TURBOJET NACELLE Russian patent published in 2014 - IPC B64D29/06 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, namely, to turbojet aircraft nacelle 1. Nacelle 1 comprises air intake section 4 to direct airflow to turbojet fan that has lengthwise outer panel 40 integrated with inlet edge 4a, mid section 5 surrounding said fan. Air intake section 4 is secured to mid section to ensure aerodynamic integrity. Besides, air intake section comprises inner panel 41 with noise absorbing jacket 53 secured on its lower downstream end 70 to upper upstream end 72 of mid section 5 to make with said mid section a fixed nacelle structure. Besides nacelle incorporates guides 15 to guide outer panel or panels 40 to allow its/their reciprocation relative to nacelle upstream end to open air intake section 4. Nacelle incorporates also stiffness elements 90, 100, 110, 120, 130, 140, 150 to take up mechanical loads at guide mean 15 at their deformation exceeding preset magnitude at opening of air intake section.

EFFECT: limited deformation of nacelle flap guides.

14 cl, 18 dwg