Patent Application
20250038425
The disclosed embodiments relate to structural elements that can be used in conjunction with spacecraft such as satellites.
Many satellites are expensive to launch and lift into orbit. This is due, in part, to the fact that many satellites have complex structures and/or are made from heavy materials that are relatively expensive in terms of their cost-to-deploy. It would be desirable to provide structural elements for a satellite that can help resolve one or more of these issues.
In accordance with some of the embodiments disclosed herein, an apparatus is provided that includes a structural element having a first side including one or more thin film antennas, and a second side, opposite the first side. The first side may be spaced apart from the second side by one or members. The first side may include a plurality of the thin film antennas configured to operate together as a phased antenna array, and the second side may include one or more thin film solar panels and/or one or more thin film batteries. Each thin film solar panel may include a plurality of thin film solar cells. In some embodiments, the thin film antenna(s) can include an electrode that functions as an antenna element. The electrode can be printed on a carrier layer. The second side can include a support substrate that is configured to support the thin film solar panel or could act only as a ground plane for the electrodes. The support substrate is separated from, or separable from, the electrode by a specific separation distance and serves as a ground plane for the antenna element. Because the first side and the second side are flexible, the structural element can be folded or rolled prior to deployment in some embodiments. In one non-limiting embodiment, support members can be implemented as inflatable elements for deploying the structural element upon inflation. That said, other types of supporting members may be included. For instance, in one nonlimiting embodiment, the support members (or other elements) can be made of a shape memory alloy (SMA) material, such as a nitinol wire or other equivalent extendable structure, that can extend from a compact configuration to deploy the structural element and keep the two sides of the structural element, and hence the two thin films, separated at an appropriate separation distance for the antennas to optimally function at their desired frequency. The SMA can be a material having a reactive characteristic that enables it to have a contracted configuration that it is “forced” into while on the ground, and another expanded configuration that it expands into when in space. In some embodiments, the support members can carry an electrical current to stimulate the SMA material.
In another embodiment, an apparatus is provided that includes a structural element having a first side and a second side opposite the first side. In some embodiments, the apparatus is a spacecraft, such as a satellite, and includes one or more structural elements as wing(s) of that spacecraft. In some embodiments, the structural element(s) can be in a folded or rolled configuration prior to deployment (e.g., of the satellite, etc.), and can then be unfolded or unrolled during deployment (e.g., of the satellite, etc.) to deploy the structural element(s).
In the illustrative embodiment, the first side includes a thin film antenna having a carrier layer and a plurality of electrodes of a plurality of antenna elements disposed on the carrier layer. In some embodiments, the electrodes and the carrier layer may be implemented as a flexible thin film structures. For instance, the flexible thin film structure can include a thin film of an electrically conductive material printed on the carrier layer, which is also a thin film.
In the illustrative embodiment, the second side includes one or more solar panels, and a support substrate that is configured to support the solar panel. The support substrate is separable from the electrode on the carrier layer by a specific separation distance, so that in embodiments in which the support layer is electrically conductive or otherwise rendered so, the support layer additionally functions as a ground plane of the antenna when it is deployed. During operation of the antenna, the support substrate is separated from the electrode by the specific separation distance so that the antenna operates at as desired.
The support substrate can be any type of suitable backing material that supports the solar panel. If intended to serve as a ground plane, the support substrate must be electrically conductive, or have a second layer of an electrically conductive material attached to it. In the latter case, the solar panel(s) are disposed on one side of the support substrate and layer of electrically conductive material is attached or otherwise adhered to its other side.
In some embodiments, prior to use, the electrodes on the carrier layer and the support substrate (and hence the ground plane) can be in close proximity or direct contact. When the structural element is in use, the support substrate and the carrier layer separate from one another to achieve and maintain a specific separation distance between the antenna elements on the carrier layer and the substrate layer functioning as the ground plane. In some other embodiments, the support substrate and the carrier layer are separated prior to deployment and use of the structural element. In both cases, maintaining a proper separation distance will achieve desired antenna performance.
In some embodiments, the structural element includes one or more other elements. For example, in some of such embodiments, the structural element includes one or more inflatable elements for deploying the structural element. Upon inflation, the inflatable elements cause the support substrate and the carrier layer to move apart from one another, such as to the specific separation distance. In some of such embodiments, in addition to the inflatable elements, the structural element includes one or more “cross members” disposed along a surface of the structural element. In some of such embodiments, the cross members and/or inflatable elements can be implemented with a curable material, disposed on the support substrate and/or the carrier layer, which hardens upon being exposed to ultraviolet radiation. This increases the rigidity of the structural element.
