초록 ▼

A monomolecular carbon-based film can be placed on an aircraft part, such as the leading edge designed to directly impinge against air during flight, ascent or descent, in order to form a smooth surface having increased lubricity and reduced air friction. The aircraft part may be in the form of a he

A monomolecular carbon-based film can be placed on an aircraft part, such as the leading edge designed to directly impinge against air during flight, ascent or descent, in order to form a smooth surface having increased lubricity and reduced air friction. The aircraft part may be in the form of a helicopter rotor, wing, propeller, fin, aileron, nose cone, and the like. The monomolecular carbon-based film can be deposited on the aircraft part, for example, using a reactor that includes a bed of silica and through which emissions from a diesel engine are passed. The monomolecular carbon-based film decreases air friction and increased lift of a modified aircraft that includes an aircraft part treated with the film. It also provides a structured shock absorber.

대표청구항 ▼

1. A treated aircraft or spacecraft part having increased lubricity and resistance to air lift friction and scratch damage, comprising: a body, main surface, and leading edge designed to directly impinge against air and penetrate the atmosphere during flight, ascent or descent; anda continuous, sing

1. A treated aircraft or spacecraft part having increased lubricity and resistance to air lift friction and scratch damage, comprising: a body, main surface, and leading edge designed to directly impinge against air and penetrate the atmosphere during flight, ascent or descent; anda continuous, single molecule thick monomolecular carbon-based film having aligned elongated carbon-based molecules deposited on at least the leading edge and optionally at least a portion of the main surface of the aircraft or spacecraft part, the monomolecular carbon-based film providing a smooth surface with increased lubricity and resistance to air friction when the leading edge or main surface of the aircraft or spacecraft part directly impinges air during flight, ascent or descent. 2. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft part is a helicopter rotor blade. 3. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft part is a wing. 4. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft part is a propeller. 5. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft part is a jet compression rotor designed to be subjected to compression during use. 6. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft part is an aileron. 7. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft part is a fin. 8. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft or spacecraft part is a nose cone. 9. A treated aircraft or spacecraft part as in claim 1, wherein the aircraft or spacecraft part comprises at least one metal selected from the group consisting of iron, steel, aluminum, copper, and other dense materials. 10. A treated aircraft or spacecraft part as in claim 8, the monomolecular carbon-based film providing friction, scratch and corrosion resistance to the at least one metal. 11. A modified aircraft or spacecraft having reduced air friction and increased lift during flight, descent or ascent, comprising: at least one aircraft or spacecraft part with a leading edge designed to directly impinge against moving or stationary air during flight, descent or ascent; anda continuous, single molecule thick monomolecular carbon-based film having aligned elongated carbon-based molecules deposited on at least the leading edge of the aircraft or spacecraft part, the monomolecular carbon-based film providing a smooth surface with increased lubricity and resistance to air friction due to each elongated carbon-based molecule being a naturally structured shock absorber when the leading edge of the aircraft or spacecraft part directly impinges air during flight and ascent or descent of the aircraft or spacecraft. 12. A modified aircraft or spacecraft as in claim 11, the aircraft comprising a helicopter. 13. A modified aircraft or spacecraft as in claim 11, the aircraft comprising a jet powered aircraft engine, wherein the film reduces fuel consumption. 14. A modified aircraft or spacecraft as in claim 11, the aircraft comprising an airplane. 15. A modified aircraft or spacecraft as in claim 11, the aircraft comprising a missile. 16. A method of flying an aircraft with reduced air friction, wing icing, and metal wetting, comprising: providing a modified aircraft comprised of: at least one aircraft part with a leading edge designed to directly impinge against moving or stationary air during flight, descent or ascent an air; anda continuous, single molecule thick monomolecular carbon-based film having aligned elongated carbon-based molecules deposited on at least the leading edge of the aircraft part, the monomolecular carbon-based film providing a smooth surface with increased lubricity and resistance to air friction when the leading edge of the aircraft part directly impinges air during flight, ascent or descent of the aircraft; andcausing or allowing the modified aircraft to fly, ascend or descend through air. 17. A method of manufacturing a treated aircraft or spacecraft part as in claim 1, comprising: operating a reactor containing a bed of particles comprised of at least one of silica or alumina particles coupled to a diesel engine to produce the elongated carbon-based molecules as a byproduct; andcausing or allowing the elongated carbon-based molecules to form on at least the leading edge of the aircraft or spacecraft part and optionally on at least a portion of the main surface and align so as to form the continuous, single molecule thick monomolecular carbon-based film comprising aligned elongated carbon-based molecules, the monomolecular carbon-based film providing a lubricious surface that inhibits air friction, corrosion and surface scratches. 18. A method as in claim 17, wherein the exhaust stream is produced by a diesel engine, the reactor producing hydroxyl radicals within 30 seconds of diesel ignition, and thereafter the diesel engine having essentially complete combustion in which is 99.995% of the exhaust gases produced thereby include oxygen, nitrogen and 80% depleted CO2, with a substantial drop in exhaust temperature.