In recent years, several innovative companies around the globe have pursued a strategy of providing global coverage with large-number small-satellite constellations. These constellations seek to provide several different types of applications, including global internet availability, global commercial imaging capability, and global military situational awareness. A common requirement for these constellations, which may number in the hundreds of SmallSats, is the ability to communicate with the ground and with each other in a virtual network. Since the satellite orientation at deployment is varying and may be unpredictable, the antennas used to send and receive signals preferably operate omnidirectionally.
Typical antennas are rigid structures made from conductive metals. The nominal size of the antenna is conventionally on the order of the radio wave being received, which for S-band frequencies can be as much as 10-15 centimetres. This is the size of a typical U CubeSat that must also contain electronics, cameras, a power source, and other components. This poses logistical problems for the satellite that would preferably be stowed during launch and deployed when in orbit. Such stowable configurations of conventional antennas are difficult given their material construction limitations. As a result, antennas used for small satellites are generally very limited in size. Therefore, the beam pattern of an antenna may be comprised or narrowed to reduce size.
Antennas and satellites described herein may include a unique Shape Memory composite (SMC) material in the construction of an antenna design. Exemplary embodiments may include an omnidirectional antenna design.
Exemplary embodiments disclosed use shape memory composite material to construct Compactible antennas for free space communications between spacecraft, and ground stations or other spacecraft.
Exemplary embodiments include an antenna made of shape memory composite material. Exemplary embodiments permit the transition of the antenna from a deformed, stowed shape to a deployed shape. The deformed shape may be collapsed or otherwise define a smaller dimension or volume for storage and transport. In an exemplary embodiment, the shape memory composite material may have a remembered configuration such that the deformed shape retains energy to deploy or transition the shape memory composite to the deployed shape without outside intervention or applied force. For example, a mechanism may be used to impose an outside force to retain the shape memory composite material in the deformed configuration. Upon removal of the applied force, the shape memory composite material deploys.
In an exemplary embodiment, the shape memory composite material may be conductive to act as an antenna. The shape memory composite material may be conductive through material selections of the fibers, the resin to retain the fibers, additives to the fibers and/or resin, coatings, and other methods described herein. The fibers may be conductive. The resin may be conductive. Metallic or conductive powders, additives, or fillers may be added to the resin or filler between fibers. Metallic strands may be incorporated with or used exclusively as the composite fibres. Thin metallic foils may be wrapped or used to cover all or part of the members created by the shape memory composite material. Conductive paint or other coatings may be applied to all or part of a surface of the component created by the shape memory composite material.
The following detailed description illustrates by way of example, not by way of limitation, the principles of the invention. This description will clearly enable one skilled in the art to make and use the invention, and describes several embodiments, adaptations, variations, alternatives and uses of the invention, including what is presently believed to be the best mode of carrying out the invention. It should be understood that the drawings are diagrammatic and schematic representations of exemplary embodiments of the invention, and are not limiting of the present invention nor are they necessarily drawn to scale.
Exemplary embodiments may use a dynamically deformable material as a support and deployment structure for supporting an electrically conductive material to create an antenna form geometry.
In an exemplary embodiment, the dynamically deformable material may include an electrically conductive material for creating an antenna form.
In an exemplary embodiment, the dynamically deformable material may not include an electrically conductive material, but may support an electrically conductive material in a desired form.
Exemplary embodiments may use an envelope contained around and/or supported by the dynamically deformable material. The envelope may be gas impermeable or semi-gas impermeable to inflate upon deployment of the antenna. The envelope may be inflated to assist the antenna to transition to a deployed configuration. The envelope may be inflated to release the antenna from a stowed configuration. The envelope may act as a substrate to support an electrically conductive material to create the antenna form.
