FIELD: transport.
SUBSTANCE: proposed device comprises multiple IR radiation elements 13, 13a, 13b arranged inside said leading edge 1 of aircraft air intake 3, radiator electric power supply 17 and power supply control means 27. Radiators are made of ceramics and feature the following parameters: radiation power-to-weight ratio approximating to 500 W per 100 g, radiation capacity approximating to 97% at 800°C making 1.5-10 mcm, radiation power surface density exceeding 70 kW/m2, and efficiency exceeding 95%.
EFFECT: ruled out removal of hot air from engine, compact design, ease of replacement, longer life, high radiation capacity, low thermal inertia.
16 cl, 13 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD FOR PROTECTING SURFACES OF AIRCRAFT AIR INTAKE FROM ICING | 2020 |
|
RU2753977C1 |
| AIRCRAFT DE-ICING SYSTEM AND AIRCRAFT WITH SUCH SYSTEM | 2011 |
|
RU2529927C1 |
| AIRCRAFT LEADING EDGE | 2007 |
|
RU2467927C2 |
| AIRCRAFT SOUND ABSORBING COATING INCLUDING ANTI-ICING SYSTEM EXPLOITING JOULE EFFECT | 2007 |
|
RU2445238C2 |
| METHOD FOR PREVENTING ACING OF AIRCRAFT WINGS WITH THE USE OF LASER ANTI-ICING SYSTEM | 2017 |
|
RU2671069C1 |
| LEADING EDGE STRUCTURE, PARTICULARLY, TO AIRCRAFT ENGINE NACELLE | 2011 |
|
RU2577975C2 |
| DEVICE AND METHOD FOR ELIMINATION OF ICING AND/OR PREVENTING ICE FORMATION AND PROFILE BODY AND AIRCRAFT WITH SAID DEVICE | 2014 |
|
RU2602266C2 |
| AIRCRAFT ENGINE NACELLE ANTI-ICING SYSTEM WITH RESISTIVE LAYER | 2006 |
|
RU2411161C2 |
| AIRCRAFT TURBOJET SUSPENSION ASSEMBLY | 2010 |
|
RU2518991C2 |
| IMPROVED DESIGN OF THE INPUT DEVICE | 2018 |
|
RU2727820C2 |
