| 摘要 |
FIELD: aircraft manufacture. SUBSTANCE: proposed aircraft has fuselage, wing, horizontal and vertical tails and engine plant. Lower portion of fuselage behind planing step is raised at angle of 8 deg relative to level. Fuselage has hydrodynamic aspect ratio about 6.2 and form factor of merit of 0.021 for steady hydroplaning at preflight speeds and trim angles from 3 to 8 deg. Lower portion of fuselage is made in form of hermetic caisson having volume about 2.2 cu.m. Aircraft wing includes center-wing section and two outer panels, ailerons, extensible flaps and slats. Center portion of wing has leading- edge assemblies separated from wing and mounted on longitudinal axles of rotation; leading-edge assemblies may be turned in vertical plane relative to said axles through angles exceeding 90 deg relative to wing chord. Two turbofan engines at power of 1250 hp each are equipped with reversible tractor propellers which may be turned together with leading- edge assemblies of wing during their turn. Metal frames inscribed in wing contour are provided with rotational half-axles with whose help load- bearing frames are connected to bearing bushes fitted with ball bearings and mounted on ribs of center-wing section. Engine mount frames to which engines are connected are installed on load-bearing frames. Engine mount frames are provided with units with controllable locks used for connecting them to lower portion of wing in area of rear spar. Load- bearing frames are connected to strong ribs by means of controllable locks. Geometric sizes of swivel leading edges of wing are dictated by sizes of propeller diameter taking into account narrowing of propeller jets after plane of rotation at distance of 1/2 of propeller diameter. EFFECT: improved service properties of aircraft. 9 cl, 29 dwg |
