FIELD: aviation.
SUBSTANCE: invention relates to aircraft engineering, particularly, to vertical take-off and landing aircraft power plants. Power plant of vertical take-off and landing aircraft consists of vertically oriented and horizontally oriented engines. Circular combustion chamber of vertical-oriented engine is arranged in vertical position. Turbine shaft passes inside it. Turbine is arranged in vertical position under combustion chamber. Torque from turbine shaft to compressor is transmitted by reduction gear. Nozzle consists of two tapered interconnected static parts - one larger size, another smaller size located inside the first one with some gap, increasing towards the end. Nozzle is located in lower part of aircraft in vertical position. Horizontally oriented turbojet with variable thrust vector provides high speed of aircraft in horizontal direction.
EFFECT: higher manoeuvrability and stability of aircraft in both vertical and horizontal modes of flight.
2 cl, 2 dwg
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