Abstract
Example aspects of an assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The assembly can comprise a deployable deployed electromagnetic radiation deflector shield comprising: a power supply; and an electromagnet configured to generate a magnetic field to deflect radiation; and a spacecraft, wherein the deployed electromagnetic radiation deflector shield is unattached to the spacecraft when deployed from the spacecraft, wherein the deployed electromagnetic radiation deflector shield is deployed at a distance away from the spacecraft, and wherein the distance is configured to prevent the magnetic field generated by the electromagnet from interfering with the spacecraft.
Claims
1. An assembly comprising: a deployable deployed electromagnetic radiation deflector shield comprising: a power supply; and an electromagnet configured to generate a magnetic field to deflect radiation; and a spacecraft, wherein the deployed electromagnetic radiation deflector shield is unattached to the spacecraft when deployed from the spacecraft, wherein the deployed electromagnetic radiation deflector shield is deployed at a distance away from the spacecraft, and wherein the distance is configured to prevent the magnetic field generated by the electromagnet from interfering with the spacecraft.
2. The assembly of claim 1, wherein the deployed electromagnetic radiation deflector shield further comprises a plasma injector configured to inject a plasma gas into the magnetic field to boost an effectiveness of the magnetic field.
3. The assembly of claim 2, wherein the plasma injector comprises a plasma gas, the plasma gas comprising at least one of barium and lithium.
4. The assembly of claim 1, wherein the magnetic field is configured to vary in strength to optimize a zone of minimum radiation.
5. The assembly of claim 1, wherein the deployed electromagnetic radiation deflector shield further comprises a refrigeration unit, the refrigeration unit comprising a refrigerant configured to reduce a temperature of the electromagnet.
6. The assembly of claim 5, wherein the refrigerant comprises at least one of helium and nitrogen.
7. The assembly of claim 5, wherein the refrigeration unit comprises coils surrounding the electromagnet, and wherein the refrigerant is transferred through the coils.
8. The assembly of claim 1, further comprising a sensor configured to sense radiation and a propulsion device configured to move the position of the deployed electromagnetic radiation deflector shield relative to the spacecraft to align the magnetic field with the radiation.
9. The assembly of claim 8, wherein the propulsion device comprises at least one thruster coupled to the deployed electromagnetic radiation deflector shield and a thruster control unit configured to control the thruster.
10. The assembly of claim 1, wherein the deployed electromagnetic radiation deflector shield is stowed within the spacecraft when not deployed from the spacecraft.
11. An assembly comprising: a deployable first deployed electromagnetic radiation deflector shield comprising a first electromagnet configured to generate a first magnetic field; a deployable second deployed electromagnetic radiation deflector shield comprising a second electromagnet configured to generate a second magnetic field, wherein the first and second magnetic fields together define a primary magnetic field; and a spacecraft, wherein the first and second deployed electromagnetic radiation deflectors shield are each deployed to a distance away from the spacecraft such that the primary magnetic field does not interfere with the spacecraft.
12. The assembly of claim 11, wherein each of the first and second deployed electromagnetic radiation deflector shields are unattached to the spacecraft when deployed from the spacecraft.
13. The assembly of claim 11, wherein at least one of the first and second deployed electromagnetic radiation deflector shields are stowed within the spacecraft when not deployed from the spacecraft.
14. The assembly of claim 11, wherein the primary magnetic field creates a zone of minimum radiation, and wherein the entire spacecraft lies within the zone of minimum radiation.
15. The assembly of claim 14, wherein the first deployed electromagnetic radiation deflector shield is repositionable relative to the second deployed electromagnetic radiation deflector shield to adjust at least one of a size and a shape of the zone of minimum radiation.
16. A method for using a deployed electromagnetic radiation deflector shield comprising: deploying the deployed electromagnetic radiation deflector shield from a spacecraft, wherein the deployed electromagnetic radiation deflector shield is unattached to the spacecraft when deployed; moving the deployed electromagnetic radiation deflector shield into a desired position relative to the spacecraft; and generating a magnetic field to deflect radiation from the spacecraft, wherein the deployed electromagnetic radiation deflector shield is deployed to a distance such that the magnetic field does not interfere with the spacecraft.
17. The method of claim 16, further comprising sensing radiation with a sensor of the deployed electromagnetic radiation deflector shield and moving the position of the deployed electromagnetic radiation deflector shield to align the magnetic field with the radiation.
