Systems and methods for deploying parabolic reflector with integrated origami folding hinges

Abstract

Systems and methods herein provide for deployable reflectors. In one embodiment, a deployable antenna includes a reflector having a plurality of integrated hinges defining a crease pattern that permits the reflector to transition between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature. The reflector may be formed from a composite laminate and may include a reflective layer suitable for radio-frequency or other electromagnetic applications. Deployment may be driven at least in part by strain energy stored in the reflector, with optional actuators, retaining mechanisms, and rate-limiting devices providing controlled release, deployment, and re-stowage. The antenna may be integrated with a satellite or other platform and may be repeatedly deployed and retracted to support dynamic mission requirements. Systems and methods are also disclosed for controlling deployment and retraction of the antenna, including a controller which coordinates actuator operation and communications during and after deployment.

Description

Attorney Docket No. 23193.001WO1SYSTEMS AND METHODS FOR DEPLOYING PARABOLIC REFLECTOR WITH INTEGRATED ORIGAMI FOLDING HINGESField of the Invention

[0001] The present embodiments relate generally to deployable antenna structures and, more particularly, to compactly stowable and re-deployable reflective antennas employing integrated hinge and origami-inspired folding architectures for use across space-based and other platforms.Background

[0002] Deployable antenna systems are increasingly important across space-based, airborne, terrestrial, and maritime platforms due to persistent constraints on size, mass, and packaging volume during transport, launch, or relocation. In particular, satellite systems, including small satellites and CubeSats, face stringent volumetric and mass limitations imposed by standardized form factors and launch vehicle interfaces. These constraints often limit the achievable antenna aperture size, which in turn restricts communication range, data throughput, signal-to-noise ratio, and overall system performance. As mission requirements expand to include higher data rates, wider bandwidths, and more demanding sensing or energy-directing functions, there is a growing need for antenna architectures that can achieve large effective apertures while remaining compatible with compact stowage requirements.

[0003] Conventional approaches to deployable antennas have primarily relied on mesh reflectors, truss-supported structures, rib-wrap architectures, or umbrella-style mechanisms. While such systems can achieve relatively large deployed apertures, they often suffer from significant drawbacks. Mesh reflectors typically rely on tensioned metallic meshes supported by complex backing structures, resulting in surfaces that are faceted rather than smooth. This lack of surface continuity can degrade electromagnetic performance, particularly at higher frequencies, where surface accuracy and smoothness are critical. Additionally, mesh-based systems frequently require numerous discrete components, complex assembly processes, and precise alignment of structural members, contributing to long production lead times and high nonrecurring engineering costs.Attorney Docket No. 23193.001WO1

[0004] Solid-surface reflectors offer improved surface accuracy but are generally incompatible with compact stowage unless segmented into multiple rigid panels. Panelized reflectors introduce their own challenges, including hinge complexity, alignment tolerances, and the risk of discontinuities or gaps between panels that negatively affect performance. Moreover, many existing deployable reflector systems are designed for one-time deployment and lack the capability to be reliably re- stowed after deployment. This limitation restricts operational flexibility, particularly for missions that require orbital maneuvering, threat avoidance, collision avoidance, servicing, or relocation after initial deployment.

[0005] The inability to re- stow large apertures is especially problematic for small satellite platforms, where changes in mass distribution, moment of inertia, and aerodynamic or radiation pressure effects can significantly impact attitude control and maneuverability. During high-acceleration events, such as orbit raising or rapid repositioning, deployed antenna structures may be subjected to loads beyond their design limits, increasing the risk of damage or failure. As a result, operators are often forced to choose between maintaining a deployed high-performance antenna and preserving spacecraft agility and survivability.

[0006] Manufacturing considerations further compound these challenges. Many existing deployable antenna architectures require extensive manual assembly, custom tooling, and platform-specific redesigns, limiting scalability and driving up cost. These issues are particularly acute for large satellite constellations, where hundreds or thousands of antennas may be required, and where production throughput, repeatability, and cost efficiency are critical. Long lead times and high per-unit costs can hinder rapid deployment of new systems and constrain responsiveness to evolving mission needs.

[0007] Thus, there is a need for deployable antenna architectures that can achieve large, high-performance reflective surfaces while remaining compatible with compact stowage volumes, especially for small satellite platforms. Such architectures should preferably provide smooth, continuous reflective surfaces with high dimensional accuracy, support wideband operation across radio-frequency and optical regimes, and be capable of repeated deployment and re-stow cycles without significant degradation. Additionally, there is a need for antennaAttorney Docket No. 23193.001WO1systems that can be manufactured using scalable, mold-based or automated processes, reducing complexity, cost, and production time.Summary

[0008] Embodiments herein address the above needs based on structural approaches that integrate deployment functionality directly into the antenna surface itself, rather than relying on bulky external support frameworks. Origami-inspired folding architectures, compliant integrated hinges, and flexible structural supports offer a pathway to achieving compact stowage and controlled deployment of curved surfaces. By storing strain energy within the structure and selectively releasing it during deployment, such systems can reduce reliance on complex motors or pyrotechnic devices while enabling predictable and repeatable deployment behavior.Furthermore, integrating re-stow capability enables antenna systems to dynamically adapt to changing operational requirements, enhancing mission flexibility, survivability, and overall system utility across a broad range of applications.

[0009] In accordance with these principles, the embodiments described herein provide a deployable antenna that includes a reflector configured to transition between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature. The reflector may assume a variety of surface geometries suitable for reflective operation, including parabolic, cylindrical, conical, singly curved, doubly curved, or irregular shapes, depending on the intended electromagnetic performance. The reflector may be formed as a continuous solid surface or as a faceted or tessellated surface comprising multiple rigid regions, while maintaining controlled deployment behavior through an integrated crease pattern.

[0010] The reflector may be constructed from a composite laminate that includes one or more structural fiber-reinforced layers, such as carbon fiber reinforced polymer, optionally combined with a reflective layer formed from conductive metals or coated fibers. A plurality of hinges are disposed along the reflector and define an origami-inspired crease pattern, such as a Miura-Ori pattern or variations thereof, that governs folding and deployment. One or more of the hinges may include compliant materials, such as aromatic polyamide fiber materials, embedded within the laminate and exposed by selective machining of structural layers to create durable,Attorney Docket No. 23193.001WO1fatigue-resistant hinge regions. Relief features may further be incorporated to manage strain during repeated folding cycles.

