This paper pays attention on the specific problems of the suborbital flight comfort / safety ensuring. It shows that the physical limitations in the boost and descent flight phases form the mutual contradictory requirements on the launcher and re-entry vehicle arrangement. The algorithm of construction of permissible ranges of parameters determining a shape of such vehicles and their critical flight regimes is offered. The technique is demonstrated as an application to analysis of the "Angara-1" launcher availability for space tourism purposes.
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