Although embodiments of the invention may be described and illustrated herein in terms of specific antenna configurations, it should be understood that embodiments of this invention are not so limited, but are additionally applicable to different antenna configurations. Exemplary embodiments also disclosed include different combinations of the dynamically deformable material as a support, as including the conductive material for the antenna, as the spring support for deploying the antenna from a stowed configuration, as the support for an envelope that can support a conductive material for creating the antenna shape, as a support for the deployed configuration, and any combination thereof. Exemplary embodiments may include alternative features, such as a tear away surface, removable retraction or stowage material or cords, an envelope, one or more antenna shapes, one or more sleeves or envelopes, one or more support infrastructures made from shape memory material, a hub, one or more inflation mechanisms. Any feature, component, configuration, and/or attribute described for any one example may be used in combination with any other example. Accordingly, any step, feature, component, configuration, and/or attribute may be used in any combination and remain within the scope of the instant description. Features may be removed, added, duplicated, integrated, subdivided, or otherwise recombined and remain within the scope of the instant disclosure. The exemplary embodiments described herein are provided for sake of example only. Therefore, any antenna configuration may be used with or without an envelope according to embodiments described herein. Any antenna configuration may be used with or without a tear away or break away retention device according to embodiments described herein. Any antenna configuration may be used with an inflation mechanism according to embodiments described herein.
Although exemplary embodiments are shown and described with respect to creating omnidirectional antennas for free space communications between ground stations and other spacecraft, other applications are within the scope of the instant disclosure. For example, directional antennas are within the scope of the instant disclosure. Other uses are also within the scope of the instant application and not just space communications between spacecraft.
If constructed from copper or some other conductive metal, the antenna is rigid and its “footprint” cannot be reduced for stowage during launch. Exemplary embodiments described herein include shape memory components that can dynamically deform. Dynamic deformation as described and used herein includes non-structured deformation for stowage and/or deployment. Exemplary embodiments of the shape memory component may flex and bend or otherwise deform along a length of the shape memory component. The deformation may be along an entire length or portion of the shape memory component. The dynamic deformation can be folded into a smaller configuration, stowed in the SmallSat or other storage compartment, and released to expand to a deployed configuration. In an exemplary embodiment, the shape memory component comprises a remembered configuration. During use, exemplary embodiments may include a stowed configuration where the shape memory component may be retained through application of an outside force in the deformed shape. Upon removal of the outside force, such as a deformation force, the shape memory component expands to a remembered configuration. The remembered configuration may be the deployed configuration. Deployment may therefore be straightforward for a shape memory component structure since it merely requires that the mechanism constraining the shape memory component (such as the antenna) in the folded or stowed configuration be removed.
In an exemplary embodiment the shape memory component may comprise a shape memory composite. The shape memory composite may comprise fibers retained in a matrix or resin. The shape memory component may be conductive. To improve the antenna gain, the conductivity can be increased, such as by adding: (1) metallic powders to the matrix of the composite; (2) thin metallic foils wrapped around the shape memory composite component creating the antenna; (3) conductive paint applied to the surface of the shape memory component; and combinations thereof.
An exemplary shape memory composite material includes a base material of one or more of carbon fiber, Vectran, Kevlar, fiberglass, glass fibers, plastics, fiber metal. The base material may comprise strands. The stands may be generally aligned along a length of the structure, may include one or more aligned arrangements, may be wound or helically positioned, may be woven, or any combination thereof. The shape memory composite material may include a matrix around and/or between the base material. The matrix may be silicone, urethane, or epoxy. Exemplary shape memory composite materials are described in co-owned patent application U.S. Patent Publication No. 2016/0288453, titled “Composite Material”. Exemplary embodiments include a high strain material to permit deformation. High strain materials generally have the capability to strain beyond 3% and not enter plastic deformation. In other words, the material may yield beyond 3%.
In an exemplary embodiment, the shape memory composite material includes a volume fraction ratio of fiber-to resin that may be controlled to achieve a desired shape memory retention even after long-term storage in a folded/packaged state. An exemplary fiber-to-resin volume fraction ratio is from 52 to 65, namely 52 percent to 65 percent fiber or 48 percent to 35 percent matrix or resin. The average fiber-to-matrix ratio is about 58 percent. The fibers may be carbon, Kevlar, Vectran, nylon, or otherwise described herein and the resin may be urethane, silicone or epoxy or otherwise described herein as the matrix.