18. The method of claim 16, wherein the deployed electromagnetic radiation deflector shield comprises a power supply and an electromagnet, and wherein generating a magnetic field comprises supplying power from the power supply to the electromagnet.
19. The method of claim 16, wherein generating a magnetic field creates a zone of minimum radiation, and wherein the entire spacecraft lies within the zone of minimum radiation.
20. The method of claim 19, wherein the deployed electromagnetic radiation deflector shield is a first deployed electromagnetic radiation deflector shield, the method further comprising: deploying a second deployed electromagnetic radiation deflector shield from the spacecraft; and repositioning the first deployed electromagnetic radiation deflector shield relative to the second deployed electromagnetic radiation deflector shield to adjust at least one of a size and a shape of the zone of minimum radiation.
Description
BRIEF DESCRIPTION OF THE DRAWINGS
[0024] The features and components of the following figures are illustrated to emphasize the general principles of the present disclosure. Corresponding features and components throughout the figures may be designated by matching reference characters for the sake of consistency and clarity. Some embodiments of the present invention (DERDS) are illustrated as an example and are not limited by the figures of the accompanying drawings, in which like references may indicate similar elements and in which:
[0025] FIG. 1: FIG. 1 depicts an embodiment of the novel use of the DERDS where it is shown to be deployed away from the spacecraft and creates a zone of minimum radiation in which the spacecraft resides. Herein it is depicted to be tethered to the spacecraft.
[0026] FIG. 2: FIG. 2 depicts the deployment of the DERDS via a rigid telescopic device attached to the spacecraft. This embodiment would not require thrusters and associated equipment on the DERDS as it would move as one when the spacecraft maneuvers. Again, it shows the zone of minimum radiation created for the spacecraft.
[0027] FIG. 3: FIG. 3 depicts a preferred embodiment of the structure and components of the DERDS.
[0028] FIG. 4: FIG. 4 depicts an embodiment of a superconducting electromagnet within the DERDS.
[0029] FIG. 5: FIG. 5 depicts an embodiment of the fully deployed and unattached DERDS. It shows one possibility of where plasma can be contained within a magnetic torus generated by the DERDS. It shows a magnetic field and plasma field positioned away from the spacecraft.
[0030] FIG. 6: FIG. 6 is a side view of FIG. 5 illustrating the magnetic field and possible plasma field positioned away from the spacecraft.
[0031] FIG. 7: FIG. 7 depicts an embodiment of a formation of smaller DERDS creating a larger or differently shaped zone of minimum radiation.
[0032] FIG. 8: FIG. 8 illustrates an embodiment of the DERDS as deployed on an ecliptic track and providing a large zone of minimum radiation for an extra-planetary or moon base.
[0033] FIG. 9: FIG. 9 is a side view of FIG. 8. It shows how the ecliptic track allows the DERDS to be properly positioned always, as it moves in concert along the track as the Sun (or other source of radiation) arcs across the horizon. It thereby keeps the zone of minimum radiation surrounding the base station as the radiating emitting body moves across the sky.
DETAILED DESCRIPTION
[0034] The terminology used herein is for the purpose of describing embodiments only and is not intending to be limiting of the invention (also referred to herein as DERDS). As used herein, the term and/or includes any and all combinations of one or more of the associated listed items. As used herein, the singular forms a, an, and the are intended to include the plural forms as well as the singular forms, unless the context clearly indicates otherwise. It will be further understood that the terms comprises and/or comprising, when used in this specification, specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof.
[0035] Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one having ordinary skill in the art to which this invention belongs. It will be further understood that such terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and the present disclosure, and will not be interpreted in an idealized or overly formal sense unless expressly so defined.
[0036] In describing the invention, it will be understood that a number of techniques and steps are disclosed. Each of these has individual benefit and each can also be used in conjunction with one or more, or in some cases all, of the other disclosed techniques. Accordingly, for the sake of clarity, this description will refrain from repeating every possible combination of the individual steps in an unnecessary fashion. Nevertheless, the specification and claims should be read with the understanding that such combinations are entirely within the scope of the invention and claims.
[0037] In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be evident, however, to one skilled in the art that the present invention may be practiced without these specific details. The present disclosure is to be considered as an exemplification of the invention and is not intended to limit the invention to the specific embodiments illustrated by the figures or description below.
