Heat conditioning through deflection/reflection/absorption of electromagnetic waves
地域：
Muharraq
摘要
A system for heat conditioning an area of Earth includes an Earth-orbiting satellite. The satellite includes a power supply, a precursor gas supply, and one or more double helicon plasma beam generators coupled to the power supply and the gas supply and configured to generate a high-density plasma and further configured with a magnetic nozzle to maintain a shape of the beam; therefore, the top surface area of the beam is maximized. The generated high-density plasma provides enhanced electromagnetic waves absorption, reflection, and deflection of incoming solar light and electromagnetic radiation, thereby, reducing the heat striking the area of the Earth.
說明書
This application claims priority to U.S. Provisional Patent Application 63/404,647, filed Sep. 8, 2022, and entitled HEAT CONDITIONING THROUGH DEFLECTION/REFLECTION/ABSORPTION OF ELECTROMAGNETIC WAVES. The content of this Provisional Application is incorporated by reference.
Energy (heat) is transmitted to Earth from the Sun by radiation and light, which are electromagnetic waves. Maxwell's equations provide the relation between the electrical and magnetic components of electromagnetic waves. Waves move at the speed of light in a vacuum. The energy of the electromagnetic waves is proportional to their frequency. We know from Einstein's General Theory that electromagnetic waves move in a straight line in vacuums and bend at an astronomic distance with the planets' gravity and the Sun's gravity.
The distance between the Sun and Earth is measured by the astronomical unit (AU)=1; but this distance varies since the Earth travels around the Sun in an oval orbit.
權利要求
I claim:1. A system for heat conditioning an area of Earth, comprising:a satellite comprising:a power supply, a precursor gas supply, and one or more double plasma beam generators coupled to the power supply and the gas supply and configured to:generate closed loop magnetic flux lines, wherein the closed loop magnetic flux lines constrain the plasma beams generated the one or more double plasma beam generators; generate a high-density plasma; and shape the high-density plasma using magnetic nozzles to maintain low beam thickness, high electron density of the plasma to improve absorption, reflection, and deflection of incoming electromagnetic waves. 2. The system of claim 1 , wherein the satellite is geostationary. 3. The system of claim 1 , wherein the one or more double plasma beam generators comprise helicons plasma beam generators. 4. The system of claim 1 , wherein the satellite is further configured to inject solids, liquids, and gases into the plasma to improve a reflection factor. 5. The system of claim 1 , wherein the satellite operates in an elliptical, retrograde sun-synchronous orbit. 6. The system of claim 1 , comprising multiple satellites arranged in a satellite constellation. 7. The system of claim 6 , wherein the multiple satellites in the satellite constellation follow a same orbital path. 8. The system of claim 6 , wherein the multiple satellites in the satellite constellation follow different orbital paths. 9. The system of claim 1 , wherein the precursor gas supply provides a gas selected from a group consisting of argon, CH4, CO2, hydrogen, nitrogen (N2) N2O3, neon, xenon and gasses. 10. The system of claim 1 , wherein the area of Earth comprises a land area, an ocean area, and a man-made structure. 11. The system of claim 1 , wherein the satellite follows a Molynia orbit. 12. The system of claim 1 , wherein the satellite is configured to trap solar dust in the plasma. 13. The system of claim 1 , wherein the power supply is selected from a group consisting of solar collectors and converters, a plutonium-based heat engine, and combinations of the solar collectors and converters and the plutonium-based heat engine. 14. The system of claim 1 , wherein the precursor comprises a refillable, pressured gas supply tank. 15. An Earth satellite configured for heat conditioning areas of Earth, comprising:a satellite power supply; a precursor gas supply tank containing a pressurized precursor gas; one or more double plasma beam generators coupled to the satellite power supply and the gas supply tank, each double plasma beam generator comprising:opposing plasma tubes configured to receive the pressurized gas from the precursor gas supply tank, a magnetic coil assembly surrounding the opposing plasma tubes and configured to impose a magnetic field on gas in the opposing plasma tubes to form a plasma, an output nozzle connected to a distal end of each of the opposing plasma tubes, and a solenoid assembly integrated with each output nozzle, and configured to generate a closed loop magnetic field, wherein each opposing plasma tube cooperates with the output nozzle and the solenoid assembly to expand the plasma gas and trap the plasma gas within the closed loop magnetic field; and a processor executing machine instructions to control operation of the power supply and each of the one or more double plasma beam generators, the satellite provides plasma beams for absorption, reflection, and deflection of incoming electromagnetic waves emitted by a Sun. 16. The satellite of claim 15 , further comprising a solid particle injection tank, the solid particle injection tank storing solid particles into the plasma tubes in concert with supply of the pressurized precursor gas, wherein the solid particles are trapped in a plasma beam and improve the absorption, reflection, and deflection of the incoming electromagnetic waves emitted by the Sun. 17. The satellite of claim 16 , wherein the satellite follows an elliptical orbit selected and maintained to position the satellite between a specific Earth area and the Sun for each rotation of the satellite around the Earth. 18. The satellite of claim 17 , wherein the satellite is one of multiple, closely-spaced satellites in a constellation of satellites, each of the multiple, closely-spaced satellites following a same orbit, wherein satellite spacing is selected to provide near-continuous coverage of the specific earth area by the plasma beams. 19. The satellite of claim 17 , wherein the satellite is one of multiple, satellites in a constellation of satellites, each of the multiple, satellites following a same orbit type at differing altitudes when traversing a specific Earth area. 20. The satellite of claim 17 , configured to follow a Lagrange point orbit. 21. A method for heat conditioning a specific area of Earth, comprising:a processor executing machine instructions to:operate a precursor gas supply tank containing a pressurized precursor gas to release the gas; and operate one or more double plasma beam generators coupled to a satellite power supply and the gas supply tank, each double plasma beam generator, comprising:opposing plasma tubes configured to receive the pressurized gas from the precursor gas supply tank, a magnetic coil assembly surrounding the opposing plasma tubes and configured to impose a magnetic field on gas in the opposing plasma tubes to form a plasma, an output nozzle connected to a distal end of each of the opposing plasma tubes, and a solenoid assembly integrated with each output nozzle, and configured to generate a closed loop magnetic field, wherein the processor controls operation of each opposing plasma tube cooperates with the output nozzle and the solenoid assembly to expand the plasma gas and trap the plasma gas within the closed loop magnetic field.
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