a hypersonic flight vehicle with a hori-zontal cruise flight section on the maximum flight range under the conditions of limiting dimen-sions. The ram jet and the solid propellant rocket engine were chosen as the cruise engine, and re-spective calculations were performed. The hypersonic flight vehicle was configured based on the design patented in the Russian Federation, under the condition of launch using the 3S14 universal launcher. Dependencies of the maximum range on the ratio between the launch mass to the payload were analysed. The mass efficiency indicator for a two-stage ballistic missile was chosen as a crite-rion for a comparison with other available alternatives.
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