In an exemplary embodiment, the member composed of the shape memory composite material may be conductive to define an antenna shape. All of a portion of the component may be conductive. The component may be conductive by incorporating a conductive material into the shape memory material. The component material may include a metallic powder, coating, wrapping, sheet, film, paint, strands, or combinations thereof. The conductive material may be in the fiber, resin, on the surface of the fiber, on the surface of the component material, or a combination thereof In an exemplary embodiment, the shape memory composite component is conductive to create the antenna shape by wrapping the component in a thin sheet of copper. The copper sheet may be adhered or otherwise coupled to an exterior surface of the shape memory composite material shaft.
In an exemplary embodiment, the antenna structure 40, 50, 60, 70, 80, 90, 100 may be supported by a support structure 46, 56, 66, 76, 86, 96, 106. The support structure 46, 56, 66, 76, 86, 96, 106 may be conductive or non-conductive. The support structure may provide other features for the antenna, such as shape support, signal effects, directional effects, storage retention, deployment actuation, or combinations thereof. In an exemplary embodiment, the support structure comprises a thin film that is flexible. The support structure may therefore be collapsible and/or deformable in the same or similar way as the antenna structure. The support structure may be a dielectric membrane. The support structure may be a fabric, mesh, or sheet. The support structure may be Kapton, Mylar, Teflon, cotton, or other dielectric and/or non-conductive material. Although shown as included with only a subset of the exemplary embodiments, the support structure may be used with any antenna configuration described herein. The support structure may be coupled to the shape memory composite material, the conductive components, other components of the antenna, or combinations thereof.
In an exemplary embodiment, the support structure 46, 56, 66, 76, 86, 96, 106 defines a thin surface. The support structures 46, 56, 66, 76, 86, 96, 106 may comprise flexible materials coupled to any combination of other additional support structures, support structure, shape memory composite components, and/or conductive components. In an exemplary embodiment, the support structure 46, 56, 66, 76, 86, 96, 106 defines a gas impermeable or semi-impermeable surface. The support structure may define an interior cavity. The support structure may be positioned to create a continuous and gas-impermeable surface around the interior cavity. In an exemplary embodiment, as described more fully herein, the support structure may be inflatable. In an exemplary embodiment, the support structure may be inflatable to assist in the deployment of the antenna structure. The support structure may be configured to vent the inserted fluid after inflation and/or may be configured to retain the fluid for a period of time after inflation. A gas impermeable surface may therefore include a surface that retains sufficient gas in order to assist with deployment and initial inflation but may vent gas thereafter.
Exemplary embodiments may also use a combination of dielectric and/or non-conductive layers to create complex antenna configurations with leads that may overlap each other but may or may not contact one another. For example, a first cylindrical support structure may be used with conductive material one either interior or exterior surface. A second cylindrical support structure may be positioned over or inside the first cylindrical support structure enclosing conductive material between the first layer and the second layer. Another side of the second cylindrical support structure on a side opposite the side contacting the enclosed conductive material may also include conductive material. The antenna may therefore include a first conductive layer defining a first pattern, a non-conductive and/or dielectric layer, a second conductive layer defining a second pattern. The antenna may include additional combinations of conductive layers and non-conductive and/or dielectric layers. The different layers may be used to create complex antenna configurations and different conducting patterns that may be electrically coupled and/or electrically isolated.
As illustrated in
As illustrated in
In an exemplary embodiment, the shape memory composite material may be integrated with the support structure. The shape memory composite material may create the support structure.
In an exemplary embodiment, the shape memory composite material may create a framework to which the support structure is attached. As described herein the shape memory composite may be within or coupled along its entirety to the support structure. The shape memory composite components may also be coupled to the support structure along a portion or point of the shape memory composite component. A combination of support structure and/or shape memory composite components may be used.
In an exemplary embodiment, a conductive material may be incorporated with the shape memory composite component. The conductive material may be as described herein within the shape memory composite and/or on a surface thereof.
