FIELD: aviation.SUBSTANCE: hypersonic aircraft (LA) contains a housing with a thermal protection system, a fuel tank with a supply and control system. Body represents a symmetrically increasing and decreasing on the axis body, which has the form of a spindle, an acute-angled triangle or a disk, and has a regenerative cooling system for the fuel of an aircraft body. There is a system for the controlled supply of fuel to the outer shell of the housing in the zone of compression of the air flow with the possibility of its ignition in the zone of maximum compression and temperature. Ensured forced combustion in the zone of expansion of the flow creating the thrust of the aircraft at low flight speeds is provided, as well as changing the fuel supply to the corresponding area of the outer surface of the hull to control the flight of the aircraft. It is possible to use an additional rocket engine for solid fuel.EFFECT: invention is aimed at simplifying thermal protection.1 cl, 2 dwg
ГИПЕРЗВУКОВОЙ ЛЕТАТЕЛЬНЫЙ АППАРАТ
2017-08-29
Patent
Electronic Resource
Russian
IPC: | B64C AEROPLANES , Flugzeuge |