Antennas are the cornerstone of high data rate communications and transmission for Earth missions and deep-space communications, both from space and from moon/planetary surfaces. Deploying operational antennas into space in an efficient manner remains a challenge. In order to meet the increasing demand for high-throughput satellited (HTS) antennas that can operate at higher frequencies, larger reflector configurations are required.
Conventional, fixed, solid surface antenna radiofrequency (RF) reflectors up to 4 meters in diameter are available and can target Ka-Band or above RF transmission. Deployable versions with rigid panels up to 10 meters in diameter have been explored, but present mechanical complexities to stow/deploy due to volume and mass.
Deformable versions using thin-shell composite reflective surface construction, such as that described in U.S. Pat. No. 6,344,835, are possible but have size limitations, e.g., less than 10 m diameter, due to surface accuracy requiring deep backbones or perimeter ring structures to scale up. Mesh reflector antennas are currently the only technical approach to realize effectively deployable reflectors larger than 10 meters for Ka-Band RF transmission but have limitations for higher RF bands due to faceting inherent to the mesh architecture and not having a solid surface. The RF energy at higher frequencies would leak through the gaps in the mesh. It is understood that frequencies above 60-70 GHz require a solid, highly accurate surface.
For even larger reflector needs greater than 10-20 meters, in-space assembly (ISA) is a considered approach. Current concepts like the Space Infrastructure Dexterous Robot (SPIDER) rely on robotic arm to assemble many individual panels that do not package well, and require complicated techniques for joining and multiple operations, increasing cost and risk. The discontinued SPIDER experiment by Maxar on NASA's On-orbit Servicing, Assembly and Manufacturing (OSAM-1) mission was planned to robotically assemble a 3-m scale reflector from seven 1-m rigid segments fixed to the spacecraft, but the rigid elements do not package efficiently inside the rocket fairing and must be assembled by a large robotic arm using overly complicated techniques.
There remains a need for improved materials, configurations and processes for efficient self-deployment of antenna reflectors of varying sizes in space to support S-band and above RF (≥2 GHZ).
In a first exemplary embodiment, an antenna reflector array having at least a stowed position and a deployed position includes: multiple panels and a central panel, each of the multiple and central panels including a functional side and a non-functional side, wherein in the stowed position, the multiple hexagonal and central panels are in a compact configuration; multiple sets of heat actuated flexible hinges formed of a shape memory composite (“SMC”) substrate, each of the multiple sets of flexible hinges being connected at a first end thereof to a non-functional side of one of the multiple panels and at a second end thereof to the non-functional side of the central panel, the heat actuated flexible hinges being controllable between a first shape and a second shape; and further wherein, when each set of heat actuated flexible hinges changes from the first shape to the second shape, a panel connected thereto is moved from a first position to a second position.
In a second exemplary embodiment, an antenna reflector array having at least a stowed position and a deployed position includes: multiple panels and a central panel, each of the multiple and central panels including a functional side and a non-functional side, wherein in the stowed position, the multiple hexagonal and central panels are in a concentrically stacked configuration; multiple sets of heat actuated flexible hinges, each of the multiple sets of flexible hinges being connected at a first end thereof to a non-functional side of one of the multiple panels and at a second end thereof to the non-functional side of the central panel, the heat actuated flexible hinges being controllable between a first shape and a second shape, and further wherein, when each set of heat actuated flexible hinges changes from the first shape to the second shape, a panel connected thereto is moved from a first position to a second position; and multiple closing mechanisms, each of the multiple closing mechanisms being movably attached to a set of heat actuated flexible hinges and an associated one of the multiple panels, wherein each of the multiple closing mechanisms is triggered when its associated panel is in the second position, the multiple closing mechanisms moving its associated panel to a third position responsive to the trigger, the third position resulting in the final deployed position.
In a third exemplary embodiment, a process for assembling multiple individual reflector sub-arrays into a consolidated reflector array includes: deploying multiple individual reflector sub-arrays from their stowed positions, each of the multiple individual reflector sub-arrays including multiple connected panels and a connecting boom for maintaining connection with a spacecraft, wherein deploying an individual reflector sub-array includes activating one or more hinges connected between each side panel and a central panel of the subarray on the non-functional surfaces thereof to deploy each of the side panels from their stowed positions; robotically connecting each of the multiple deployed individual sub-arrays to a designated central deployed individual sub-array, wherein the boom of each of the multiple deployed individual sub-arrays is robotically attached to a different connection point on the central deployed individual sub-array; and further wherein at least one additional securing mechanism is robotically attached between at least one panel of each of the multiple deployed individual sub-arrays and a panel of the designated central deployed individual sub-array
These and other features, advantages, and objects of the present embodiments will be further understood and appreciated by those skilled in the art by reference to the following specification, claims, and appended drawings.