[0011] Deployment of the reflector may be driven at least in part by strain energy stored within the reflector, the hinges, perimeter support structures, or deployable ribs. In some embodiments, deployment and re-stow operations may be assisted or controlled by actuators, motors, cables, dampers, escapements, or other rate-limiting mechanisms to regulate deployment speed and reduce shock loads. The rate-limiting mechanism may be passive, active, or a combination thereof. Structural supports may be disposed on a backside of the reflector, including deploy able ribs that rotate away from the reflector during deployment and enter a tensioned state to increase stiffness and surface accuracy. A perimeter support structure formed from a rigid yet flexible material may further enhance deployed rigidity while contributing additional stored strain energy.

[0012] The antenna may further include one or more retaining mechanisms that secure the reflector in its stowed configuration and cooperate with hinge structures to guide controlled deployment. In certain embodiments, a retaining mechanism may also function as a feed element positioned relative to the deployed reflector to transmit or receive electromagnetic energy. The antenna may be configured for center-fed or offset-fed operation and may support wideband performance across radio-frequency, millimeter-wave, or optical regimes. Example applications include communication, sensing, LiDAR, power beaming, and directed or detected electromagnetic energy systems.

[0013] In some embodiments, the reflector is configured to be electrically reflective and / or optically reflective by incorporating one or more reflective materials on or within the reflector structure. For electrically reflective embodiments, the reflector may include a conductive layer formed from metals such as aluminum, copper, gold, silver, or alloys thereof, applied as a foil, coating, sputtered film, vapor-deposited layer, or conductive veil embedded within a composite laminate. Such conductive layers may be continuous or patterned and may be electrically coupled across hinge regions to maintain reflective continuity when the reflector is deployed. For optically reflective embodiments, the reflector may include reflective coatings or films configured to reflect visible, infrared, or other optical wavelengths, such as polished metalAttorney Docket No. 23193.001WO1layers, dielectric mirror coatings, multilayer interference stacks, or metallized polymer films. Tn some embodiments, the reflective material is selected to balance reflectivity, mass, durability, and compatibility with folding and deployment, and may be applied to a front surface of the reflector or embedded within the laminate structure. The choice of reflective material and deposition technique may be tailored to the intended operational frequency range, environmental exposure, and surface accuracy requirements, enabling the same deployable reflector architecture to be used across electrical and optical applications.

[0014] Although certain embodiments are described in the context of satellite platforms, including CubeSats, the antenna architectures described herein are not limited to space-based use. The same deployable and re-stowable features may be applied to airborne, terrestrial, maritime, mobile, or portable platforms, as well as fixed installations. The combination of compact stowage, scalable manufacturing, smooth reflective surfaces, and repeatable deployment enables the embodiments described herein to address the needs of high-performance antenna systems across a wide range of operational environments and mission profiles.

[0015] In one embodiment, a deployable antenna is provided that includes a reflector configured to assume a predetermined three-dimensional curvature when in a deployed configuration and a plurality of hinges disposed along the reflector. The hinges define a crease pattern that permits the reflector to transition between the deployed configuration and a substantially flat stowed configuration, enabling compact storage and controlled deployment of the antenna.

[0016] In some embodiments, the predetermined three-dimensional curvature of the reflector comprises a parabolic geometry suitable for reflective antenna operation. In some embodiments, the reflector is formed from a composite laminate that includes at least one structural fiber-reinforced layer, providing a lightweight yet stiff structural surface. In some embodiments, the composite laminate further includes a reflective layer selected from an electrically reflective material or an optically reflective material. In some embodiments, the reflector comprises a tessellated or faceted surface formed from a plurality of rigid panels interconnected by the hinges, allowing controlled folding while maintaining structural integrity in the deployed configuration. In some embodiments, at least one hinge includes a compliantAttorney Docket No. 23193.001W01material embedded within the reflector, wherein the compliant material comprises an aromatic polyamide fiber material configured to permit repeated folding and deployment. In some embodiments, the crease pattern defined by the hinges comprises a Miura-Ori crease pattern that governs folding kinematics and deployed surface geometry.

[0017] In some embodiments, transition of the reflector from the stowed configuration to the deployed configuration is driven at least in part by strain energy stored in the reflector. In some embodiments, the deployable antenna further includes an actuator configured to deploy or re-stow the reflector. In some embodiments, a rate-limiting mechanism is provided to control deployment speed and reduce shock or dynamic loads during deployment. In some embodiments, the deployable antenna further includes a perimeter support structure configured to strengthen the reflector when deployed and improve surface stability. In some embodiments, a feed element is positioned relative to the reflector to receive or transmit electromagnetic energy reflected by the reflector. In some embodiments, the antenna is configured for radio-frequency communication. In some embodiments, the antenna is configured for use on a satellite platform. In some embodiments, the reflector is configured for repeated deployment and re-stow cycles without permanent deformation.

[0018] In one embodiment, a method of deploying a reflector antenna is provided. The method includes providing a reflector having a plurality of hinges integrated into the reflector and defining a crease pattern, the reflector being configurable between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature. The method further includes stowing the reflector in the substantially flat configuration by folding the reflector along the plurality of hinges, restraining the reflector in the substantially flat configuration on a platform, releasing the reflector from the restrained configuration, and deploying the reflector from the substantially flat configuration to the deployed configuration by permitting the reflector to articulate along the plurality of hinges, wherein deployment is driven at least in part by strain energy stored in the reflector.

[0019] In one embodiment, a non-transitory computer readable medium is provided that includes instructions which, when executed by a controller, direct the controller to deploy a reflector antenna having a plurality of hinges integrated into the reflector and defining a creaseAttorney Docket No. 23193.001WO1pattern, the reflector being configurable between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature. The instructions further direct the controller to direct an actuator to restrain the reflector in a substantially flat configuration on a platform, wherein the reflector is folded along the plurality of hinges, and to direct the actuator to release the reflector from the restrained configuration to deploy the reflector from the substantially flat configuration to the deployed configuration by permitting the reflector to articulate along the plurality of hinges, wherein deployment is driven at least in part by strain energy stored in the reflector. In some embodiments, execution of the instructions results in measurable improvements in deployment reliability, reduction in peak actuator loads, and reduced communication downtime during deployment relative to uncontrolled or manual deployment processes.

[0020] The various embodiments disclosed herein may be implemented in a variety of ways as a matter of design choice. For example, some embodiments herein are implemented in hardware whereas other embodiments may include processes that are operable with the hardware. Other exemplary embodiments, including software and firmware, are described below.Brief Description of the Drawings

[0021] Some embodiments of the present invention are now described, by way of example only, and with reference to the accompanying drawings. The same reference number represents the same element or the same type of element on all drawings.