In another embodiment, an apparatus is provided that includes one or more structural elements that may be in a folded or rolled configuration prior to deployment. Each structural element can include a first side that includes a thin film antenna, a second side opposite the first side, that includes a thin film solar panel, and possibly one or more inflatable elements. The thin film antenna and the thin film solar panel are flexible. The inflatable elements can be used to deploy the structural element upon inflation.
The structural element(s) described above can be implemented as part of a satellite, or other spacecraft, incorporating one or more of the structural elements, for example, as a wing of the satellite. The thin films that are used to carry the antenna(s) and solar panel(s) can provide an ultralightweight solution. Additionally, because the structural elements are made of flexible material, the structural elements can be folded or rolled prior to deployment. Use of lightweight thin film materials results in a small volume, light weight and compact package. This saves significant cost when deploying any apparatus that includes these structural elements. For example, a satellite incorporating one or more of the structural elements can have very low mass, and a relatively high surface-area to volume ratio. This reduces the cost of components, the cost of assembly and manufacturing, and the cost of launching a satellite that includes the structural elements. These features can allow for a simplified and cost-effective deployment of a satellite that includes the structural elements described above.
In some further embodiments, an apparatus in accordance with the present teachings provides a first inflatable satellite, comprising: at least one wing, wherein the wing is structured to be at least partially inflatable, the wing including inflatable portions, and uninflatable portions, the inflatable and uninflatable portions collective defining a first plurality of payload-receiving regions on at least a first external surface of the one wing; a first plurality of antenna elements, the first plurality of antenna elements collectively functioning as a phased-array antenna, wherein the first plurality of antenna elements is received by at least some of the first plurality of payload-receiving regions, and wherein a spacing between the payload-receiving regions of the first plurality thereof defines an operating characteristic of the phased-array antenna; and a processor, the processor for managing operation of the phased array antenna.
In some further embodiments, the first inflatable satellite further comprises solar panels, wherein the solar panels are disposed on a second external surface of the one wing.
In some further embodiments, for the first inflatable satellite having the solar panels, the inflatable and uninflatable portions collectively define a second plurality of payload-receiving regions on the second external surface of the one wing, wherein the solar panels are received by the second plurality of payload-receiving regions.
In some further embodiments, for the first inflatable satellite having the solar panels, the processor manages operation of the solar panels.
In some further embodiments, the first inflatable satellite comprises: a second wing, a first external surface of the second wing comprising a second plurality of payload-receiving regions defined by inflatable and uninflatable portions of the second wing; and a second plurality of antenna elements, the second plurality of antenna elements collectively functioning with the first plurality of antenna elements as a phased-array antenna, wherein the second plurality of antenna elements is received by at least some of the second plurality of payload-receiving regions.
In some further embodiments, the first inflatable satellite comprises a battery.
In some further embodiments, the first inflatable satellite comprises an inflator for inflating the inflatable portions of the at least one wing.
In some further embodiments, the at least one wing of the first inflatable satellite comprises bi-axially oriented polyester film that is at least partially metallized.
In some further embodiments, the first inflatable satellite comprises plural attitude control systems.
In some further embodiments, for the first inflatable satellite comprising plural attitude control systems, a first portion of the at least one wing has a relatively lower albedo and a second portion of the at least one wing has a relatively higher albedo.
In some further embodiments, the at least one wing of the first inflatable satellite comprises plural layers of material, at least one of which layers of material harden upon inflation of the inflatable portions.
In some further embodiments, an apparatus in accordance with the present teachings provides a second inflatable satellite, comprising: a first wing and a second wing, wherein: (a) each of the first and second wings are at least partially inflatable, including inflatable and uninflatable portions, and (b) a first external surface of each of the first and second wings may include a plurality of payload-receiving regions defined, collectively, by the inflatable and uninflatable portions; a plurality of antenna elements, the plurality of antenna elements collectively functioning as a phased-array antenna, wherein the first plurality of antenna elements is received by at least some of the plurality of payload-receiving regions, and wherein a spacing between the payload-receiving regions defines an operating characteristic of the phased-array antenna; and an inflator for inflating the inflatable portions of the first wing and the second wing.
