Abstract: A light multi-purpose aircraft with a controlling integrated complex comprises a fuselage (1); a wing (2); a fin assembly (3); a landing gear (4); a power plant (5); a radio inertial navigation and landing complex; an integrated electronic display system; a complex emergency escape system; an objective monitoring system; a complex control system; a general-purpose aircraft equipment system; a crest-of-helmet target indication system; a speech information control system; a data input system; control panels; an on-board communication complex; on-board maintenance panels; and also a controlling integrated complex (6) incorporating an on-board digital computer system (7); an information exchange system composed of multiplexer and radial channels; and systems and/or units for interfacing with all functional complexes and systems of the aircraft in which the on-board digital computer system (7), through corresponding interfacing systems and/or units, is connected by multiplexer channels with the aircraft systems, i

Abstract: A light multi-purpose aircraft comprises a fuselage (1); a wing (2); a fin assembly (3); a landing gear (4); a main power plant (5); an auxiliary power plant (7); pylons (10); outboard suspension objects (9) arranged on the undersurface and at the ends of the wing (2); at least one outboard suspension object (9) being arranged on the undersurface of the wing (2) and at least one outboard suspension object (9) being arranged at each end of the wing (2); a gun mount (8) or a guidance and tracking mount arranged in the lower part of the fuselage (1); a controlling integrated complex of airborne electronic equipment (17) with an electric power supply system (16) and an armament control complex (19) incorporating an on-board electronic guidance and tracking system (20); a defense system (21); a multi-purpose control panel (22); a group interaction system (23); an armament control system (24) which are related to each other and to the controlling integrated complex of airborne electronic equipment (17) through a mu

Abstract: A start flame igniter of the combustion chamber of a gas-turbine engine has a housing with an injector for spraying fuel supplied to a combustion chamber of the igniter. Located inside the igniter housing are a spark plug in such a way that a discharge zone of the spark plug contacts the fuel sprayed by the injector and a cylindrical bushing which is coaxial to the spark plug and partially embraces said spark plug at the side where the spark plug discharge zone is situated. The length of the bushing is sufficient to ensure a direct contact with the fuel sprayed by injector at a minimum cone of the fuel spray relative to the operation duty of the injector. The bushing butt facing the sprayed fuel has an inclination which coincides approximately with a generatrix of the minimum cone of the fuel spray. The bushing butt is provided with a plate following the shape of a half of butt nearest to the injector. The plate along the axis has a recess embracing the discharge zone of the spark plug.