[0022] FIG. 1 illustrates an exemplary embodiment of a deployable antenna integrated with a compact satellite platform, such as a CubeSat, with the antenna shown in a substantially flat stowed configuration and including a reflector having integrated hinges defining a crease pattern.

[0023] FIG. 2 illustrates an exemplary embodiment of an operational sequence for a satellite-based system in which the deployable antenna remains stowed during launch, orbit raising, and maneuvering phases, is deployed during an active operational phase, and may subsequently be retracted to enable repositioning or reconfiguration.Attorney Docket No. 23193.001WO1

[0024] FTG. 3 illustrates an exemplary embodiment of a deployable antenna mounted on a CubeS at, showing retaining mechanisms configured to secure the antenna in a stowed configuration prior to deployment.

[0025] FIG. 4 illustrates the exemplary embodiment of FIG. 3 with the antenna deployed, wherein one retaining mechanism functions as a feed antenna and deployable solar panels extend from the CubeS at.

[0026] FIG. 5 illustrates an exemplary embodiment showing articulation of the deployable antenna relative to the CubeS at during deployment and retraction about a hinge and retaining mechanism.

[0027] FIG. 6 illustrates an exemplary embodiment of a deployed antenna reflector including an outer support structure and internal support structures formed from rigid yet flexible materials configured to provide structural rigidity and surface stability in the deployed configuration.

[0028] FIG. 7 illustrates an exemplary embodiment of a flowchart representing a method for stowing, restraining, releasing, and deploying a reflector antenna, including embodiments in which a controller directs an actuator to release and deploy the antenna using stored strain energy.

[0029] FIGS. 8 A and 8B illustrate an exemplary embodiment of a single-fold reflector configuration, with FIG. 8A showing the reflector in a stowed configuration and FIG. 8B showing the reflector unfolding toward a deployed configuration.

[0030] FIGS. 9A and 9B illustrate an exemplary embodiment of a multi-fold reflector configuration, with FIG. 9A showing the reflector in a compact stowed configuration and FIG.9B showing the reflector in an unfolded or deployed configuration.

[0031] FIGS. 10A through 10D illustrate an exemplary embodiment of a multi-fold reflector configuration transitioning through successive stages from a fully stowed configuration to a deployed configuration having a predetermined three-dimensional curvature.Attorney Docket No. 23193.001W01

[0032] FIGS. 11 A through 11D illustrate an exemplary embodiment of a polygonal bloom- style reflector configuration, with the reflector shown in a compact radially folded stowed configuration and progressively unfolding to form a deployed reflective surface.

[0033] FIG. 12 illustrates an exemplary embodiment of a cloud-computing system configured to support communications, control, command generation, and telemetry processing associated with deployment, operation, and re-stowage of the deployable antenna, wherein some components may be remote from the platform and other components may be located on the platform.Detailed Description of the Drawings

[0034] The figures and the following descriptions illustrate specific exemplary embodiments. It will thus be appreciated that those skilled in the art will be able to devise various arrangements that, although not explicitly described or shown herein, embody certain principles and are included within the scope of the embodiments. Furthermore, any examples described herein are intended to aid in understanding the embodiments and are to be construed as being without limitation to such specifically recited examples and conditions. As a result, the embodiments are not limited to any of the examples described below.

[0035] FIG. 1 illustrates one representative embodiment of a deployable antenna system, shown in a stowed configuration suitable for transport and subsequent deployment. In this embodiment, the reflector 102 of the deployable antenna in FIG. 1 is configured as a flat-packed structure in its stowed state 100 A, occupying an approximately rectangular footprint that corresponds to an available mounting surface. In this configuration, the reflector 102 presents a substantially planar exterior surface, with its thickness minimized to reduce protrusion beyond the structural envelope of the platform. The reflector 102 may comprise a continuous solid composite laminate surface or, in other embodiments, a tessellated or faceted assembly of rigid surface regions interconnected by a defined crease pattern. In either case, the reflector 102 is configured such that, when stowed as shown in FIG. 1, it remains substantially flat while retaining the ability to transition into a predetermined three-dimensional curvature upon deployment.Attorney Docket No. 23193.001WO1

[0036] A plurality of hinges 104 are disposed along and within the reflector 102 and collectively define the crease pattern that permits the reflector 102 to transition between the stowed configuration illustrated in FIG. 1 and a deployed configuration having a predetermined three-dimensional curvature. The hinges 104 extend along predetermined fold lines distributed across the reflector 102 and may be arranged in an origami-inspired geometry, such as a Miura-Ori crease pattern, a Yoshimura crease pattern, or a fan fold pattern, a single fold pattern, a simple vertex pattern, a scroll fold pattern, a waterbomb fold pattern, a polygon bloom pattern, an even-gon twist pattern, a tri-fold taco pattern, a flattening trough pattern, or any modification thereof. Although the hinges 104 are not shown schematically in FIG. 1 while the reflector 102 is in its flat, stowed state, their placement and orientation are selected to control both the folding kinematics and the final deployed surface geometry.

[0037] In some embodiments, each hinge 104 is formed integrally within the composite structure of the reflector 102 by selectively introducing compliant regions within the laminate. This may be achieved, for example, by embedding a compliant material layer between structural composite plies and machining through one or more structural layers to expose the compliant material at the hinge locations 104. In certain embodiments, the compliant material comprises an aromatic polyamide fiber material, such as Kevlar, which provides flexibility, fatigue resistance, and durability while maintaining overall structural continuity of the reflector 102. One or more of the hinges 104 may further include relief slits or cutouts configured to reduce localized strain during folding and unfolding.

[0038] The reflector 102 itself may be fabricated from a composite laminate that includes one or more fiber-reinforced structural layers, such as carbon fiber reinforced polymer, providing a high stiffness-to-weight ratio and dimensional stability. A reflective layer may be integrated into or applied onto the front surface of the reflector 102, although such a layer may not be visible in FIG. 1 due to the stowed orientation of the reflector 102 against the platform. Suitable reflective layers include metallic films or coatings, such as aluminum, gold, copper, or conductive fiber veils coated with metals such as nickel, configured to reflect electromagnetic energy when the reflector 102 is deployed.Attorney Docket No. 23193.001WO1

[0039] Tn the stowed configuration shown in FIG. 1 , the reflector 102 is retained against the platform by one or more restraints, covers, or launch locks, which may be mechanical, frangible, or releasable devices configured to secure the reflector 102 and the associated hinges 104 during launch loads and dynamic environments. The overall stowed geometry of the reflector 102. including the folded configuration defined by the hinges 104. is optimized to maintain compatibility with launch vehicle constraints and standardized deployment interfaces, while maximizing the aperture size achievable upon deployment from the platform.