In some further embodiments, the second inflatable satellite comprises an attitude control system.
In some further embodiments, the second inflatable satellite comprises solar panels, wherein the solar panels are disposed on a second external surface of each of the first and second wings.
In some further embodiments, for second inflatable satellite comprising the solar panels, the first and second wings comprises a material having metallized portions.
In some non-limiting embodiments, the structural element 100 can also include supports 106A and 106B that are configured to support the substrate 102 and carrier layer 104. In some embodiments, structural element 100 can be implemented as part of a spacecraft, such as a wing of a satellite. Structural element 100 can reduce the cost of components and assembly, while also reducing the cost to launch a satellite incorporating one or more of these structural elements 100.
As illustrated in
Support substrate 102 can be any type of suitable backing material that supports the solar panels. Depending on the implementation, support substrate 102 can be made of, or can include, an ultra-thin, ultralightweight, and foldable substrate material, such as any of a variety of plastics (e.g., polyethylene, polypropylene, acrylonitrile-butadiene-styrene, etc.). In an illustrative embodiment, support substrate 102 is Mylar® brand stretched polyethylene terephthalate (PTE) film, available from Dupont Teijin Films US and others. Support substrate 102 has a thickness that is typically, but not necessarily, between about 1 and 250 microns.
In addition to supporting solar panels 109-i, in some embodiments, support substrate 102 functions as a ground plane for antenna elements 110-i. While
For example, in some embodiments, support substrate 102 is itself made of an electrically conductive material; alternatively, in some other embodiments, an otherwise non-electrically conductive support substrate 102 can be rendered electrically conductive via additives (i.e., electrically conductive dopants, etc.) to its formulation. In some embodiments, support substrate 102 can be made from DuraLar™ brand metallized film from Grafix Plastics of Maple Heights, Ohio. And in yet some further embodiments, as described later in conjunction with
As illustrated in
In one embodiment, the antenna elements 110-i can be implemented as a very thin, flat “patch” of an electrically conductive material comprising an electrode that, in the illustrative embodiment, is formed on the carrier layer 104. As described in further detail below in conjunction with
In some embodiments, the thin film antenna array 111 may have a thickness of between about 1 and 250 microns. The thin film antenna elements 108-i are flexible and can be bent or rolled without deformation that impacts the ability to operate within antenna parameters they are designed for upon being deployed (e.g., from a folded or rolled configuration). For instance, in one implementation, the antenna elements can have a flexural modulus of between about 35 and about 60 megapascals when fabricated with appropriate dimensions. As such, the thin film antenna elements are highly deformable during storage without impacting desired performance characteristics once they are deployed. The electrodes can be made from a wide variety of electrically conductive materials that are also flexible and are capable of achieving the required performance characteristics in a given implementation. Two non-limiting examples of electrically conductive materials that the electrodes can be made of can include aluminum and silver, but it should be appreciated that other conductive materials, or combinations thereof, can be used. The shape of the electrodes can vary depending on the implementation, as discussed below in conjunction with
In some embodiments, carrier layer 104 comprises an ultra-thin, ultralightweight, and flexible substrate material, such as any of a variety of plastics (e.g., polyethylene, polypropylene, polyethylene terephthalate, acrylonitrile-butadiene-styrene, polyamides, etc.). In some embodiments, the carrier layer 104 is Mylar® brand stretched polyethylene terephthalate (PTE) film, available from Dupont Teijin Films US and others. In one non-limiting embodiment, carrier layer 104 has a thickness in a range of about 1 to about 250 microns.
In the illustrative embodiment depicted in
In some embodiments, the structural element 100 can include one or more inflatable elements for deploying the structural element 100. Upon inflation, the inflatable elements cause the support substrate 102 to be spaced apart from carrier layer 104 by a specific separation distance, attaining the state depicted in
The structural element 100 can include support elements, also referred to as “supports” herein, that enhance structural integrity of the structural element 100. In one non-limiting embodiment, supports 106A and 106B are inflatable elements. In one embodiment, these inflatable elements can be “tubes” of material, such as the same material as support substrate 102 and/or carrier layer 104. In such embodiments, support substrate 102 and carrier layer 104 might not define an enclosed volume. As such, in these embodiments, for some of the space-faring embodiments (e.g., incorporation into a satellite, etc.) of structural element 100, when the structural element is deployed such that the support substrate 102 and carrier layer 104 are spaced apart, there is nothing but the vacuum of space between these layers (except to any minimal extent that portions of support tubes may extend into the region between the layers). In other words, there is neither solid material nor liquid material between these layers. And to the extent there is any gas present, it is no more than is experienced by a space vehicle orbiting at Low Earth Orbit. That is, the pressure is in the range of about 10−4 to about 10−8 Pascals, as a function of orbital height within LEO (approx. 300 to 2000 km above the surface of the Earth).
