초록 ▼

A supercharging system for supplying pressurized combustion air to a piston engine of an aircraft at high altitudes. The engine has an output shaft on which the propeller is supported, together with a small ducted centrifugal fan. The duct leads to the intake side of the engine. A diverter is movabl

A supercharging system for supplying pressurized combustion air to a piston engine of an aircraft at high altitudes. The engine has an output shaft on which the propeller is supported, together with a small ducted centrifugal fan. The duct leads to the intake side of the engine. A diverter is movable to one position constraining pressurized air to enter the engine through the intake side, and a second position which diverts compressed air away from the intake side. Natural aspiration is employed at low altitudes and supercharging is employed at altitudes wherein there is an oxygen deficiency. Preferably, the centrifugal fan is located between the propeller and the engine block, has blades staggered from those of the propeller so as to be directly exposed to incoming air. The centrifugal fan blades are preferably of different pitch than the propeller blades.

대표청구항 ▼

1. A supercharged reciprocating engine assembly for a miniature, unmanned aircraft, comprising:an engine sized and configured for powering said miniature, unmanned aircraft and having an engine block defining at least one cylinder, and a piston reciprocatingly and slidably disposed within each cylin

1. A supercharged reciprocating engine assembly for a miniature, unmanned aircraft, comprising:an engine sized and configured for powering said miniature, unmanned aircraft and having an engine block defining at least one cylinder, and a piston reciprocatingly and slidably disposed within each cylinder; a single air intake passage for conducting combustion air into said at least one cylinder; a rotatable output shaft rotatingly driven by said engine and projecting forward therefrom; a propeller disposed proximate a forward end of said rotatable output shaft; a single duct disposed to house an axial flow air pressurization device mounted on said output shaft therein, said single duct having an intake end disposed proximate said propeller, and a discharge end operatively connected to said single air intake passage, said single duct configured to route air pressurized by said axial flow air pressurization device within said single duct to said single air intake passage of said engine; and a diverter disposed in said single duct to selectively route pressurized air into said single air intake passage of said engine and to discharge pressurized air away from said single air intake passage of said engine; both said single duct and said single air intake passage being disposed between said propeller and a forward side of said engine. 2. The supercharged reciprocating piston engine according to claim 1, wherein said air pressurization device is an axial flow fan.3. The supercharged reciprocating piston engine according to claim 2, wherein said air pressurization device is an axial flow fan having blade of pitch characteristics different from those of said propeller.4. The supercharged reciprocating piston engine according to claim 2, wherein said propeller has propeller blades, and said axial flow fan has air pressurization blades arranged in staggered relationship to said propeller blades such that said air pressurization blades are directly exposed to incoming air passing between said propeller blades.5. The supercharged reciprocating piston engine according to claim 1, wherein said air pressurization device is located in said single duct and on said output shaft between said propeller and said engine block.6. The supercharged reciprocating piston engine according to claim 1, wherein said diverter is infinitely movable between a first position wherein at least most of the pressurized air is constrained to flow away from said single air intake passage and a second position wherein at least most of the pressurized air is constrained to flow into said single air intake passage.7. The supercharged reciprocating piston engine according to claim 1, wherein said diverter is moved between said first and said second positions by a servomechanism.8. The supercharged reciprocating piston engine according to claim 7, wherein said servomechanism is controlled by at least one of the control sources: a microprocessor, a control signal originating remotely from an aircraft carrying and powered by said supercharged reciprocating piston engine.9. A supercharged reciprocating engine assembly for a miniature, unmanned aircraft, comprising:a) an engine comprising an engine block defining at least one cylinder, a piston reciprocatingly and slidably disposed within said at least one cylinder, a single air intake passage for receiving combustion air and conducting said combustion air to said at least one cylinder; and a rotatable output shaft projecting forward from a front surface of said engine block; b) a propeller having blades arranged in a first, predetermined radial arrangement and affixed to said rotatable output shaft proximate a distal end thereof; c) a single duct having an intake end disposed adjacent to and rearward of said propeller, and a discharge end operably connected to said single air intake passage of said engine to route air from said intake end to said single air intake passage; d) an axial flow air pressurization device disposed on said output shaft rearward of said propeller and within said single duct, for pressurizing air therein; e) a diverter disposed within said single duct between said air pressurization device and said single air intake passage to selectively route pressurized air into said single intake passage of said engine and to discharge pressurized air away from said single air intake passage of said engine. 10. A supercharged reciprocating engine assembly for a miniature, unmanned aircraft as recited in claim 9, further comprising:f) means for producing laminar air flow disposed within said single duct between said axial flow air pressurization device and said diverter. 11. A supercharged reciprocating engine assembly for a miniature, unmanned aircraft as recited in claim 7, wherein said axial flow air pressurization device comprises blades arranged in a second, predetermined arrangement, said second, predetermined arrangement being such that said blades of said axial flow air pressurization device are disposed in staggered relationship to said propeller blades such that said air pressurization blades are directly exposed to incoming air passing between said propeller blades arranged in said first, predetermined arrangement.12. A supercharged reciprocating engine assembly for a miniature, unmanned aircraft as recited in claim 9, wherein said diverter is infinitely movable between a first position wherein at least most of the pressurized air is constrained to flow away from said single air intake passage and a second position wherein at least most of the pressurized air is constrained to flow into said single air intake passage.13. The supercharged reciprocating piston engine according to claim 12, wherein said diverter is moved between said first and said second positions by a servomechanism.