SYSTEMS AND METHODS FOR RADIANT GAS DYNAMIC MINING OF PERMAFROST

Abstract

Systems and apparatus are disclosed for mining the permafrost at the landing sites using radiant gas dynamic mining procedures. The systems can comprise a rover vehicle with an integrated large area dome for cryotrapping gases released from the surface and multi-wavelength radiant heating systems to provide adjustable heating as a function of depth. Various antenna arrays and configurations are disclosed, some of which can cooperate for a specific aiming or targeting effect.

Claims

1. (canceled)

2. A heating system for use in a rover vehicle, comprising: a plurality of phased wire dipole antennas configured to be installed on an interior surface of a dome of the rover vehicle, wherein each of the plurality of phased wire dipole antennas is configured to generate a microwave beam to heat a surface of a landing site of the rover vehicle to sublimate ice within the landing site, and wherein the plurality of phased wire dipole antennas are arranged such that each of the microwave beams converges at a region below the surface of the landing site.

3. The heating system of claim 2, further comprising: a plurality of infrared heaters configured to warm the surface of the landing site.

4. The heating system of claim 2, further comprising: a plurality of radio frequency (RF) dielectric heating probes configured to warm the surface of the landing site.

5. The heating system of claim 4, wherein plurality of radio frequency (RF) dielectric heating probes are further configured to be deployed into holes in the surface of the landing site to heat a subsurface of the landing site.

6. The heating system of claim 2, wherein the plurality of phased wire dipole antennas are connected by a plurality of wire transmission lines to a common feed point.

7. The heating system of claim 6, wherein each of the wire transmission lines has a length that is about one-half of an operating wavelength.

8. The heating system of claim 2, wherein each of the plurality of phased wire dipole antennas has a length that is about one-half of an operating wavelength.

9. The heating system of claim 2, wherein the phased wire dipole antennas are arranged into a plurality of broadside arrays.

10. The heating system of claim 9, further comprising a microwave source connected to each of the broadside arrays via a corresponding parallel wire transmission line.

11. The heating system of claim 10, further comprising a plurality of shunt tuning devices configured to tune coupling efficiency between the microwave source and the broadside arrays.

12. A phased wire dipole antenna array for use on an interior surface of a dome of a rover vehicle, the phased wire dipole antenna array comprising: a plurality of phased wire dipole antennas configured to be installed on the interior surface of the dome, wherein each of the plurality of phased wire dipole antennas is configured to generate a microwave beam to heat a surface of a landing site of the rover vehicle to sublimate ice within the landing site

13. The phased wire dipole antenna array of claim 12, wherein the plurality of phased wire dipole antennas are connected by a plurality of wire transmission lines to a common feed point.

14. The phased wire dipole antenna array of claim 13, wherein each of the wire transmission lines has a length that is about one-half of an operating wavelength.

15. The phased wire dipole antenna array of claim 12, wherein each of the plurality of phased wire dipole antennas has a length that is about one-half of an operating wavelength.

16. The phased wire dipole antenna array of claim 12, wherein the phased wire dipole antennas are arranged into a plurality of broadside arrays.

17. The phased wire dipole antenna array of claim 16, wherein each of the broadside arrays is configured to be connected to a microwave source via a corresponding parallel wire transmission line.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0025] FIGS. 1A and 1B are schematic illustrations of an embodiment of an apparatus or system for implementing RGD mining, including the use of radiant gas dynamic (RGD) mining implemented in a large scale rover design.

[0026] FIG. 2 is an illustration of one embodiment of a cylindrically oriented 1 to 8 waveguide power dividing network which splits power from the magnetron to the 8 WGSA focusing panels which direct the power into the permafrost.

[0027] FIGS. 3A and 3B illustrates the basic configuration of a dipole array in accordance with aspects of this disclosure.

[0028] FIG. 4 illustrates the installation of a plurality of 40-element dipole arrays which are curved and installed along the inner surface of a spherical rover dome in accordance with aspects of this disclosure.

DETAILED DESCRIPTION

[0029] Aspects of this disclosure relate to a shadowed polar ice (SPICE) harvester which can be used an in situ dome. Radian Gas Dynamic (RGD) mining uses a combination of microwave, radio frequency (RF), and infrared or optical heating inside an insulated dome that can be carried on a rover along with vapor capture equipment and water tanks. A rigid dome can be heated on the interior and insulated to prevent heat loss and water collection in unwanted locations. Aspects of this disclosure further describe testing apparatus and methods (e.g., cryo shroud, cryogenic vacuum, and valve and seal cycle testing) to prepare for delivery and deployment of such systems. Some dome embodiments use a 5 kW S-band magnetron power supply for 100 kg class water harvesting and a continuous flow cryobelt.