In some embodiments, a UV-curable resin is applied to supports 106A and 106B, or to a material disposed on top of the supports, which becomes rigid when exposed to sunlight (such as when structural element 100 is deployed in space as part of a satellite). In some other embodiments, supports 106A and 106B are telescoping arrangements of hollow plastic rods, or some other type of actuatable, lightweight, mechanical linkage as known to those skilled in the art.
Although not illustrated in
In some other embodiments, the structural element 100 can also include one or more spacers disposed along a surface of the structural element 100. In one embodiment, the spacers are formed from a curable material that hardens upon exposure to ultraviolet (UV) radiation. Such materials can include UV curable resins, which can be a material in which monomers, oligomers, etc. are solidified through a chain polymerization reaction by ultraviolet rays. The UV curable resin may be applied, for example, as a plurality of spaced-apart, narrow strips (e.g., an inch wide, etc.) on one or both of support substrate 102 and carrier layer 104. Once exposed to sunlight, for example, such regions become rigid and thus provide structural integrity.
As such, structural element 100 can include one or more solar panels 111 that each include plural thin film solar cells 108-i supported on a substrate 102, as well as an antenna array 111 comprising plural thin film antenna elements 110-i supported on the carrier layer 104. In the illustrative embodiment, support substrate 102 and carrier layer 104 comprise an ultralightweight flexible material. Although not depicted in the figures, when implemented as such ultralightweight flexible materials, support substrate 102 and carrier layer 104 can be folded or rolled prior to deployment, and subsequently unfolded or unrolled during deployment, such as in conjunction with the launch and deployment of a satellite incorporating one or more instances of structural element 100. Due to the use of lightweight thin film materials, a satellite incorporating one or more of the structural elements can have very low mass, and a relatively high surface-area to volume ratio. This can reduce the cost of launching and deploying the satellite.
In this one embodiment that is illustrated, the ground plane is implemented by via a thin, electrically conductive layer 202. In some embodiments, layer 202 is a foil of an electrically conductive material, such as aluminum or copper, typically having a thickness in a range of about 25 to about 130 microns. The foil can be printed (using low-cost screen printing) or could be adhered (e.g., vacuum deposited or laminated) to the “underside” (i.e., the side of support substrate 102 that faces carrier layer 104 of support substrate 102). In some other embodiments, the electrically conductive foil is used without support substrate 102. Although depicted in
As illustrated in
In some embodiments, prior to deployment of structural element 100, support substrate 102 and carrier layer 104 are separated by the specific separation distance. However, in some other embodiments, at least initially or prior to deployment of structural element 100, the support substrate 102 and carrier layer 104 may not be separated by this specific separation distance. For example, as previously discussed, prior to deployment, they may be in a folded or rolled state. As previously noted, inflation of the volume created by unitary thin film defining support substrate 102 and carrier layer 104, or inflatable elements, such as supports 106A and 106B, can be used to create the specified separation distance. Additionally, in some embodiments, inflation of the supports facilitates deployment of structural element 100.
Antenna elements 110-i and the electrodes of those antenna elements can have any one of variety of shapes (e.g., spiral, rectangular, square, circular, include cut outs, etc.) and sizes. As non-limiting examples, the electrode may have a spiral shape (e.g., a circular or rectangular spiral), a spherical shape, a flat planar shape, etc. The antennas that make up the array can be patch antennas that have any of these shapes, and can thus be characterized as one or more of a spiral antenna, a spherical antenna, a patch antenna, etc. depending on the implementation. In the embodiment illustrated in
In the illustrative embodiment, antenna elements 110-i can be printed on carrier layer 104 utilizing any known methods. For example, in some embodiments, antenna elements 110-i can be formed using an electrically conductive ink that is printed or stamped onto carrier layer 104. In some embodiments, the electrically conductive ink can include a polymer thick film (PTF) containing electrically conductive material, such as silver flakes or graphite. Any formulation that provides an electrically conductive ink, as known to those skilled in the art, may suitably be used. The thickness of such printed antenna elements 110-i is typically in a range of about 1 to about 250 microns. In some other embodiments, a very thin piece (e.g., about 1 to about 250 microns) of electrically conductive material such as aluminum, copper, silver, etc., can be fabricated (e.g., cut into pieces using a die cutter, laser cutter, etc.) to have a desired shape and size, and can then be adhered or otherwise attached to carrier layer 104.