In an exemplary embodiment, the conductive material may be support by or on the support structure. The conductive material may be positioned on the support structure in any fashion, such as being on a surface of the support structure, within the support structure, and/or coupled to the support structure. In an exemplary embodiment, the conductive material may be painted, coated, positioned on, woven into, or otherwise coupled to the support structure. For example, the conductive material may include thin sheet metal of copper. The sheet metal may be patterned and positioned on the surface of the support structure and coupled thereto. As another example, the conductive material may be fibers of thin copper wires. The fibers may be woven into or coupled to the support structure.
In an exemplary embodiment, additional structures may be used to deform and/or support the support structure and/or the conductive component. In an exemplary embodiment, additional structures may include flexible components, but may or may not also be shape memory. Additional support structures may couple to the shape memory components and/or the support structure to couple components parts together, define a deployed shape, support or create additional attachment points between component parts, influence deployment, or otherwise contribute to the design of the antenna structure.
Exemplary embodiments described herein may use any combination of the features described herein. In an exemplary embodiment, antenna structure may include any combination of the support structure, shape memory composite components, conductive components, additional structures, whether separate component parts and/or integrated in one or more ways such that a single component part functions as more than one component part. Exemplary embodiments include any combination of the support structure, shape memory composite components, conductive components, and additional structures comprise flexible components. Flexible components comprise a component part that may bend at any point or along a length. In an exemplary embodiment, any combination of the support structure, shape memory composite components, conductive components, and additional structures permit non-structured dynamic deformation. As described herein, the non-structure dynamic deformation permits flexing that may be defined by the external force deforming the component and not in an pre-configured or structurally limited fashion.
Exemplary embodiments may include a stowed configuration as seen in
As seem in
As seen in
In an exemplary embodiment, the support structure may define a gas impermeable cavity. At deployment, the support structure may be injected with a fluid to inflate the support structure. The inflation of the support structure may be used to overcome the failure interface and release the antenna structure for deployment. Inflation of the support structure may assist in the shape memory composite material in deploying to a remembered configuration. The inflation may be used to counteract any creep or deformation that may have occurred in the antenna structure during storage for long periods of time. The support structure may thereafter loose inflation fluid over time. However, the shape memory composite material may thereafter sufficiently support the antenna structure such that additional inflation fluid is not required to retain the shape of the antenna structure for long term deployment.
In an exemplary embodiment, the antenna structure is retain in a housing 131A, 131B as seen in
When ready for use and transport to space, the second part 131B may be removed from the first part 131A as seen in
Exemplary embodiments of the system may include electronics for controlling portions of the system. For example, 144 sequencer and/or electronic may include communication systems; interface systems for coupling to other electronic system; controllers; sequencer; and combinations thereof The sequencer and/or electronics may communicate with controllers, and/or permit the actuation of one or more of the system components described herein. For example, a controller may interface with the fluid injection system to inflate the inflation envelope as described herein. For example, a controller may interface with the release mechanism for the antenna structure for removing the deformation force and permitting the antenna structure to return to a remembered configuration. This may be by opening the door 142 of the housing, or by firing a pyrotechnic charge to remove another failure component, by inflating the inflation envelop with a fluid to overcome a failure interface, or combinations thereof.
Exemplary embodiments of an antenna system may include one or more actuators 145 for controlling one or more components of the system. As illustrated, an exemplary actuator may include a compressed gas canister and controller. The compressed gas canister may be in fluid communication with an interior of a cavity of an inflation envelope created by a support structure as described herein.
Exemplary embodiments of an antenna system may include the antenna structure 146. The antenna structure 146 may include one or more component parts including any combination of a shape memory composite component, conductive component, support structure, housing, additional support structures, etc.
Antenna designs according to embodiments described herein may be capable of sending and receiving circularly polarized waves. Since the magnetic field generated by charged particles in the ionosphere induce Faraday rotation of linearly polarized beams, circularly polarized waves may be preferable to travel through the ionosphere.
