FIELD: transport.
SUBSTANCE: method of adjusting mouth area and position of compression shocks by simultaneous turn of the front adjustable panel and rear adjustable panel. Axis of said front panel rotation is aligned with interaction of first and second steps of one of arrow-shape wedge, not perpendicular incident flow. Axis of said rear panel rotation is located in zone of rear edge of rear adjustable panel and is directed subject to location of the point of intersection with front panel rotational axis. In turn of both said panels, their side edges displace relative to channel shaped side surfaces with making clearances there between.
EFFECT: improved gas dynamic characteristics, stealth properties.
4 cl, 8 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SUPERSONIC CONTROLLED AIR INTAKE | 2011 |
|
RU2472956C2 |
| STEALTH AIR INTAKE OF SUPERSONIC AIRCRAFT | 2022 |
|
RU2801718C1 |
| ASYMMETRICAL AIR-SCOOP FOR THREE FLOW ENGINE OF FASTER-THAN-SOUND AIRCRAFT | 2018 |
|
RU2670664C9 |
| SUPERSONIC INTAKE | 2007 |
|
RU2343297C1 |
| SUPERSONIC AIR INTAKE (VERSIONS) | 2001 |
|
RU2200240C1 |
| SUPERSONIC UNREGULATED AIR INTAKE | 2021 |
|
RU2779515C1 |
| VARIABLE GEOMETRY AIR INTAKE FOR SUPERSONIC PASSENGER AIRCRAFT | 2021 |
|
RU2766238C1 |
| AIR INTAKE WITH VARIABLE GEOMETRY FOR SUPERSONIC AIRCRAFT (VERSIONS) | 2007 |
|
RU2353550C1 |
| JET ENGINE AIR INTAKE | 2024 |
|
RU2823410C1 |
| SELF-ADJUSTABLE AIR INTAKE | 1997 |
|
RU2171211C2 |
