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US-12621921-B2 - Heat conditioning through deflection/reflection/absorption of electromagnetic waves

US12621921B2US 12621921 B2US12621921 B2US 12621921B2US-12621921-B2

Abstract

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 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 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.

Inventors

  • Ali Kaddoura

Assignees

  • Ali Kaddoura

Dates

Publication Date
20260505
Application Date
20240308

Claims (20)

  1. 1 . A satellite-based system for heat conditioning a specified area on Earth, comprising: a satellite constellation comprising one or more Earth satellites, wherein at least one Earth satellite of the one or more Earth satellites, comprises: a power supply, a gas precursor supply comprising a supply tank storing a pressurized gas, one or more double plasma beam generators coupled to the power supply and the gas precursor supply, and configured to: generate a plasma; generate closed loop magnetic field lines, wherein the closed loop magnetic field lines constrain plasma generated by the plasma generators; and shape the plasma into plasma beams using magnetic nozzles to maintain low beam thickness and high electron density of the plasma to improve absorption, reflection, and deflection of incoming electromagnetic waves, and one or more magnetic front ends and corresponding magnetic field generators configured to generate additional closed loop magnetic field lines, wherein the additional closed loop magnetic field lines operate to further constrain the plasma; and a ground station in two-way signal communication with each of the one or more Earth satellites to track and to control orbits and heat reduction operations of each of the one or more Earth satellites.
  2. 2 . The satellite-based system of claim 1 , wherein the one or more Earth satellites are in elliptical orbits.
  3. 3 . The satellite-based system of claim 2 , wherein in the elliptical orbits are identical, and a plurality of the Earth satellites are configured to operate in series, comprising: the plurality of Earth satellites are configured to maintain a close spacing between successive ones of the plurality of Earth satellites such that plasma beams generated by each Earth satellite provide near-continuous coverage of the specified area on Earth, whereby the specified area on Earth does not experience a temperature increase from one Earth satellite to another Earth satellite; and each Earth satellite is configured to reach apogee over the specified area on Earth.
  4. 4 . The satellite-based system of claim 3 , wherein the elliptical orbit is a low-Earth, inclined orbit.
  5. 5 . The satellite-based system of claim 2 , wherein in the elliptical orbits are staggered in apogee, and a plurality of the Earth satellites are configured to operate simultaneously, comprising: the plurality of Earth satellites are configured to maintain a close spacing between successive ones of the plurality of Earth satellites such that plasma beams generated by each Earth satellite provide near-continuous coverage of the specified area on Earth during times of apogee of each of the plurality of Earth satellites, whereby the specified area on Earth does not experience a temperature increase from one Earth satellite to another Earth satellite; and each Earth satellite is configured to reach its individual apogee over the specified area on Earth, wherein orbital speeds of each of the plurality of Earth satellites over the specified area on Earth vary according to their individual apogees.
  6. 6 . The satellite-based system of claim 1 , wherein the one or more double plasma beam generators are selected from a thruster group consisting of helicon plasma beam generators, magnetoplasma dynamic thrusters, pulsed inductive thrusters, pulsed plasma thrusters, electrodeless plasma thrusters, variable specific magnetoplasma rockets (VASIMR), gridded Ion engines, hall effect thrusters, hydrazine thrusters, hydrogen thrusters, and lithium thrusters.
  7. 7 . The satellite-based system of claim 1 , wherein one or more of the Earth satellites is configured to inject solids, liquids, and gases into the plasma to improve a solar energy reflection factor.
  8. 8 . Satellite-based system of claim 1 , wherein one or more Earth satellites is configured to operate in an elliptical, retrograde sun-synchronous orbit.
  9. 9 . The satellite-based system of claim 1 , wherein one or more of the Earth satellites comprises a refillable precursor gas supply configured to be refilled during orbit.
  10. 10 . The satellite-based system of claim 1 , wherein the gas is selected from a group consisting of argon, CH 4 , CO 2 , hydrogen, nitrogen (N 2 ) N 2 O 3 , neon, krypton, and xenon gasses.
  11. 11 . The satellite-based system of claim 1 , wherein the area on Earth comprises a land area, an ocean area, and a man-made structure.
  12. 12 . The satellite-based system of claim 11 , wherein the satellite constellation is configured to reduce ocean area temperature to limit hurricane formation.
  13. 13 . The satellite-based system of claim 1 , wherein one or more Earth satellites is configured to trap solar dust in the plasma.
  14. 14 . The satellite-based system of claim 1 , wherein one or more of the double plasma beam generators comprises: opposing plasma tubes configured to receive the pressurized gas from the 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.
  15. 15 . The satellite-based system of claim 14 , wherein the output nozzle comprises an exit plane configured to shape expanding plasma gas in a desired configuration.
  16. 16 . The satellite-based system of claim 1 , wherein one or more of the Earth satellites comprises a processor configured to execute machine instructions to control operation of the power supply and each of the one or more double plasma beam generators, wherein execution of the machine instructions causes the Earth satellite to provide plasma beams for absorption, reflection, and deflection of incoming electromagnetic waves emitted by a Sun.
  17. 17 . A method for heat conditioning a designated area of Earth, comprising: a ground-based processor executing machine instructions to direct operations of one or more Earth satellites of a constellation of Earth satellites, comprising: direct the one or more Earth satellites orbiting over the designated area of Earth to operate a precursor gas system, comprising a refillable supply tank containing a pressurized precursor gas, to release the pressurized precursor gas, and operate one or more double plasma beam generators, each double plasma beam generator comprising opposing plasma tubes and a magnetic coil assembly surrounding each of the plasma tubes comprising: energizing a magnetic coil assembly surrounding the opposing plasma tubes and to impose a magnetic field on gas in the opposing plasma tubes to form a plasma, and energizing a solenoid assembly integrated with each output nozzle, and configured to generate a closed loop magnetic field to expand the plasma gas and trap the plasma gas within the closed loop magnetic field.
  18. 18 . The method of claim 17 , further comprising instructing one or more of the Earth satellites to adjust its apogee for orbit over the designated area of Earth.
  19. 19 . The method of claim 17 , further comprising instructing each Earth satellite of a plurality of the Earth satellites to operate in series, wherein each of the plurality of Earth satellites is instructed to maintain a close spacing between successive ones of the plurality of Earth satellites such that plasma beams generated by each Earth satellite provide near-continuous coverage of the designated area of Earth, whereby the designated area of Earth does not experience a temperature increase from one Earth satellite to another Earth satellite, and each Earth satellite reaches apogee over the designated area of Earth.
  20. 20 . The method of claim 17 , wherein each Earth satellite in a plurality of Earth satellites follows a same orbit type at differing altitudes when traversing the designated area of Earth.