As previously noted, antenna elements 110-i must be either directly or indirectly electrically coupled to signal-processing electronics, as is known in the art. In the illustrative embodiment depicted in
In the illustrative embodiment, signal-processing electronics 112-i may include radio frequency front end (RFFE) circuitry for amplifying an RF signal radiated from each antenna element 110-i, and for amplifying an RF signal that is received by each antenna element 110-i. In other embodiments multiple antenna elements may be grouped together to create a sub-array and such sub-arrays would be connected as noted to the signal processing electronics. It is desirable for this circuitry to be as close to antenna elements 110-i as is practical. In the illustrative embodiment, and as illustrated in
In some embodiments, multiple antenna elements 110-i, which are connected to multiple instances of signal-processing electronics 112-i, are coupled to one another to provide a phased-array antenna.
The greater the number of antenna elements 110-i, the larger the physical size of the antenna and the more directivity and/or gain the antenna will have. Directivity is an important end-state metric used to describe the focusing power of an antenna, and higher gains are often highly desirable. Thus, a goal for many applications is to have an array with as many antenna elements as possible to create the highest directivity.
In some embodiments, signal processing electronics 112-i may also include (i) a modem and (ii) other circuitry to modulate or demodulate a signal into a signal that may be stored on memory, connected to a computer for data transfer, or any other use.
Each antenna element 110-i may include feed system, which electrically couples it to signal processing electronics 112-i. The feed system can be, for example and without limitation, a microstrip line, coaxial probe, aperture coupled feed, or proximity coupled feed, and it is within the capabilities of those skilled in the art to design a feed system for embodiments of the invention. In some embodiments, the feed line comprises electrically conductive ink or foil. In some embodiments this feed system may be coupled with one or more of the support structures to maintain the distance between the element 110-i and 102.
Because the structural element 100 is flexible and highly compactable, it can rolled or folded in multiple directions and multiple times as a function of the overall size of support substrate 102 and carrier layer 104. For example, in some embodiments, structural element 100 can be compacted to a thickness of less than 0.25 inches, in a “stow” state. Because of its construction, structural element 100 has negligible mass in addition to stowing to a very small size. Yet, in fully deployed mode, antenna array 111 incorporated therein will exhibit very high directivity and gain.
As previously noted, structural element 100 may form part of a satellite, such as satellite 500 illustrated in
Satellite 500 further includes pouch 530, which is centrally located between structural elements 100. Pouch 530 receives battery 532, and processor(s) and associated electronics 534. The processor may include software for managing various satellite functions, including, without limitation, management of the solar panels 109 and battery 532, control functions related to deployment of structural elements 100, and telecommunications management. Cover 536 serves as a carrying board for processor/electronics 534 and battery 532. Additionally, cover 536 is usable for attaching satellite 500 to a dispenser, etc., during launch. In some embodiments thin film batteries may be embedded into, or included on either flexible structures 102 or 104.
When in space, such as in low Earth orbit, structural element 100 is normally oriented so that the antenna array (not illustrated in
In some embodiments, support substrate 102 and carrier layer 104 are treated to alter albedo (i.e., reflectivity) at select regions. With such regions of relatively lower and relatively higher albedo, the temperature of the satellite can be controlled by altering the attitude of satellite 500 (via the aforementioned attitude control systems). More particularly, if the temperature of the satellite drops based below a desire temperature based on the attitude of the satellite and its resulting orientation with respect to the sun, the satellite's attitude is then altered to increase the exposure of relatively lower albedo regions of the wing to the sun. This will cause the satellite to absorb more energy, such that the desired temperature is maintained. Conversely, if the temperature of the satellite increases due to the attitude of the satellite and its resulting orientation with respect to the sun, the satellite's attitude is altered to increase the exposure of the relatively higher albedo regions of the wing to the sun. This will cause the satellite to reflect more energy, such that the desired temperature is maintained.
