Abstract
A helicopter is propelled by a jet‐driven rotor 15 and a pair of turbine‐driven propellers 12 mounted on fixed stub wings 10, each rotor blade consisting of an inboard portion 20 mounted on the hub by a flapping and collective pitch‐adjusting hinge 22 and provided with a jet nozzle 24 at its outer end, together with an outboard portion 21 connected to the portion 20 by a cyclic pitch adjusting hinge 23. This arrangement enables the outboard blade portion 21, which contributes most of the lift, to be designed solely in accordance with aerodynamic considerations. Rods for controlling the outlet area of the nozzle 24 and for cyclic pitch adjustment of the blade portion 21 pass through the inboard portion 20. Gases for the propulsion units are supplied from a pair of gas turbines 14 through ducts 16, 18 provided with valves 17, 19 enabling the relative proportions supplied to the main rotor and propellers to be varied as desired.
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