Rover Vehicle With Microwave Focusing Panels

[0030] With reference to FIGS. 1A and 1B, the various features of one embodiment of an RGD mining apparatus and system will be described. These features may be incorporated into a roving vehicle or other mining apparatus or system. In this embodiment, with reference to FIG. 1A, the upper illustration shows the bottom perspective view of the dome structure of the mining apparatus, while the lower illustration is a side view. The various components illustrated in FIG. 1A are as follows: [0031] 1. Microwave Waveguide Network [0032] 2. Focusing Microwave Panels (Eight) [0033] 3. Microwave Wavefronts [0034] 4. Simulated Regolith or Permafrost [0035] 5. Simulated Surface Roughness [0036] 6. High Power RF Coax Cables [0037] 7. RF Dielectric Heating Probes (Six) [0038] 8. RF Wavefronts [0039] 9. Sublimated Water Vapor [0040] 10. Radiant Infrared Heaters (Four) [0041] 11. Infrared Radiation [0042] 12. Gas Directing Dome Structure [0043] 13. Surface Conforming Skirt Mechanism [0044] 14. Resistive Patch Heaters (Many) [0045] 15. Stainless Steel Cryobelt [0046] 16. Liquid Nitrogen Cooled Rotary Drum [0047] 17. Water Vapor Collected as Frost [0048] 18. Direction of Rotation [0049] 19. Follower Closures [0050] 20. Cryobelt Radiant Heater [0051] 21. Roughing Pump Duct [0052] 22. Vacuum System Port

[0053] With reference to FIG. 1B, the upper left illustration shows a rover design in which foldable drive wheels and a stackable design allow the rover to be integrated as a payload in a space craft, such as the New Glenn. The upper right illustration shows a bottom perspective view of the unfolded, deployed rover, including the dome structure, while the lower two illustrations show two side views with the dome lowered to contact the surface and raised away from the surface.

[0054] The dome is configured to support the eight microwave focusing panels, also referred to as waveguide slotted arrays (WGSA); the power divider waveguide network; the Cryobelt vapor collection assembly; and the skirt assembly that reduces the area for volatiles to escape at an efficiency level modeled and accounted for in Table 1 of US Patent Application Publication No. 2020/0240267. The design of the embodiments of FIGS. 1A and 1B can be an assembly based on readily-obtainable materials and processes to the greatest extent possible. Materials are preferably functional at cryogenic temperatures. The skirt assembly can avoid cyclic flexing and associated fatigue risk. Preferably, the skirt assembly also provides that any leakage area between the dome and the mined surface (e.g., lunar or Martian surface) be much less than the cryopump area. Preferred structures of the dome can have multiple surfaces (e.g., have an octagonally shape) and a sufficiently supportive and protective design (e.g., aluminum walls). For example, preferred designs surround and supports the eight WGSAs and the power divider network as shown in FIGS. 1A and 1B.

[0055] With reference to FIG. 2, in some embodiments the arrays and the waveguide used in the power divider network are dip brazed Aluminum structures using COTS WR340 waveguide components and dimensions. Preferred embodiments of the antennae and the waveguides are sized to operate in the TE10 mode. Waveguide straight sections and bends can be dip brazed together into individual pieces, and individual pieces can be attached together using standard waveguide bolted flanges. A view of an example divider assembly is also shown in FIG. 2.

[0056] A microwave design that can be used with the described structures comprises a multi-sided (e.g., octagonal) array comprising elements in the near field of each other as shown in FIG. 1A. The electro-magnetic fields radiating from the elements can be focused slightly below a mined surface (e.g., within a 0.03 m.sup.3 volume approximately 20 cm below a mined surface, such as of the moon or mars). In some embodiments, the rectangular waveguide elements are spaced one-half wavelength apart. In the illustrated embodiment, the rectangular waveguide elements are square (e.g., 1212 cm square) and can be excited by a TE10 mode with a given complex amplitude. The array can comprise multiple (e.g., eight) rectangular arrays (e.g., 34 arrays) of these square, open-ended waveguide elements that are tilted downward at about 15 degrees to facilitate focusing of the beam as shown in FIGS. 1A and 1B.

[0057] Apertures can be located at the ends of lenses (which can comprise phase shifters used to adjust the phase for each element). WGSAs with lenses can thus be used to good effect. Associated complex amplitude and phase coefficients are configured to be adjusted using a conjugate phase approach. To determine the focusing capability with the conjugate phase approach, the fields can be computed on a plane below the array (e.g., 20 cm below) as the array can be focused at different points along the Z-axis of the array. Phase shifting of the multiple (e.g., 8) panels can effectively direct the microwave energy down and toward the center of the system. The power density profile suggests that the focusing system can deliver nearly all 15 KW into a small region. Such a focusing process can help improve heating at given depth, thereby driving vapor upward into the dome system.