[0040] Although not explicitly visible in FIG. 1, the backside of the reflector 102 may include one or more deployable structural supports disposed opposite the reflective surface and oriented toward the platform 100 in the stowed configuration. These deployable structural supports may be folded substantially flat against the backside of the reflector 102 when the reflector 102 is restrained in its stowed configuration and articulated through the hinges 104. In deployed configurations, such supports may expand or otherwise deflect away from the reflector 102 and enter a tensioned state to increase the structural rigidity and surface accuracy of the deployed reflector, as illustrated in 100B. Similarly, a perimeter support structure may be integrated along an outer boundary of the reflector 102, such as a tape-spring-like compliant member that cooperates with the hinges 104 and remains flattened in the stowed configuration shown in FIG. 1, later deploying to provide edge stiffness and additional stored strain energy.

[0041] In various embodiments, some of which are shown below, the number, arrangement, and geometry of the hinges incorporated into the antenna 102, as well as the corresponding origami-inspired crease pattern defined thereby, are not limited to the specific configurations illustrated in the figures. Rather, the antenna 102 may be configured with a greater or fewer number of hinges, and with alternative hinge layouts, to accommodate different stowed volumes, deployed aperture sizes, surface curvatures, or structural performance requirements. The hinge pattern may be tailored to produce differing folding kinematics, deployment sequences, or final deployed geometries, including variations in cell size, aspect ratio, symmetry, or orientation of fold lines. Such modifications may be implemented to optimize parameters such as strain distribution, deployment reliability, surface accuracy, or compatibility with a particular platform or mission profile. Accordingly, the origami pattern associated with the antenna 102 may be selectively configured or modified without departing from theAttorney Docket No. 23193.001WO1underlying deployable functionality, enabling a wide range of deployable configurations suited to diverse applications and operational constraints.

[0042] In this regard, the configuration shown in FIG. 1 emphasizes the compactness and volumetric efficiency of the deployable antenna system in its stowed form. By enabling the reflector 102, which is capable of assuming a predetermined three-dimensional curvature such as a parabolic or otherwise curved surface, to be packaged into a substantially flat form factor through the coordinated action of the hinges 104, the embodiments illustrated allow a relatively large effective aperture to be carried on a relatively small platform, such as a CubeSat (i.e„ a cubically shaped small satellite). This stowed configuration supports applications in which mass, volume, and launch constraints are critical, while preserving the capability to deploy the reflector 102 into a high-performance reflective geometry once on orbit or at an operational location.

[0043] In some embodiments, the one or more deployable structural supports disposed on a backside of the reflector are configured to increase structural rigidity when the reflector is in the deployed configuration. These structural supports may be implemented as ribs, struts, spars, frames, or other elongate members that extend across or along portions of the reflector surface. The deployable structural supports may be foldable or collapsible in the stowed configuration such that they lie substantially flush against (e.g., affixed to) the backside of the reflector, and may rotate, extend, or otherwise move away from the reflector during deployment. In the deployed configuration, the structural supports may assume a load-bearing state in which they resist bending, twisting, or out-of-plane deformation of the reflector, thereby improving surface figure accuracy and maintaining the predetermined three-dimensional curvature during operation. In some embodiments, the structural supports may be spring-preloaded such that, after deployment, they remain in tension or compression to provide continuous stiffening of the reflector structure.

[0044] The structural supports may be formed from rigid yet flexible materials selected to accommodate repeated folding and deployment while providing sufficient stiffness when deployed. Suitable materials may include metallic materials such as spring steel, aluminum alloys, titanium alloys, or shape-memory alloys, as well as composite materials such as carbon fiber reinforced polymers, glass fiber composites, or hybrid composite-metal laminates. In someAttorney Docket No. 23193.001WO1embodiments, the structural supports may incorporate compliant regions, flexural hinges, or tape-spring-like geometries that enable elastic deformation during folding and automatic stiffening upon deployment. The material selection and cross-sectional geometry of the structural supports may be tailored to balance stored strain energy, deployment reliability, and deployed stiffness.

[0045] In addition to or in combination with the deployable structural supports, a perimeter support structure may extend along at least a portion of an outer boundary of the reflector. The perimeter support structure may be configured to stabilize the reflector edge, distribute loads across the reflector surface, and reduce edge deflection or flutter during operation. In some embodiments, the perimeter support structure comprises a continuous or segmented member formed from a rigid yet flexible material, such as a tape-spring-like element, that is flattened or folded in the stowed configuration and elastically returns to a stiffened shape when deployed. The perimeter support structure may cooperate with the deployable structural supports on the backside of the reflector to form a reinforced framework that enhances global stiffness, reduces sensitivity to thermal gradients or dynamic disturbances, and improves overall surface accuracy of the deployed reflector.

[0046] Overall, FIG. 1 conveys the integration of a flat-pack deployable reflector 102 with a compact platform, illustrating how the reflector 102 and its integrated hinges 104 cooperate to achieve a low-profile stowed configuration without sacrificing the ability to deploy into a precise three-dimensional reflective surface suitable for radio-frequency communication, sensing, or other electromagnetic applications when deployed. In some embodiments, the predetermined three-dimensional curvature of the reflector is defined by the geometry, placement, and orientation of the hinges and crease pattern such that the reflector repeatedly assumes substantially the same deployed surface geometry upon each deployment.

[0047] It should be noted that the deployable antenna described herein is not intended to be limited to implementation on satellite platforms. Rather, the antenna may be integrated with and deployed from a wide variety of platforms depending on the intended application and operating environment. By way of example, the antenna may be mounted on space-based, airborne, terrestrial, maritime, or mobile platforms, including but not limited to larger spacecraft,Attorney Docket No. 23193.001WO1high-altitude platforms, unmanned aerial vehicles, aircraft, ground vehicles, naval vessels, fixed ground installations, portable or man-carried systems, and temporary or rapidly deployable infrastructure. The ability of the reflector 102 to transition between a substantially flat stowed configuration and a deployed configuration through the use of integrated hinges 104 enables compact packaging, transport, and re-deployment across diverse platforms and mission profiles. Accordingly, the embodiments described herein are applicable to a broad range of operational contexts in which low stowed volume, low mass, and deployable aperture performance are advantageous, irrespective of whether the antenna is deployed in space, air, land, or sea environments.

[0048] FIG. 2 illustrates an exemplary operational sequence for one embodiment of a deployable antenna system implemented on a satellite platform, showing multiple representative mission phases in which the antenna may be selectively deployed and retracted to support differing operational objectives over the lifetime of the satellite. The figure conceptually depicts the satellite progressing through a series of modes, beginning with launch, transitioning through orbital maneuvers, entering an operational state with the antenna deployed, and subsequently returning to a stowed configuration to enable mobility, survivability, or reconfiguration.

