Air scoop lip warmer de-icing system

Claim 2

An improved air scoop lip warmer de-icing system for an aircraft having at least one internal combustion engine mounted thereon for powering of said aircraft and having an elongated air scoop mounted thereto with a forwardly open end facing the air stream passing over the aircraft for operatively feeding air to the engine from the air scoop to effect a combustible mixture with engine fuel, and wherein said engine includes an exhaust pipe system for exhausting hot exhaust gases, said system comprising: a tubular metal loop configured to the open end of said air scoop, mounted to the interior of said air scoop adjacent said open end at the edge thereof, said tubular metal loop comprising a complete loop of relatively small diameter metal tubing, an inlet tube integral with said loop, extending away from said open end of said air scoop and within said air scoop, a hose clamped at one end to said inlet tube and at the other end to said exhaust pipe of said engine, an outlet tube integral with said loop at a point within said loop remote from said inlet tube, said outlet tube extending away from the open end of said air scoop and projecting through said air scoop wall rearwardly of the air scoop opening with said outlet tube open to the aircraft exterior on the surface of the elongate air scoop remote from the open end thereof, such that the exhaust gases bled from said exhaust pipe feeds to the loop through said inlet tube, divides at the intersection of said inlet tube and said loop, transverses portions of said loop as a split flow and joined at the connection of said outlet tube of said loop for common exhaust to the aircraft exterior.

Claim 3

An improved air scoop lip warmer de-icing system for an aircraft, said aircraft having at least one internal combustion engine mounted thereon for powering said aircraft and having an elongated air scoop mounted thereto with a forwardly open end facing the air stream passing over the aircraft for operatively feeding air to the engine from said air scoop to effect a combustible mixture with the engine fuel, and wherein said engine includes an exhaust pipe system for exhausting hot exhaust gases, said de-icing system comprising: a tubular metal loop configured to the open end of said air scoop, mounted to said air scoop and extending about the interior of said air scoop at the edge thereof, said aircraft taking the form of a single engine pusher type aircraft, said engine being mounted within the fuselage at the rear of the aircraft, said air scoop being of generally oval transverse cross-section, said opening within said air scoop being of generally rectangular cross-section, said tubular loop being of similar generally rectangular cross-section and sized to said air scoop opening to closely fit to said air scoop at the open inlet end thereof, said tubular metal loop comprising a small diameter continuous loop tube, an inlet tube connected to the bottom of the loop at the center thereof, an outlet tube being connected to the top of the loop at one end, said outlet tube extending within said air scoop away from said loop and having the other end of the outlet tube projecting through said air scoop and terminating flush with the upper surface thereof, rearwardly of the air scoop inlet opening, and said inlet tube being connected to the exhaust pipe of said engine such that exhaust gas bled from the exhaust gas pipe feeds to the loop, devices at the intersection of said inlet tube and said loop, traverses portions of said loop as a split flow and joins at the connection of said outlet tube to said loop for common exhaust to the aircraft exterior.

Claim 4

An improved air scoop lip warmer de-icing system for an aircraft, said aircraft having at least one internal combustion engine mounted thereon for powering said aircraft and having an elongated air scoop mounted thereto with a forwardly open end facing the air stream passing over the aircraft for operatively feeding air to the engine from said air scoop to effect a combustible mixture with the engine fuel, and wherein said engine includes an exhaust pipe system for exhausting hot exhaust gases, said de-icing system comprising: a tubular metal loop configured to the open end of said air scoop, mounted to said air scoop and extending about the interior of said air scoop at the edge thereof, said aircraft taking the form of a single engine pusher type aircraft, said engine being mounted within the fuselage at the rear of the aircraft, said air scoop being of generally oval transverse cross-section, said opening within said air scoop being of generally rectangular cross-section, said tubular loop being of similar generally rectangular cross-section and sized to said air scoop opening to closely fit to said air scoop at the open inlet end thereof, said tubular metal loop comprising a small diameter continuous loop tube, an inlet tube connected to the bottom of the loop at the center thereof, an outlet tube being connected to the top of the loop at one end, said outlet tube extending within said air scoop away from said loop and having the other end of the outlet tube projecting through said air scoop and terminating flush with the upper surface thereof, rearwardly of the air scoop inlet opening, and said inlet tube being connected to the exhaust pipe of said engine such that exhaust gas bled from the exhaust gas pipe feeds to the loop, devices at the intersection of said inlet tube and said loop, traverses portions of said loop as a split flow and joins at the connection of said outlet tube to said loop for common exhaust to the aircraft exterior.