# US 10,501,212 B2 · Removing orbital space debris from near earth orbit

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- Number: US 10,501,212 B2
- Document ID: US10501212B2
- Status: Granted
- Kind: B2
- Application number: 16/399,151
- Filed: 2019-04-30
- Published: 2019-10-31
- Granted: 2019-12-10
- Earliest claimed: 2018-04-30
- Assignees: John Francis Dargin
- Applicants: John Francis Dargin, III
- Inventors: John Francis Dargin, III
- Web page: https://patentgrep.com/patent/US10501212B2

## CPC

- B64G 1/32: using earth's magnetic field
- B64G 1/10: Artificial satellites; Systems of such satellites; Interplanetary vehicles (space shuttles B64G1/14)
- B64G 1/105: {Space science}
- B64G 1/1081: {for debris removal}
- B64G 1/1085: {Swarms and constellations}
- B64G 1/242: {Orbits and trajectories}
- B64G 1/366: {using magnetometers}
- B64G 1/66: Arrangements or adaptations of apparatus or instruments, not otherwise provided for
- B64G 1/2425: {Geosynchronous orbits}
- B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR

## Abstract

A system utilizing an antenna generating an electromagnetic (EM) wave to interact with a solar EM wave to streamline magnetic flux in the polar cusp and to facilitate the flow of solar plasma through the Polar Cusp, resulting in an elevated plasma flux at the exit of the Polar Cusp. The elevated plasma flux intercepts and removes small space debris from Low Earth Orbit (LEO), Geosynchronous Earth Orbit (GEO) and Geosynchronous Transfer Orbits (GTO) transiting the LEO altitude regimes.

## Claims

### Claim 1

A system for removing space debris from near Earth orbit, comprising:
a solar plasma sensor (SPS) to detect parameters of a solar electromagnetic (EM) wave and a solar plasma; a space debris sensor (SDS) to detect parameters of space debris;
a satellite in communication with the SPS and positioned over an entry point of a polar cusp, the satellite comprising:
an antenna to direct a local EM wave to interact with the solar EM wave at the entry point of the polar cusp; and
control systems to control an orientation of the antenna and to select parameters of the local EM wave to convert a turbulent magnetic flux of the solar EM wave to a laminar magnetic flux, wherein a component of solar plasma is directed into the polar cusp in a uniform flow that maximizes a plasma flux at an exit point of the polar cusp.

### Claim 2 (depends on 1)

The system of claim 1, wherein the plasma flux in the polar cusp is operable to intercept and decelerate near-Earth orbit debris, wherein the near-Earth orbit debris is removed from orbit.

### Claim 3 (depends on 1)

The system of claim 1, wherein the uniform flow comprises one or more of a linear laminar flow and a spiral laminar flow of the component of the solar plasma.

### Claim 4 (depends on 1)

The system of claim 1, wherein the component of the solar plasma comprises positively charged ions.

### Claim 5 (depends on 1)

The system of claim 1, wherein the component of the solar plasma comprises negatively charged electrons.

### Claim 6 (depends on 1)

The system of claim 1, wherein the parameters of the EM wave comprise power, frequency and polarization of the EM wave.

### Claim 7

A method for removing space debris from near Earth orbit, comprising:
positioning a satellite over an entry point of a polar cusp;
receiving, from a solar plasma sensor, parameters of a solar electromagnetic (EM) wave and a solar plasma;
receiving, from a space debris sensor, parameters of targeted space debris;
directing, with an antenna of the satellite, a local EM wave to interact with the solar EM wave at the entry point of the polar cusp;
selecting parameters of the local EM wave to convert a turbulent magnetic flux of the solar EM wave to a laminar magnetic flux, wherein a component of the solar plasma is directed into the polar cusp in a uniform flow that maximizes a plasma flux at an exit point of the polar cusp.

### Claim 8 (depends on 7)

The method of claim 7, wherein the plasma flux in the polar cusp is operable to intercept and decelerate near-Earth orbit debris, wherein the near-Earth orbit debris is removed from orbit.

### Claim 9 (depends on 7)

The method of claim 7, wherein the uniform flow comprises one or more of a linear laminar flow and a spiral laminar flow of the component of the solar plasma.

### Claim 10 (depends on 7)

The method of claim 7, wherein the component of the solar plasma comprises positively charged ions.

### Claim 11 (depends on 7)

The method of claim 7, wherein the component of the solar plasma comprises negatively charged electrons.

### Claim 12 (depends on 7)

The method of claim 7, wherein the parameters of the EM wave comprise power, frequency and polarization of the EM wave.

### Claim 13

An apparatus, comprising a satellite configured to be positioned at an entry point of a polar cusp, the satellite further configured to receive parameters of a solar electromagnetic (EM) wave and parameters of a solar plasma from a solar plasma sensor, and to receive parameters of targeted space debris from a space debris sensor; the satellite comprising:
an antenna configured to direct a local EM wave to interact with the solar EM wave at the entry point of the polar cusp; and
control systems to control an orientation of the antenna and to select parameters of the local EM wave to convert a turbulent magnetic flux of the solar EM wave to a laminar magnetic flux, wherein a component of solar plasma is directed into the polar cusp in a uniform flow that maximizes a plasma flux at an exit point of the polar cusp to intercept the targeted space debris.