[0049] In a first phase labeled “Launch,” a satellite platform is shown in a fully stowed configuration, with the reflector 102 folded into a substantially flat, compact form and secured against the satellite body by restraints or launch locks. In this phase, the reflector 102 and its associated hinges 104 are restrained to withstand the high acceleration, vibration, and acoustic loads associated with launch. The flat-packed geometry minimizes protrusions and ensures compatibility with the launch vehicle fairing and standardized deployment interfaces, while protecting the reflector 102 and hinges 104 from mechanical damage during ascent.

[0050] Following launch, the satellite transitions into an “Orbit Raising” phase, during which propulsion or maneuvering systems are used to adjust orbital parameters. During this phase, the reflector 102 remains stowed, preserving a low moment of inertia and reduced aerodynamic or plume interaction cross-section. Maintaining the antenna in its stowed configuration during orbit-raising maneuvers reduces structural loads on the hinges 104 and minimizes dynamic coupling between the antenna structure and the platform.Attorney Docket No. 23193.001W01

[0051] The figure further illustrates a “Stealth Mode” or quiescent operational phase, in which the reflector 102 continues to be maintained in its stowed configuration even after the satellite has reached a desired orbit. In this mode, the flat-packed reflector 102 presents a reduced observable signature and a compact physical profile, which may be advantageous for reducing detectability, managing thermal exposure, limiting solar radiation pressure effects, or controlling the satellite’s attitude dynamics. The hinges 104 remain folded along their predetermined crease pattern, maintaining the reflector 102 in a substantially planar state. The crease pattern may be implemented in a continuous composite reflector, in a tessellated reflector formed from multiple rigid panels, or in hybrid configurations combining continuous and panelized regions

[0052] In an “Active Mode” phase, FIG. 2 depicts the reflector 102 deployed away from the satellite platform into its operational three-dimensional geometry, such as a parabolic or otherwise curved reflective surface. Deployment may be initiated by releasing one or more restraints and allowing stored strain energy within the reflector 102, the hinges 104, perimeter support structures, or deployable ribs to drive the unfolding motion. In some embodiments, deployment may additionally or alternatively be assisted by actuators, motors, or other active mechanisms. As the reflector 102 transitions from the stowed configuration to the deployed configuration, the hinges 104 articulate along their fold lines, guiding the reflector surface into the predetermined curvature while controlling strain and alignment. Once fully deployed, the reflector 102 provides a large effective aperture positioned to cooperate with a feed element mounted on or extending from the satellite platform, enabling high-gain transmission or reception of electromagnetic energy.

[0053] As used herein, the term platform refers generally to any structure, vehicle, or system on which the deployable antenna is mounted and from which the antenna is deployed. In some embodiments, the platform comprises a satellite platform, including small satellites and CubeSats, while in other embodiments the platform may comprise airborne, terrestrial, maritime, mobile, or fixed installations. References to a CubeS at or satellite platform are exemplary implementations of the broader platform concept. Additionally, the plurality of hinges 104 described herein are structural elements integrated into the reflector 102 that define fold lines and control articulation of the reflector between a substantially flat stowed configuration and aAttorney Docket No. 23193.001W01deployed configuration. These hinges are distinct from retaining mechanisms, latches, or release devices, which may be used to selectively restrain and release the reflector but do not define the crease pattern or folding kinematics of the reflector. In embodiments that include actuators and controllers, the controller is configured to issue commands based on mission or system conditions, and the actuator is configured to physically restrain, release, deploy, or re-stow the reflector in response to such commands. As further used herein, the substantially flat stowed configuration refers to a folded state of the reflector in which the reflector is compactly arranged along the hinges for storage or transport, while the deployed configuration refers to a state in which the reflector has articulated along the hinges to assume a predetermined three-dimensional curvature. These terms are used consistently throughout the specification to describe the functional states of the reflector, regardless of the specific folding pattern, platform type, or deployment mechanism employed.

[0054] FIG. 2 further illustrates a “Stow & Go” phase, emphasizing the ability of the deployable antenna to be retracted after deployment. In this phase, the reflector 102 is actively or passively returned toward its substantially flat configuration by reversing the deployment sequence. Actuators, cables, motors, or other mechanisms may be used to overcome stored strain energy and fold the reflector 102 along the hinges 104 back into its stowed geometry. This retraction capability enables rapid maneuvering of the satellite platform, such as for threat avoidance, collision avoidance, orbital relocation, or repositioning for a new mission objective. By reducing the deployed cross-sectional area and structural leverage, the satellite can safely execute higher- acceleration maneuvers without subjecting the reflector 102 or hinges 104 to excessive loads.

[0055] The dashed trajectory illustrated in FIG. 2 conceptually represents the satellite transitioning between these operational modes over time, highlighting that deployment and retraction of the reflector 102 are not one-time events but may occur repeatedly as mission needs evolve. The ability to selectively deploy the antenna during active communication, sensing, or power transfer operations, and then re-stow the antenna for maneuvering, concealment, or reconfiguration, provides substantial operational flexibility. Accordingly, FIG. 2 demonstrates an embodiment in which the deployable antenna system supports dynamic mission profiles by enabling controlled deployment and retraction of the reflector 102 on a satellite platform 100Attorney Docket No. 23193.001WO1through coordinated operation of the integrated hinges 104 and associated deployment mechanisms.

[0056] FIG. 3 illustrates an embodiment of a deployable antenna system 200 integrated with a CubeSat platform 206, shown in a stowed configuration prior to deployment. In this embodiment, the antenna 102 is mounted to an exterior face of the CubeSat 206 and is retained in a substantially flat, low-profile configuration that conforms closely to the outer envelope of the CubeSat 206. The antenna 102 is held in this stowed position by a retaining mechanism 202 disposed along an edge or region of the antenna 102. The retaining mechanism 202 may function as a mechanical restraint during launch and as a rotational interface permitting deployment of the antenna 102 away from the CubeSat 206 when the retaining mechanism 202 is released. A second retaining mechanism 204 is positioned on the CubeSat 206 at a location corresponding to a feed point of the antenna 102. In the stowed configuration shown in FIG. 3. the retaining mechanism 204 secures a portion of the antenna 102 against the CubeSat 206 while also occupying a position that will later correspond to the focal region of the deployed antenna 102. The CubeSat 206 may house avionics, power systems, propulsion components, and communication electronics internally, while the antenna 102 remains externally mounted and fully restrained to withstand launch loads and environmental stresses.

