FIELD: aviation.
SUBSTANCE: supersonic inlet device for jet engine of aircraft contains inclined element with front edges; working front edges on inclined element, which comprise panels made with possibility of rotation with provision of extension of working front edges from front edges of inclined element and having retracted position, in which front edges of panels and leading edges of inclined element are aligned with shock wave (36) at Mach number for design mode. There is an extended position, in which working front edges of panels are aligned with shock wave at Mach number for non-standard mode. Method is characterized by using an input device.
EFFECT: group of inventions is aimed at improvement of operating characteristics of input device.
13 cl, 11 dwg
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