| 摘要 |
FIELD: aircraft engineering. ^ SUBSTANCE: invention relates to aviation and pertains to development of multipurpose hydroconvertipropeller plane. The propose plane wing spins accommodates two rotary propellers to create horizontal and vertical thrust with turning assemblies and reduction gears. The latter are linked up, via connection shafts, with the main reduction gear driven from the power plant two engines mounted in nacelles on both sides of the fuselage lengthwise axis and furnished with timing shaft. This propeller plane can get converted in helicopter modes from two-propeller lengthwise configuration in to four-propeller configuration combining crosswise and lengthwise configuration and vice versa. It can also, in aircraft conditions, change over from monoplane configuration in to lengthwise configuration of triplane and vice versa. Transmission incorporating two reduction gears with rotors and lengthwise system of the shafts represents X-figure in horizontal plane. Front and rear rotors, and L.H. and R.H cantilever propellers run in mutually opposite directions. Front and rear rotor reduction gears mounted on, rhombic in plane, cross-piece arranged zigzag-like along its smaller diagonal, the larger diagonal of the latter and along the fuselage lengthwise axis. Aforesaid cross-piece consists of two different-size levers representing V-like hollow load-bearing beams with spaced apart eyes hinged to the fuselage top part and allowing their mutual turning at fixed and independent deviation in vertical plane for positive and negative different-size angles. The front smaller lever can deviate for larger negative angles, while the rear one deviates for large certain positive angles. All-moving horizontal and vertical empennages are mounted on the larger rear lever end, attached to its lateral V-like sides. Lengthwise shafts passing, inside the levers, from the rotor reduction gears to the main reduction gear located at the center of rhombic frame feature universal joints to transfer power to the above rotors at various inclinations of the levers in vertical lengthwise plane. ^ EFFECT: increased take-off weight and load ratio, simpler tail beam design, improved longitudinal and yaw control in vertical take-off, landing and hovering, that allows landing on limited-size sites in surface, ship deck and sea surface. ^ 2 dwg |