[0057] FIG. 4 illustrates the deployable antenna system 200 of FIG. 3 in a deployed operational configuration. In this embodiment, the antenna 102 has rotated away from the CubeSat 206 about the retaining mechanism and hinge 202, transitioning from the substantially flat stowed configuration to a deployed configuration in which the antenna 102 assumes a predetermined three-dimensional curvature suitable for reflective operation. The retaining mechanism 204 now functions as a feed antenna, positioned relative to the deployed antenna 102 such that electromagnetic energy transmitted from or received by the feed is reflected by the antenna 102. The spatial relationship between the feed antenna 204 and the antenna 102 may correspond to a focal point or focal region of the deployed reflective surface. FIG. 4 further shows deployable solar panels 210 extending outward from the CubeSat 206. These solar panels 210 may be hingedly mounted and configured to deploy independently or in coordination with deployment of the antenna 102. The solar panels 210 provide electrical power to the CubeSat 206 and may be arranged to minimize interference with the deployed antenna 102 whileAttorney Docket No. 23193.001WO1maximizing solar exposure. The deployed configuration illustrated in FIG. 4 demonstrates how the antenna 102 can operate concurrently with other deployable subsystems of the CubeSat 206.

[0058] FIG. 5 illustrates another view of the deployable antenna system 200, emphasizing the articulation of the antenna 102 relative to the CubeSat 206 during deployment or retraction. In this embodiment, the antenna 102 is shown partially or fully deployed, extending away from the CubeSat 206 at an angle defined by the retaining mechanism and hinge 202. The retaining mechanism 202 provides a controlled rotational interface that allows the antenna 102 to pivot smoothly between stowed and deployed positions while maintaining alignment and structural integrity. The retaining mechanism 204 is shown positioned on the CubeSat 206 such that, when the antenna 102 is fully deployed, the retaining mechanism 204 operates as a feed antenna aligned with the reflective surface of the antenna 102. This figure highlights how the antenna 102 may be actively retracted by reversing the deployment motion, rotating back toward the CubeSat 206 about the hinge 202 until the antenna 102 is again secured in its stowed configuration by the retaining mechanisms 202 and 204. Such reversible deployment enables repeated cycles of deployment and retraction to support dynamic mission requirements.

[0059] FIG. 6 illustrates an embodiment of the antenna 102 removed from the CubeSat context to show structural features that support and stiffen the deployed antenna 102. In this figure, the antenna 102 is shown in a deployed, curved configuration supported by an outer support structure 220 that extends around a perimeter of the antenna 102. The outer support structure 220 is configured from a rigid yet flexible material, allowing it to store strain energy when deformed and to provide edge stiffness and shape retention when deployed. One or more internal support structures 222 and 224 are disposed on a backside of the antenna 102 and extend across portions of the reflective surface. The support structures 222 and 224 may be configured as ribs or stiffening members formed from a rigid yet flexible material that allows them to flex during folding while providing increased structural rigidity when the antenna 102 is deployed. These support structures 222 and 224 cooperate with the outer support structure 220 to maintain the desired three-dimensional curvature of the antenna 102, resist deformation due to thermal or dynamic loads, and improve surface figure accuracy during operation. FIG. 6 demonstrates how the antenna 102 can achieve a balance between deployability and deployed stiffness through the combined use of flexible structural elements that are integrated into the antenna architecture.Attorney Docket No. 23193.001WO1

[0060] FTG. 7 illustrates a representative embodiment of a method and associated control logic for stowing and deploying a deployable reflector antenna, shown as a flowchart 300. The flowchart 300 depicts an ordered sequence of operations that may be performed to transition a reflector between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature. In some embodiments, one or more steps of the flowchart 300 are executed under the supervision of a controller, such as an onboard flight computer or other electronic control unit associated with a platform on which the antenna is mounted. The controller may be communicatively coupled to one or more actuators and / or restraint mechanisms and may issue commands to restrain, release, deploy, and optionally re-stow the reflector based on mission timing, operational criteria, system health, or commanded mode changes.

[0061] As shown in the flowchart 300, the method begins with step 302, which represents providing a reflector having a plurality of hinges integrated into the reflector and defining a crease pattern. The reflector provided at step 302 is configured to be reconfigurable between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature. In this context, the plurality of hinges integrated into the reflector define fold lines that may follow an origami-inspired crease pattern, including Miura-Ori or variations thereof, to enable a controlled folding kinematic path. The reflector provided at step 302 may be formed as a continuous composite laminate surface or, in other embodiments, may include multiple rigid regions joined by the hinges. In either arrangement, the integrated hinges permit repeated articulation while maintaining sufficient structural continuity for the reflector to assume and maintain its desired deployed curvature.

[0062] The flowchart 300 proceeds to step 304, which represents stowing the reflector in the substantially flat configuration by folding the reflector along the plurality of hinges.During step 304, the reflector is folded according to the crease pattern such that the reflector transitions into a compact, substantially planar geometry suitable for packaging. This folding operation may be performed during assembly, integration, or prior to launch, and in some embodiments may be performed or assisted by an actuator under controller command. Folding the reflector along the hinge-defined fold lines may introduce elastic strain into one or more portions of the reflector, thereby storing strain energy that can later contribute to deployment.Attorney Docket No. 23193.001W01

[0063] The method then proceeds to step 306, which represents restraining the reflector in the substantially flat configuration on a platform. In step 306, the folded reflector is secured against the platform by one or more retaining mechanisms, latches, clamps, cables, or other restraints configured to hold the reflector in its stowed geometry. In some embodiments, a controller directs an actuator to engage, lock, or otherwise set the restraint so that the reflector remains stowed through expected environmental loads, such as vibration, shock, and acceleration. The restraint may be implemented in a manner that is releasable on command to enable deployment at a selected time.

[0064] After the reflector is restrained in step 306, the flowchart 300 includes a decision operation 308 labeled “Deploy Antenna?” In the decision operation 308, the controller or other logic determines whether deployment of the reflector is desired. This determination may be based on a schedule, a ground command, a mission phase, a communication requirement, an attitude state, a safety interlock, or a combination of conditions. If the determination at decision operation 308 is “No,” the method follows the “No” branch to 306, and the reflector remains restrained in the stowed configuration while the system continues to wait for a future condition or command that triggers deployment.