[0038] FIG. 1: One embodiment of the deployed electromagnetic radiation deflector shield-4, i.e. the DERDS-4, is deployed by a spacecraft-7 using an umbilical/tether device-5. The Sun-1 produces solar radiation-2. The DERDS-4 generates a magnetic field-3 which deflects the incoming radiation-2 and creates a zone of minimum radiation-6 like the Earth's magnetosphere. This is the zone-6 wherein the spacecraft-7 will reside for long durations. It is envisioned that this embodiment of the DERDS-4 will be supplied with electrical power and control of position by the spacecraft-7 through the umbilical/tether-5. The DERDS-4 can self-maneuver with on board thrusters-26 (shown in FIG. 3) and computers-90 (shown in FIG. 3) to keep the DERDS-4 aligned between the Sun-1 and the spacecraft-7 throughout the extended range of its umbilical/tether-5. During the spacecraft's launch, it is envisioned that the DERDS-4 will be fully retracted and stowed within the spacecraft-7. When the spacecraft-7 needs protection outside of Earth's magnetic field, the DERDS-4 will be deployed and moved by its thrusters-26 into the proper distance to establish its magnetic field-3 and create the zone of minimum radiation-6. It is envisioned that this distance from the spacecraft-7 will ensure minimum interference of the generated magnetic field-3 or any plasma-36 (shown in FIG. 5) that gets caught within the magnetic torus, upon the spacecraft-7. It is envisioned that the spacecraft-7 will orient itself so that the bulk of it's on board shielding will face the on-coming solar radiation-2 during CMEs or other high threat radiations.
[0039] FIG. 2: One embodiment of the DERDS-4 is deployed by the spacecraft-7 using a telescopic device-9. The Sun-1 produces the solar radiation-2. The DERDS-4 generates the magnetic field-3 which deflects the incoming radiation-2 and creates the zone of minimum radiation-6 like the Earth's magnetosphere. This is the zone-6 wherein the spacecraft-7 will reside for long durations. As the DERDS-4 is solidly attached by the telescopic device-9, there is no need for thrusters-26 or their associated equipment and supplies on the DERDS-4. It is envisioned that this embodiment of the DERDS-4 will be supplied with electrical power and control of position by the spacecraft-7 through the telescopic device-9. The spacecraft-7 can maneuver to keep the DERDS-4 aligned between the Sun-1 and itself. During the spacecraft's launch, it is envisioned that the DERDS-4 will be fully retracted and stowed within the spacecraft-7. When the spacecraft-7 needs protection outside of Earth's magnetic field, the DERDS-4 will be deployed and telescoped into the proper distance to establish its magnetic field-3 and create the zone of minimum radiation-6. It is envisioned that this distance from the spacecraft-7 will ensure minimum interference of the generated magnetic field-3 or any plasma-36 (shown in FIG. 5) that gets caught within the magnetic torus, upon the spacecraft-7. It is envisioned that the spacecraft-7 will orient itself so that the bulk of its on-board shielding will face the on-coming radiation-2 during CMEs or other high threat radiations.
[0040] FIG. 3One embodiment of the DERDS-4 is as an independent spacecraft which contains a 3-axis thruster control unit-16, a liquid (helium or similar) super cooling refrigeration unit-17, a power supply envisioned as an RTG (radioisotope thermal generator)-18, a gas injector-19 (barium or lithium or the like), alternative embodiment backup power supply umbilical/tether-5 or telescopic device-9 attached to spacecraft-7, communication unit-21, solar particle sensor unit-22, computerized station keeping sensor control unit-23, an electromagnetic generating unit-24. The DERDS-4 generates a strong magnetic field-3 by using the electricity from the power supply-18 applied to a super cooled electromagnet-25 of the electromagnetic generating unit-24. The super cooling refrigeration unit-17 supplies a refrigerant liquid-29 (shown in FIG. 4) in a closed loop system or the like through coils-27 (see FIG. 4) surrounding the electromagnet-25 enabling super conductivity of the electromagnet-25 thereby requiring less electricity for a given needed magnetic field strength. It is envisioned that an embodiment of this DERDS-4 can comprise the gas injector-19 configured to inject a plasma gas into the magnetic field-3 to assist the magnetic field-3 in deflecting certain solar radiations-2 or neutralizing certain unwanted captured solar plasmas-36 (shown in FIG. 5) in the magnetic torus. The DERDS-4 will maintain the proper distance from the spacecraft-7 and ensure a safe zone of minimum radiation-6 by using its solar particle sensor unit-22 and position itself using its thrusters-26 commanded by its computers-90. Further embodiments of the DERDS-4 have no physical connections like the umbilical/tether-5 to the spacecraft-7 once deployed. It is envisioned that the DERDS-4 would be release from its enclosure within the spacecraft-7 when the spacecraft-7 is leaving the protection of the Earth's magnetic field. Once deployed it will remain in the required formation by use of its thrusters-26 and the computer station keeping control unit-23. Very little volume of fuel or thrust would be needed as the DERDS-4 will remain in the required position (due to Newton's laws) unless the spacecraft-7 alters its trajectory. When that occurs the DERDS-4 will generate similar commands by its own solar particle sensor unit-22 or back up commands through the communications unit-21 and or umbilical/tether-5, to continue to provide that required zone of minimum radiation-6 for the spacecraft-7.
