A flying vehicle comprises an elongated airfoil having a first end and a second end defining a longitudinal axis, the first and second ends further defining an interior opening extending therebetween and terminating at an outlet port proximal the second end; a solid fuel engine includes a fuel combustion chamber proximal the first end of the airfoil; a first manifold is coupled to the fuel combustion chamber and configured to convey a pressurized gas generated by combustion of a solid fuel; wherein the interior opening conveys the pressurized gas from the first manifold to the outlet port proximal the second end and wherein the pressurized gas is exhausted at the outlet port substantially perpendicular to the longitudinal axis of the elongated airfoil, thereby producing thrust which imparts a rotational motion to the airfoil about a center of mass proximal to the first end, for thereby defining a rotor disk.
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