[0065] If the determination at decision operation 308 is “Yes,” the method proceeds along the “Yes” branch to step 310, which represents releasing the reflector from the restrained configuration. In step 310, the restraint previously engaged in step 306 is disengaged, such as by unlocking a latch, releasing a pin, paying out a restraining cable, unlatching a clamp, or otherwise removing the constraint that prevents motion of the reflector. In some embodiments, this release is actively commanded, such that the controller directs an actuator to release the reflector from the restrained configuration. The actuator may include a motorized latch, a shapememory device, a solenoid, a pin-puller, a cable-driven mechanism, or another selectively actuable release device. The controller may additionally enforce one or more interlocks prior to commanding release, such as confirming a safe attitude, verifying clearance from other deployables, and confirming adequate power and thermal conditions.

[0066] Following release at step 310, the method proceeds to step 312, which represents permitting the reflector to articulate along the plurality of hinges such that deployment from theAttorney Docket No. 23193.001W01substantially flat configuration to the deployed configuration is driven at least in part by strain energy stored in the reflector. In step 312, once the restraining mechanism no longer holds the reflector flat, the stored strain energy within the folded reflector and its hinge-defined crease pattern produces a restorative force that drives unfolding motion. The hinges guide the reflector’s kinematic path, allowing controlled rotation or bending along the fold lines as the reflector transitions toward the predetermined three-dimensional curvature. In some embodiments, step 312 may include passive deployment driven primarily by stored strain energy, while in other embodiments the controller may further direct one or more actuators to assist deployment, synchronize motion across multiple hinge regions, or regulate deployment speed using a ratelimiting mechanism. For example, the controller may command a motor or damper system to manage deployment rate to reduce shock loads imparted to the platform.

[0067] Upon completion of step 312, the reflector is in the deployed configuration and is positioned for operational use with an associated feed element. In some embodiments, the controller may monitor deployment completion using sensors, limit switches, motor current signatures, or attitude / structural response data, and may transition the system into an operational mode once the deployed geometry is confirmed. In further embodiments, the same controller may later direct an actuator to reverse the sequence, thereby re-folding and re-restraining the reflector back into the substantially flat configuration for re-stowage, enabling multiple cycles of deployment and retraction as mission needs evolve.

[0068] In some embodiments, the reflector may be returned from the deployed configuration to the substantially flat stowed configuration by reversing the deployment sequence under the control of a controller. Following completion of a mission phase or upon receipt of a re-stow command, the controller may direct one or more actuators to engage the reflector and apply forces that overcome the stored strain energy that maintains the reflector in its deployed geometry. The actuator may be mechanically coupled to one or more hinges, support structures, perimeter members, cables, or retaining mechanisms such that commanded actuation causes the reflector to begin folding along the plurality of hinges that define the crease pattern.Attorney Docket No. 23193.001WO1

[0069] As the actuator applies force, the reflector articulates along the hinges in a controlled manner, progressively collapsing from the predetermined three-dimensional curvature toward the substantially flat configuration. During this re-stow operation, the controller may regulate the rate of motion by coordinating the actuator with a rate-limiting mechanism, such as a motor, damper, escapement, or controlled cable payout, to prevent excessive dynamic loads or unintended snap-through behavior. As the reflector folds, strain energy is again stored within the reflector structure, the hinges, and any associated support elements.

[0070] Once the reflector reaches the substantially flat stowed configuration, the controller may direct the actuator to re-engage one or more retaining mechanisms to restrain the reflector against the platform. The retaining mechanisms may lock the reflector in place to withstand maneuvering loads, environmental disturbances, or subsequent launch or transport conditions. In this manner, the reflector may be repeatedly transitioned between deployed and stowed configurations in a predictable and controlled fashion, enabling dynamic mission operations, platform mobility, and repeated use without structural degradation.

[0071] FIGS. 8 A and 8B illustrate one embodiment of a reflector 400 configured with a single-fold deployment architecture. FIG. 8A depicts the reflector 400 in a stowed configuration, in which the reflector surface is folded along a single primary hinge line such that the reflector collapses into a compact, layered geometry. In this stowed state, opposing portions of the reflector 400 are brought into close proximity, reducing the overall envelope and enabling efficient packaging on a host platform. The hinge defining the single fold may be formed as an integrated compliant hinge within the reflector structure, allowing elastic bending while maintaining structural continuity. FIG. 8B illustrates the same reflector 400 during deployment, in which the reflector unfolds about the single hinge line. As the hinge articulates, the reflector surface separates and rotates outward, progressively transitioning toward its deployed shape. The unfolding motion may be driven at least in part by strain energy stored in the reflector during folding, optionally assisted or regulated by an actuator or damping mechanism. Once fully deployed, the reflector 400 assumes a predetermined three-dimensional curvature suitable for reflective operation.Attorney Docket No. 23193.001W01

[0072] FIGS. 9A and 9B illustrate another embodiment of a reflector 420 employing a multi-fold configuration. FIG. 9 A shows the reflector 420 in a stowed configuration, where the reflector surface is folded along multiple, generally parallel hinge lines to form an elongated, stacked geometry. In this arrangement, the reflector is subdivided into multiple panels or regions that overlap in the stowed state, significantly reducing the deployed footprint while maintaining a compact form factor. FIG. 9B illustrates the reflector 420 in an unfolded or partially deployed configuration, in which the multiple folds have opened and the individual regions of the reflector rotate relative to one another about their respective hinges. The hinges guide the unfolding motion such that the reflector expands outward and begins to approximate the intended deployed curvature. This multi-fold approach allows larger reflectors to be stowed within constrained volumes while enabling controlled deployment through sequential or simultaneous articulation of multiple hinge lines.

[0073] FIGS. 10A through 10D illustrate a further embodiment of a reflector 440 configured with a multi-fold architecture that transitions through several intermediate stages during deployment. FIG. 10A depicts the reflector 440 in a fully stowed configuration, in which the reflector surface is folded along a plurality of hinge lines such that multiple layers of the reflector overlap in a compact stack. FIG. 10B illustrates an early stage of deployment, in which one or more folded sections begin to rotate outward from the stowed stack, separating adjacent layers and initiating expansion of the reflector. FIG. 10C shows a plan view of the reflector 440 at an intermediate stage, where the hinge pattern defining the fold lines is visible across the reflector surface. At this stage, the reflector is partially unfolded but has not yet achieved its final curvature. FIG. 10D illustrates the reflector 440 in a further deployed state, in which the reflector surface has substantially unfolded and the hinge-defined regions have articulated to form a continuous, curved surface. The multi-stage unfolding shown in FIGS. 10A-10D demonstrates how complex folding patterns may be used to achieve controlled deployment of large reflective surfaces while managing strain, alignment, and surface accuracy.