[0041] FIG. 4: In this embodiment of the electromagnet-25 within the DERDS-4 is the coil-27 (e.g., copper windings) (or other conducting metal), the internal power unit for electricity RTG-18 (or fuel cell/spaceship provided power or the like), a cooling refrigeration unit-17, and a closed (or open) loop of the refrigerant liquid-29 (helium, nitrogen or the like). In this embodiment, it is envisioned that the refrigerant liquid-29 will reduce the temperature of the electromagnetic metal (iron, nickel, chromium and the like) of the electromagnet-25 down to that temperature in which it will behave as a superconductor (it is envisioned that this would be close to 25-50 Kelvin). In this embodiment, the power required to sustain a zone of minimum radiation-6 will be much reduced. In addition, when there is a significant SEP/CME event or any large blast of radiation-2, the DERDS electromagnet-25 will be able to produce a much stronger magnetic field-3 and through the Lorentz forces keep the radiation-2 well deflected. NASA/ESA (i.e., the National Aeronautics and Space Administration and the European Space Agency) have satellites and Earth bound stations that constantly monitor the Sun-1 and would be able to communicate with the spacecraft-7 and or DERDS-4 directly to warn of ensuing radiation events. The onboard solar particle sensor unit-22 (shown in FIG. 3) would also be able to ramp up the magnetic field-3 when these radiation events arrive.
[0042] FIG. 5: With the DERDS-4 in deployed operation, generating a magnetic field-3 which produces the Lorentz forces to deflect the incoming solar radiation-2 from the Sun-1 (or other radiation source like Jupiter or Saturn for those missions). The zone of minimum radiation-6 is thereby created as the solar radiation-2 has been deflected. It is within the zone-6 where the spacecraft-7 will reside for the duration of its travel, for example, from Earth to Mars and beyond. This zone-6 will allow sustained operation with minimal additional shield required for the spacecraft-7. An important embodiment of this DERDS-4 is that the magnetic field-3 generated, and the possible undesirable plasma-36 trapped within the magnetic torus (like the radiation trapped within the Earth's Van Allen belts) will not be impinging on the spacecraft-7 incurring other undesirable effects on the spacecraft-7.
[0043] FIG. 6: This is FIG. 5 rotated to view the DERDS-4 operation from the side. With the DERDS-4 in deployed operation, generating a magnetic field-3 and a deflection limit-39 which produces the Lorentz forces to deflect the incoming solar radiation-2 from the Sun-1 (or other radiation source like Jupiter or Saturn for those missions). The zone of minimum radiation-6 is thereby created as the solar radiation-2 has been deflected. It is within the zone-6 where the spacecraft-7 will reside for the duration of its travel, for example, from Earth to Mars and beyond. This zone-6 will allow sustained operation with minimal additional shield required for the spacecraft-7. An important embodiment of this DERDS-4 is that the magnetic field-3 generated, and the possible undesirable plasma-36 trapped within the magnetic torus (like the radiation trapped within the Earth's Van Allen belts) will not be impinging on the spacecraft-7 (as seen in prior art) incurring other undesirable effects on the spacecraft-7.