Example embodiments will become more fully understood from the detailed description given herein below and the accompanying drawings, wherein like elements are represented by like reference characters, which are given by way of illustration only and thus are not limitative of the example embodiments herein.
It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It is also to be understood that the specific devices and processes illustrated in the attached drawings, and described in the following specification, are simply exemplary embodiments of the inventive concepts defined in the appended claims. Hence, specific dimensions and other physical characteristics relating to the embodiments disclosed herein are not to be considered as limiting, unless the claims expressly state otherwise.
In the embodiment shown in
Composite hinges H1, H2, H3, H4, H5, and H6 are formed from a flexible shape memory composite (“SMC”) substrate such as that described in co-owned U.S. patent application Ser. No. ______ (LAR-20532-1) and U.S. Provisional Patent Application No. 63/452,712 which are incorporated herein by reference in their entireties. Components formed from SMC can be programmed into a temporary shape through applied force and internal heating. In the programmed shape, the deformed structure is in a frozen state remaining dormant without external constraints. Upon heating once more, the substrate will return slowly (several to tens of seconds) to the original shape.
Referring to
Similar to the first exemplary hinge 100, a second exemplary hinge 200 (
As described in co-owned U.S. patent application Ser. No. ______ (LAR-20532-1) SMC hinges used in the present embodiments may also include on or more layers of heat spreading material to assist with distribution of applied heat, as well as sensors, such as strain and temperature sensors and a microprocessor for implementing a monitoring and feedback process.
As illustrated in
In a preferred embodiment, each panel Px is connected to the central panel PC by two parallel hinges, 100a and 100b as shown in
In
Referring to
One skilled in the art will recognize that panel stacking configurations described above are not limited to the configurations shown. For example,
All references, including publications, patent applications, and patents, cited herein are hereby incorporated by reference to the same extent as if each reference were individually and specifically indicated to be incorporated by reference and were set forth in its entirety herein.
The use of the terms “a” and “an” and “the” and similar referents in the context of describing the embodiments (especially in the context of the following claims) are to be construed to cover both the singular and the plural, unless otherwise indicated herein or clearly contradicted by context. The terms “comprising,” “having,” “including,” and “containing” are to be construed as open-ended terms (i.e., meaning “including, but not limited to,”) unless otherwise noted. Recitation of ranges of values herein are merely intended to serve as a shorthand method of referring individually to each separate value falling within the range, unless otherwise indicated herein, and each separate value is incorporated into the specification as if it were individually recited herein. All methods described herein can be performed in any suitable order unless otherwise indicated herein or otherwise clearly contradicted by context. The use of any and all examples, or exemplary language (e.g., “such as”) provided herein, is intended merely to better illuminate the features of the embodiments and does not pose a limitation on the scope of the embodiments unless otherwise claimed. No language in the specification should be construed as indicating any non-claimed element as essential to the practice of the embodiments.
Preferred embodiments are described herein. Variations of those preferred embodiments may become apparent to those of ordinary skill in the art upon reading the foregoing description. The inventors expect skilled artisans to employ such variations as appropriate, and the inventors intend for the invention to be practiced otherwise than as specifically described herein. Accordingly, these embodiments includes all modifications and equivalents of the subject matter recited in the claims appended hereto as permitted by applicable law. Moreover, any combination of the above-described elements in all possible variations thereof is encompassed by the embodiments unless otherwise indicated herein or otherwise clearly contradicted by context.
This patent application claims the benefit of and priority to U.S. Provisional Application No. 63/452,712, filed on Mar. 17, 2023 entitled Shape Memory Polymer Composite Substrate and priority to U.S. Provisional Application No. 63/452,713 filed on Mar. 17, 2023, the contents of which are hereby incorporated by reference in their entirety. The patent application also cross-references commonly owned U.S. Pat. No. 9,796,159 entitled Electric Field Activated Shape Memory Polymer Composite; U.S. Pat. No. 11,267,224 entitled Method for Preparing and Electrically-Activated Shape Memory Polymer Composite; and U.S. patent application Ser. No. 18/238,137 entitled Composite Deployable Structure; U.S. Provisional Application No. 63/401,394, filed on Aug. 26, 2022; U.S. Provisional Application No. 63/452,752, filed on Mar. 17, 2023; U.S. Provisional Application No. 63/455,468, filed on Mar. 29, 2023; U.S. patent application Ser. No. ______[LAR 20352-1] entitled SHAPE MEMORY POLYMER COMPOSITE SUBSTRATE, and U.S. patent application Ser. No. ______ (LAR 20513-1) entitled Deployable Antenna Reflectors Array Formed of Multiple Connected Gores, each of which is incorporated herein by reference in its entirety.
The invention described herein was made by employees of the United States Government and may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefore.
Number | Date | Country | |
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63452712 | Mar 2023 | US | |
63452713 | Mar 2023 | US |