Description

RELATED APPLICATIONS This application is a continuation of U.S. patent application Ser. No. 17/972,185, filed Oct. 24, 2022, entitled Heat Conditioning through Deflection/Reflection/Absorption of Electromagnetic Waves, now U.S. Pat. No. 11,930,583, issued Mar. 12, 2024, which 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 contents of these patent documents are incorporated by reference. BACKGROUND 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. FIG. 1 illustrates the natural phenomena of solar limbs. In FIG. 1, solar limbs, namely, the solar plasma atmosphere through which the light rays are directed along a minimum energy or least time path towards Earth. The thickness of the plasma atmosphere of the Sun, frequently referred to as the solar rim or the solar limb, is very negligible in comparison to the solar radius R. Centuries of observations confirm the existence of gravitational light bending as a function of the distance above the solar plasma limb. (Many of the observed solar light bending events were recorded during solar eclipses during which the Moon provided near-perfect masking of the solar disk, allowing only the thin plasma limb of the sun to be exposed for astrophysical observations.) FIG. 2 is a representation of Earth-Sun magnetic flux connection. SUMMARY A system for heat conditioning an area of Earth includes a geosynchronous satellite comprising one or more double helicon plasma beam generators configured to generate a plasma and further configured to shape the plasma using an oval shape nozzle to maintain beam thickness to a minimum and maximize the beam top surface area. Only electromagnetic waves with a frequency higher than the plasma frequency will propagate through the plasma. A portion of the electromagnetic waves with a frequency higher than the plasma frequency will deflect through the plasma. A portion of the electromagnetic waves will be absorbed in the plasma due to photons absorption. Thus, the plasma beam absorption, reflection, and deflection of a portion of incoming solar electromagnetic waves will reduce the heat striking an area of Earth. In addition, trapped dust around the satellite will block light and electromagnetic waves either by absorption or reflection. The dust can be deposited naturally from the solar wind or placed intentionally around the satellite. A satellite-based, computer-controlled method for heat-conditioning an area of Earth comprises a processor onboard the satellite receiving control communications to produce a plasma beam for a specified period (start and stop times) in a day and to cover a specific area of Earth for that specified time. In response, the satellite orients to produce the desired coverage by a specified start time and the satellite begins plasma generation. The satellite reorients, as needed, to maintain coverage for the specified area. When the specified stop time is reached, the satellite stops plasma generation. An Earth satellite configured for heat conditioning areas of Earth includes a satellite power supply, a precursor gas supply tank containing a pressurized precursor gas. and one or more double plasma beam generators coupled to the satellite power supply and the gas supply tank. Each double plasma beam generator includes 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. The satellite includes 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. A satellit