초록 ▼

An aircraft converting aerodynamic compression ram thermal stream energy into thrust power generation comprising: (a) an aerodynamic compression ram thermal stream generating multiple vane diffuser as the air-inlet to a pressure plenum; (b) a ram thermal-pressure stream induction double throttle duc

An aircraft converting aerodynamic compression ram thermal stream energy into thrust power generation comprising: (a) an aerodynamic compression ram thermal stream generating multiple vane diffuser as the air-inlet to a pressure plenum; (b) a ram thermal-pressure stream induction double throttle duct consisting of a main ramflow inducing nozzle and a fuel injection ramflow inducing nozzle wihch coalesce to form the air-oulet of a pressure plenum-engine pod; (c) a compressed air shooting annular slotted ignition chamber downstream of the fuel injecting ramflow inducing nozzle with flame bed-walled combustion chamber forming a ramjet engine; (d) a ram thermal-pressure stream induction annular slotted thrust nozzle extending rearward from the combustion chamber of the ramjets and exit nozzle of a turbojet engine thereby creating a tailpipe for the turbo-ram induction jet engine; and (e) an aerodynamic compression ram thermal stream sink double-walled shockcone airframe, the double walled shockcone housing the ram thermal stream spaces communicating with the ram thermal-pressure flow induction thrust generating channel.

대표청구항 ▼

An aircraft converting aerodynamic ram thermal stream energy generated by aerodynamic compression heat-flow directly into thrust power thereby creating an aerothermal ultra hypersonic aircraft, said aerothermal ultra hypersonic aircraft comprising an airfoil shaped disk airframe, said disk airframe

An aircraft converting aerodynamic ram thermal stream energy generated by aerodynamic compression heat-flow directly into thrust power thereby creating an aerothermal ultra hypersonic aircraft, said aerothermal ultra hypersonic aircraft comprising an airfoil shaped disk airframe, said disk airframe further comprising: (a) an aerodynamic compression ram thermal stream generating vane diffuser mounted on the forward face of an air plenum-engine pod, said vane diffuser defining the air inlet of a ram thermal-pressure plenum wherein said vane diffuser further comprises vertical multiple vanes; and (b) at least two ram thermal-pressure stream induction nozzle mounted on the rearward portion of said air plenum-engine pod, said induction nozzles defining an air outlet of the ram thermal-pressure plenum wherein said induction nozzle consists of a convergent-divergent double throttle duct, the center throttle being a main ramflow inducing nozzle and the outer throttle being a fuel injecting ram flow inducing nozzle, both nozzles convergent from a bellmouth-shaped air inlet located in the ram thermal-pressure plenums on both sides of a turbojet engine, said main throttle duct and said outer throttle duct having a main throat and an outer throat respectively, the main throat being slightly divergent along its extension and venting into a combustion chamber, and the outer throat being divergent to ensure adequate ignition velocity of the ramjet stream in an ignition-combustion chamber; and (c) a combustion chamber, the downstream end-inner edges of this combustion chamber being tangentially jointed with the exit nozzle of a turbojet engine and the outer edges of this combustion chamber peripherally reshaped to form an oval thrust nozzle, said oval thrust nozzle being enveloped by a ram thermal stream induction annular slot communicating from the ram thermal-pressure plenum; and (d) an aerodynamic compression ram thermal stream sink shockcone forming the forward section of a disk airframe, said shockcone enclosing double walled ram thermal stream spaces continuous with and extending into a hollow space located behind channel walls, said channel walls enclosing a plurality of inclined orifices, said inclined orifices directing the flow of air therethrough toward the rear of the aircraft.