FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircrafts. Aircraft (1) includes fuselage (2) with engine (8a). Maximum fuselage (2) width is defined in engine (8a) area. Front fuselage fairing and rear fuselage fairing are partially closing engine (8a) and are spaced apart in direction across engine (8a) lengthwise axis, by means of a predetermined fairing displacement, for dynamic air intake (9) determination, through which sucked air flow is supplied to said at least one engine (8a) using air as oxidant in operation.
EFFECT: invention improves aircraft engine protection.
15 cl, 16 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIRCRAFT GAS TURBINE ENGINE WING PYLON FAIRING | 2007 |
|
RU2391260C1 |
| SUPERSONIC AIRCRAFT JET ENGINE | 2007 |
|
RU2499739C2 |
| SUPERSONIC AIRCRAFT JET ENGINE | 2007 |
|
RU2454354C2 |
| UNMANNED JET-HELICOPTER | 2018 |
|
RU2699513C1 |
| NACELLE-MOUNTED GAS-TURBINE ENGINE AIR INLET | 2010 |
|
RU2538350C2 |
| SUPERSONIC LOW-VISIBILITY AIRCRAFT-HELICOPTER | 2018 |
|
RU2692742C1 |
| AIR INTAKE FOR TURBOJET ENGINE NACELLE | 2020 |
|
RU2806229C2 |
| LEADING EDGE STRUCTURE, PARTICULARLY, TO AIRCRAFT ENGINE NACELLE | 2011 |
|
RU2577975C2 |
| AIR MISSILE SYSTEM WITH AN UNMANNED PERCUSSIVE AIRCRAFT HELICOPTER | 2018 |
|
RU2710317C1 |
| FAN BODY SUPPORT FRAME MOUNTED AT NACELLE ATTACHMENT PYLON AND AIR INTAKE | 2008 |
|
RU2468963C2 |