Antenna designs according to embodiments described herein may be omnidirectional to allow for arbitrary satellite orientations. As examples only, different antenna designs are provided and described herein. Some examples may provide both circularly polarized waves and/or may be omnidirectional. For example, exemplary antenna designs that may provide both circularly polarized waves and be omnidirectional may include electrically conductive components in a helical shape and/or may define a biconical horn. Exemplary embodiments may use polarizing feeds. An exemplary helical design includes a quadrifilar (4 helical conductors) Helical Antenna, as illustrated in
It should be emphasized that many variations and modifications may be made to the herein-described embodiments, the elements of which are to be understood as being among other acceptable examples. All such modifications and variations are intended to be included herein within the scope of this disclosure and protected by the following claims. Moreover, any of the steps described herein can be performed simultaneously or in an order different from the steps as ordered herein. Moreover, as should be apparent, the features and attributes of the specific embodiments disclosed herein may be combined in different ways to form additional embodiments, all of which fall within the scope of the present disclosure.
Certain terminology may be used in the following description for the purpose of reference only, and thus are not intended to be limiting. For example, terms such as “above” and “below” refer to directions in the drawings to which reference is made. Terms such as “front,” “back,” “left,” “right,” “rear,” and “side” describe the orientation and/or location of portions of the components or elements within a consistent but arbitrary frame of reference which is made clear by reference to the text and the associated drawings describing the components or elements under discussion. Moreover, terms such as “first,” “second,” “third,” and so on may be used to describe separate components. Such terminology may include the words specifically mentioned above, derivatives thereof, and words of similar import.
Conditional language used herein, such as, among others, “can,” “could,” “might,” “may,” “e.g.,” and the like, unless specifically stated otherwise, or otherwise understood within the context as used, is generally intended to convey that certain embodiments include certain features, elements and/or states. However, such language also includes embodiments in which the feature, element or state is not present as well. Thus, such conditional language is not generally intended to imply that features, elements and/or states are in any way required for one or more embodiments or that one or more embodiments necessarily exclude components not described by another embodiment.
Moreover, the following terminology may have been used herein. The singular forms “a,” “an,” and “the” include plural referents unless the context clearly dictates otherwise. Thus, for example, reference to an item includes reference to one or more items. The term “ones” refers to one, two, or more, and generally applies to the selection of some or all of a quantity. The term “plurality” refers to two or more of an item.
As used herein, the terms “about,” “substantially,” or “approximately” for any numerical values, ranges, shapes, distances, relative relationships, etc. indicate a suitable dimensional tolerance that allows the part or collection of components to function for its intended purpose as described herein. Numerical ranges may also be provided herein. Unless otherwise indicated, each range is intended to include the endpoints, and any quantity within the provided range. Therefore, a range of 2-4, includes 2, 3, 4, and any subdivision between 2 and 4, such as 2.1, 2.01, and 2.001. The range also encompasses any combination of ranges, such that 2-4 includes 2-3 and 3-4.
When used in this specification and claims, the terms “comprises” and “comprising” and variations thereof mean that the specified features, steps or integers are included. The terms are not to be interpreted to exclude the presence of other features, steps or components.
The features disclosed in the foregoing description, or the following claims, or the accompanying drawings, expressed in their specific forms or in terms of a means for performing the disclosed function, or a method or process for attaining the disclosed result, as appropriate, may, separately, or in any combination of such features, be utilised for realising the invention in diverse forms thereof.
Although embodiments of this invention have been fully described with reference to the accompanying drawings, it is to be noted that various changes and modifications will become apparent to those skilled in the art. Such changes and modifications are to be understood as being included within the scope of embodiments of this invention as defined by the appended claims. Specifically, exemplary components are described herein. Any combination of these components may be used in any combination. For example, any component, feature, step or part may be integrated, separated, sub-divided, removed, duplicated, added, or used in any combination and remain within the scope of the present disclosure. Embodiments are exemplary only, and provide an illustrative combination of features, but are not limited thereto.
This application is a continuation of International Application No. PCT/US2020/048848, published as WO2021/042076, filed Aug. 31, 2020, which claims priority to U.S. Provisional Patent Application No. 62/894,600, filed Aug. 30, 2019, each of which is incorporated by reference in its entirety into this application.
Number | Date | Country | |
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62894600 | Aug 2019 | US |
Number | Date | Country | |
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Parent | PCT/US2020/048848 | Aug 2020 | US |
Child | 17652547 | US |