[0044] FIG. 7: In this embodiment, there are there are several DERDS-4 deployed and maintaining formation with one another (much like current quadcopter drones are able with those skilled in the arts) to maintain a magnetic field-3 that deflects incoming solar radiation-2 from a radiation source-47 (like the Sun-1, Jupiter or Saturn and the like). The deflection due to Lorentz forces creates a zone of minimum radiation-6 within which the spacecraft-7 resides for long duration flight. This zone-6 can be made larger or have its shape changed by the repositioning of the formation of DERDS-4. When not needed, the additional DERDS-4 can be re-stowed on board the spacecraft-7, and used as spares for long duration flight. These DERDS-4 can be made smaller in size and have smaller magnetic field generation capability and use their collective magnetic fields-3 for the protection of the spacecraft-7. As the spacecraft-7 goes into less dense solar radiation-2 (in missions to Jupiter or Saturn and beyond and the like) the smaller DERDS-4 might only be needed singly, with the rest dispatched or re-stowed as spares. It is envisioned in this embodiment that the DERDS-4 so deployed can be smaller and have electromagnets-25 that are not boosted in strength by the need for super conductivity and the refrigeration needed. In another embodiment, the DERDS-4 can be deployed in a formation to deflect radiation-2 from multiple sources such as from the Sun-1 and flight near Jupiter or Saturn. One DERDS-4 protects from the solar radiation-2 and the other positions itself to deflect the planetary radiation.
[0045] FIG. 8: In this embodiment, a manned or unmanned base station-50 on a planetary body (such as Mars or one of the moons of Jupiter/Saturn and the like) would need a large zone of minimum radiation-6 and has a DERDS-4 mounted but moveable to be constantly inline between the radiation source-47, such as the Sun-1, and the base station-50. This embodiment of the DERDS-4 is deployed on an ecliptic track-54 which is supported by uprights-55 anchored in the surface-56 of a planet or moon. The base station-50 is protected by the zone of minimum radiation-6 which is generated by the magnetic field-3 of the DERDS-4. The Sun-1 (or other radiation source-47 like Jupiter or Saturn) creates the incoming solar radiation-2 and is deflected by the magnetic field-3 through the Lorentz forces. It is an embodiment of this DERDS-4 to be deployed so that its generated magnetic field-3 does not interfere or impinge on the base station-50. Additionally, any plasmas-36 (shown in FIG. 5) caught within the magnetic fields torus are also kept away from the base station-50. It is envisioned that any manned base station-50 will need long-term electrical power and hence in this embodiment the power would be supplied by a modular nuclear reactor of the molten salt variety (liquid fluoride thorium reactor or the like or numerous RTGs-18). The power requirements for the base station-50 would likely be from 100 kilowatts to 1 megawatt. Additional or back up power could be provided by solar panels-59.
[0046] FIG. 9: This is a view of FIG. 8 rotated 90 to better view the DERDS-4 on the ecliptic track-54 and the DERDS-4 remaining in line with the radiation source-47 and incoming solar radiation-2 and the base station-50. In this embodiment, a manned or unmanned base station-50 on a planetary body (such as Mars or one of the moons of Jupiter/Saturn and the like) would need a large zone of minimum radiation-6 and has a DERDS-4 mounted but moveable to be constantly inline between the radiation source-47 (as it arcs across the horizon) and the base station-50. This embodiment of the DERDS-4 is deployed on an ecliptic track-54 which is supported by uprights-55 anchored in the surface-56 of a planet or moon. The base station-50 is protected by the zone of minimum radiation-6 which is generated by the magnetic field-3 of the DERDS-4. The Sun-1 (or other radiation source like Jupiter or Saturn and the like) creates the incoming solar radiation-2 and it is deflected by the magnetic field-3 through the Lorentz forces. It is an embodiment of this DERDS-4 to be deployed so that its generated magnetic field-3 does not interfere or impinge on the base station-50. Additionally, any plasmas-36 (shown in FIG. 5) caught within the magnetic fields torus are also kept away from the base station-50. It is envisioned that any manned base station-50 will need long-term electrical power and hence in this embodiment the power would be supplied by a modular nuclear reactor of the molten salt variety (liquid fluoride thorium reactor or the like or numerous RTGs-18). The power requirements for the base station-50 would likely be from 100 kilowatts to 1 megawatt. Additional or back up power could be provided by solar panels-59.