Referring to
In the illustrative embodiment, satellite 600 includes two igniters 646. The igniters ignite one or more propellants to generate a gas for inflating the appropriate portions of satellite 600. If plural propellants are used, the propellants can be ignited in series, or in parallel. As a function of size, or construction, more than two igniters 646 can be used. For example, in some embodiments, one or more igniters are used to inflate stiffener ribs 648. Ignition materials for igniters 648 include nitroguanidine, phase-stabilized ammonium nitrate, or other nonmetallic oxidizers, and a nitrogen-rich fuel.
In some other embodiments, a small pressure vessel that is mounted to the satellite is filled with a fluid at sea-level pressure, and releases fluid to maintain the satellite at a certain pressure. A relief valve can be fluidically coupled to the inflatable regions of satellite 600 to release fluid to address over-pressure situations, as may occur in higher heat environments. In such embodiments, the life of the satellite would be limited to the amount of fluid stored on the satellite.
In some additional embodiments, a pair of one-way valves is mounted in a pressure vessel that is located either internal or external to satellite 600. In some embodiments, the pressure vessel has a small compressor motor for compressing the fluid from the satellite (and through one of the one-way valves) into the pressure vessel. This would occur only in extreme heat, and when the pressure in the satellite is above the nominal operation pressure. When the satellite is in a cold environment, the one-way valve controlling flow into the inflatable regions of the satellite releases fluid to increase the satellite's pressure to the nominal operating pressure.
In yet some further embodiments, a method that avoids the use of valves, pressure vessels, and external components is used. Because the pressure on the ground is approximately 100,000 Pa, while the pressure in space the pressure is approximately 1.322×10−11 Pa, gas inside the inflatable satellite will naturally expand with altitude. Prior to launch, the satellite is fully deflated and packed in such a way as to prevent expansion. A precise amount of fluid is injected into the inflatable satellite. The fluid, which could be air, nitrogen or other fluid, will then increase the pressure within the satellites as they move to lower (ambient) pressure environments. In some embodiments, one or more one-way release valves can be incorporated to prevent over inflation.
It is of course important to carefully measure the fluid in satellite 600 so that the expansion of the fluid maintains the correct amount of pressure inside the satellite to maintain appropriate rigidity, while avoiding overpressure that might cause it to explode or leak gas. As satellite 600 moves through various altitudes, the external pressure will vary, and, additionally, changes in the temperature of the satellite will have a dramatic impact on the satellite's internal pressure. As such, material selection for the satellite, and the design of seams are important considerations, both of which are within the capabilities of those skilled in art.
In the illustrative embodiment, satellite 600 includes pouch 630, centrally located between structural elements 100′, which receives battery 632 and processor(s) and associated electronics 634. The processor may include software for managing various satellite functions, including, without limitation, management of the solar panels 108-i and battery 632, control of inflation, and telecommunications management. Cover 636 serves as a carrying board for processor/electronics 634 and battery 632. Additionally, cover 636 is usable for attaching satellite 600 to a dispenser or other object during launch. The pouch can be inflatable, or noninflatable (or inflatable but remain uninflated).
In some embodiments, satellite 600 includes plural attitude control systems (not illustrated) that are placed along structural elements 100′ in order to alter/maintain the satellite's attitude. In some embodiments, the attitude control systems are magnetically actuated in conjunction with the magnetosphere.
Summarizing, the apparatus comprising the structural element, as depicted and described, includes: (i) a first side comprising a thin-film antenna, and (ii) a second side comprising a thin-film solar panel. Embodiments of the apparatus comprising the structural element may further comprise one or more of the following features, in any (non-conflicting) combination, among other features disclosed herein:
It is to be understood that the disclosure describes a few embodiments and that many variations of the invention can easily be devised by those skilled in the art after reading this disclosure and that the scope of the disclosed embodiments is to be determined by the following claims.
This application claims priority from U.S. provisional patent application Ser. No. 63/293,616, filed Dec. 23, 2021, and which is incorporated by reference herein in its entirety.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2022/054005 | 12/23/2022 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 63293616 | Dec 2021 | US |
