TURBOJET NACELLE WITH SLIDING FRONT COWL Russian patent published in 2014 - IPC B64D29/08 

FIELD: aircraft engineering.

SUBSTANCE: nacelle 1 comprises air intake 4 to direct airflow to turbojet blower and mid structure 5 to cover said blower. Air intake is secured to mid structure 5 to make smooth aerodynamic lines and comprises outer panel 40 integrated with air intake leading edge 4a to cover mid section outer structure portion. Lengthwise outer panel can shift between working position whereat outer panel ensures smoothness of nacelle outer aerodynamic lines and servicing position whereat its is spaced from mid section outer structure for air intake leading edge is spaced from air intake inner panel. Outer panel 40 is connected with guides including rails 15 and sliders 16.

EFFECT: reduced weight, easier servicing.

15 cl, 5 dwg