FIELD: transport.
SUBSTANCE: invention relates to vertical take-off and landing (VTOL). The VTOL incorporates airframe (1) with wing (7) attached thereto accommodating turbojet two-phase engine (15). The engine behind-the-compressor space limited by the compressor casing is divided by the combustion chamber outer wall into two separate circular spaces, an inner and outer one. On both airframe sides, two arch-like cross-section wings (5, 6) are attached thereto with their upward convex and downward concave surfaces. The airframe lower part houses a ramjet (22) with lateral intake channels (25, 26), the channels lengthwise axes being tangentially directed towards the wing concave surface. The outlet channels are furnished with flap valves to open or shut off the outlet channels.
EFFECT: lower fuel consumption in vertical take-off and landing.
5 cl, 17 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| JET-PROPELLED AIRCRAFT | 2006 |
|
RU2323132C2 |
| MULTI-PURPOSE VERTICAL TAKEOFF AND LANDING FLYING VEHICLE | 2004 |
|
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|
RU2387582C2 |
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|
RU2349505C1 |
| JET ENGINE | 2006 |
|
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|
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|
RU2711760C2 |
| COMBAT AIRCRAFT COMPLEX WITH UNMANNED AERIAL VEHICLE | 2023 |
|
RU2816404C1 |
| VTOL AIRCRAFT | 2012 |
|
RU2490173C1 |
| AMPHIBIOUS AIRCRAFT | 2004 |
|
RU2281228C1 |
