On the Influence of Physical Limits on the Range of a Hypersonic Flight Vehicle

In this article the authors examine specific features of a flight vehicle equipped with a ramjet engine, taking into consideration a series of principal restrictions. When the engine is in operation, certain restrictions are applied so that the pressure in the combustion chamber is not below the level required for normal evaporation of the fuel and not higher than the limit values, exceeding which may lead to combustion pulsation and explosion. The flight vehicle should not enter altitudes with low air density where the ascensional power and the quantity of the intake oxidizer in the combustion chamber are not sufficient for a stable controlled flight. As the flight vehicle moves at hypersonic speeds, the aerodynamic heating of the body is taken into account. Taking into account the above-mentioned restrictions, the full flight procedure is evaluated, and the weight analysis is performed for a flight vehicle featuring the design protected by a patent of the Russian Federation and launched from a universal launcher 3S14. The maximum range trajectory is calculated for a synthesized concept of an ideal flight vehicle, and conclusions about the possible range of applications are made.

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