[0058] At least two microwave frequencies, 915 MHz (L-Band) and 2.45 GHz (S-Band), are well suited for penetrating and volume heating of soils. Terrestrial uses of these frequencies include cooking, curing, and drying of agricultural and many manufactured products. Magnetrons can be used as power sources in these two bands because of their high electrical efficiency. DC to microwave conversion efficiency using magnetrons are about 80% at S-band and 90% at L-Band. L-Band commercial magnetron sources are available at continuous output power levels up to 140 KW. At 2.45 GHz, the highest power tube currently available can produce 15 kW of continuous output power. In certain embodiments, a 6 kW S-Band microwave system with magnetron, autotuner and waveguide feed system has been shown to be effective. In another embodiment, a 15 kW system is proposed.

[0059] Moving from microwave design to mechanical design, the skirt assembly can include 96 PTFE (Teflon) U-channels attached to the wall of the dome with two flathead screws each, through slots symmetrically located about the center and long enough to absorb the relative movement due to the delta CTE between the wall and the channel. In some embodiments, 48 movable skirt segments can each be 10 cm wide by 30 cm tall by 0.5 cm thick and can slide +/6 centimeters up and down, guided by the U-channel. Skirt segments can be notched along a portion of their height to create captive features, and the fastener centered along the U-channel height can act as a stop preventing the skirt segments from sliding out of the U-channels.

[0060] In summary, FIGS. 1A, 1B, and 2 illustrate an embodiment of a rover vehicle with eight microwave focusing panels that are further described as waveguide slotted arrays (WGSA). A focused converging microwave beam can be projected downward from the rover dome into lunar regolith. The microwave beam is used to heat the frozen regolith in order to melt and volatize frozen water or other trapped volatile chemicals. The liberated vapors are collected on a cryobelt as part of the vapor collection system.

Wire Antenna Dipoles for Rover Vehicles

[0061] Another embodiment of the present disclosure is illustrated schematically in FIGS. 3A, 3B, and 4. In these embodiments, the WGSA panels and associated waveguide phasing networks have been replaced by a broadside phased array of dipole antennas. FIGS. 3A and 3B illustrate the basic configuration of a dipole array in accordance with aspects of this disclosure. Waveguides of the embodiment of FIGS. 1A, 1B, and 2 have been replaced by lighter and smaller wire antennas that are connected by open-wire transmission lines.

[0062] FIG. 3A illustrates an array of 16 wire dipole antennas is connected by wire transmission lines to a common feed point in accordance with aspects of this disclosure. Referring to FIG. 3A, a plurality of wire antenna dipoles 31 are about one-half wavelength long at the microwave operating wavelength. For the common microwave frequency of 2.45GHz, the dipoles are approximately 6 cm in length. Each of the dipole antennas 31 is connected at one of its ends by a wire transmission line segment 32 which is also about one-half wavelength long. The various dipoles 31 are connected by 2-wire transmission lines 32a and 32b to common feed points 33a and 33b. The interconnected dipoles 31 of FIG. 1A constitute a basic array of 16 dipoles which can radiate a microwave beam in the broadside direction (e.g., out of the page).

[0063] FIG. 3B illustrates five arrays of 16 dipole antennas connected between their common feed points to produce a broadside array of 40 dipoles in accordance with aspects of this disclosure. That is, FIG. 3B illustrates how the basic broadside arrays of FIG. 3A may be combined into larger arrays. In the particular embodiment of FIG. 3B, the larger array comprises an array of 40 dipoles. The illustrated array measures approximately 50 cm wide by 40 cm high in certain embodiments.

[0064] FIG. 4 illustrates the installation of a plurality of 40-element dipole arrays which are curved and installed along the inner surface of a spherical rover dome in accordance with aspects of this disclosure. With reference to FIG. 4, the 40-element dipole arrays 37 may be installed on the inner spherical surface of a rover dome 6. The plurality of dipole arrays can be used to project powerful focused microwave beams into the lunar regolith. The region below the surface is heated by the focused microwave beams, which drives volatile gases upwards to be collected (e.g., by rover cryotraps).

[0065] In this figure, a high-power microwave source 34 is connected to the array 37 by a parallel wire transmission line 32. A plurality of shunt tuning devices 35 can be adjusted for maximum (or to improve) coupling efficiency of microwave power between the source 34 and the antenna array 37. Each of the antenna arrays 37 launches a converging microwave beam 39 into the lunar regolith 38. The multiple converging beams 39 overlap in a region 40 below the surface of the regolith. The heated region 40 then drives volatile gases upwards to be collected by the rover cryotraps.

[0066] In this manner, the dipole broadside arrays 37 can deliver the same subsurface heating performance as the waveguide slotted arrays (WGSA) of FIGS. 1A, 1B, and 2 but with a lower weight and a more volumetrically compact design. The savings in weight and volume increase proportionally for larger rover domes and for microwave sources with longer wavelength.