[0074] FIGS. 11A through 1 ID illustrate another embodiment of a reflector 460 employing a polygonal “bloom” folding configuration. FIG. 11A depicts the reflector 460 in a stowed configuration, in which multiple polygonal segments are folded inward and stacked in a radially symmetric arrangement resembling a closed bloom or rosette. In this configuration, theAttorney Docket No. 23193.001WO1reflector occupies a compact, generally cylindrical or polygonal volume. FIG. 1 IB illustrates the reflector 460 in a partially deployed configuration, where the polygonal segments begin to rotate outward about hinge lines arranged in a radial pattern. As deployment progresses, the segments spread apart and flatten relative to one another, increasing the effective aperture. FIG. 11C illustrates a plan view of the reflector 460 at an intermediate stage, showing the network of hinge lines that define the polygonal folding pattern across the reflector surface. FIG. 1 ID illustrates the reflector 460 in a fully deployed configuration, in which the polygonal segments have fully unfolded and collectively form a substantially continuous reflective surface having a predetermined three-dimensional curvature. The bloom-style deployment enables large-area reflectors to be compactly stowed and smoothly deployed through coordinated radial articulation of multiple hinge-connected regions.

[0075] The reflector folding configurations illustrated in FIGS. 8A-11D demonstrate a range of possible folding architectures, including single-fold, multi-fold, sequential unfolding, and polygonal bloom configurations. These embodiments are merely exemplary, as many other reflector folding configurations may be implemented as a matter of design choice depending on desired stowed volume, deployed aperture size, surface accuracy, deployment dynamics, and platform constraints. The claims are intended to cover all forms of folding deployable reflectors, including variations and combinations of folding patterns that enable a reflector to transition between a compact stowed configuration and a deployed configuration suitable for reflective operation, without limitation to the specific folding geometries illustrated herein.

[0076] Any of the above embodiments herein may be rearranged and / or combined with other embodiments. Accordingly, the concepts herein are not to be limited to any particular embodiment disclosed herein. Any of the various computing and / or control elements shown in the figures or described herein may be implemented as hardware, as a processor implementing software or firmware, or some combination of these. For example, an element may be implemented as dedicated hardware. Dedicated hardware elements may be referred to as “processors,” “controllers,” or some similar terminology. When provided by a processor, the functions may be provided by a single dedicated processor, by a single shared processor, or by a plurality of individual processors, some of which may be shared. Moreover, explicit use of the term “processor” or “controller” should not be construed to refer exclusively to hardware capableAttorney Docket No. 23193.001WO1of executing software, and may implicitly include, without limitation, digital signal processor (DSP) hardware, a network processor, application specific integrated circuit (ASIC) or other circuitry, field programmable gate array (FPGA), read only memory (ROM) for storing software, random access memory (RAM), non-volatile storage, logic, or some other physical hardware component or module. Some examples of software include but are not limited to firmware, resident software, microcode, etc.

[0077] Any of the computing or control elements described herein, including that illustrated in FIG. 12, may be realized in dedicated hardware, in programmable hardware executing software or firmware, or in any suitable combination thereof. For example, a module may be implemented as a processor executing coded instructions, as a digital signal processor (DSP), application- specific integrated circuit (ASIC), field-programmable gate array (FPGA), network processor, or other logic circuitry. The explicit use of terms such as “processor,” “controller,” or “engine” is intended to encompass any physical computing element - whether dedicated or shared - that performs the described operations. When provided by a processor executing instructions, the functions may be distributed among multiple processors or cores, executed sequentially or in parallel, and may employ vectorized or GPU-accelerated computation. In some embodiments, the disclosed configuration yields measurable reductions in processing latency and memory utilization relative to conventional software pipelines, representing a technical improvement in computer performance.

[0100] In one exemplary embodiment, instructions stored on a non-transitory computer-readable medium direct a computing system, cloud instance, or networked computing node, to perform the operations disclosed herein. Portions or all of the operations may be executed in a networked or cloud-computing environment that provides elastic compute and storage resources. Cloud computing, as used herein, refers to on-demand provisioning of shared computing infrastructure that supports broad network access, resource pooling, rapid elasticity, and measured service.

[0101] FIG. 12 illustrates an exemplary cloud-computing system 500 that may be used, in some embodiments, to support communications associated with deployment, verification, operation, and re-stowage of a deployable antenna carried by a remote platform such as a satellite, including a CubeSat. In these embodiments, the physical actuator that releases andAttorney Docket No. 23193.001W01deploys the antenna is typically located on the platform itself, because the platform must mechanically restrain and then physically manipulate or release the reflector. However, FIG. 12 depicts how computation, command generation, operational scheduling, telemetry processing, and post-deployment communications management may be implemented by a distributed computing architecture that is not necessarily co-located with the platform, while still permitting certain components of the architecture to be optionally instantiated on-platform.

[0102] As shown in FIG. 12, the system 500 includes a plurality of computing systems 502-1 through 502-N, each of which may be implemented as a physical server, a virtual machine, a containerized workload, or another execution environment capable of running programmed instructions. The computing systems 502-1 through 502-N are coupled through a cloud network 520 that manages distributed data storage and processing. The cloud network 520 may include a data-storage module 522 and one or more virtualized servers 524-1 through 524-N, along with orchestration and operating-system software, networking hardware, and other infrastructure that enables workloads to be distributed, replicated, and fault-tolerant. In the context of antenna deployment and communications, this architecture allows command sequences for deployment, communications configuration, and post-deployment verification to be generated, validated, and scheduled using distributed resources, and further allows large volumes of telemetry and communications-performance data to be ingested and analyzed in near real time.

[0103] In some embodiments, the deployable antenna system on the platform includes at least one actuator configured to restrain, release, deploy, and optionally re- stow a reflector, and the platform further includes an onboard controller that is responsible for issuing direct actuator commands and enforcing local interlocks. The onboard controller may be a flight computer, microcontroller, or other embedded processor that executes time-critical control loops and safety logic, such as verifying that the platform is in a safe attitude, verifying that a deployment window is active, verifying electrical power margin, and verifying that other deployables have cleared. In such embodiments, the cloud-computing system 500 is not required to physically operate the actuator, but instead may provide higher- level operational intelligence and communications support. For example, the system 500 may compute and deliver one or more deployment command packages to the platform ahead of time, such as during a ground- station pass, enabling the platform to autonomously execute deployment at a later time even when disconnected from the ground.Attorney Docket No. 23193.001WO1

[0104] Each computing system 502 may include at least one processor 504 coupled to program and data memory 506, I / O devices 508, a network interface 510, a display-device interface 512, and a computer-readable storage medium 514, interconnected by a system bus 516. In implementations supporting antenna deployment operations, the processor 504 may execute software modules that perform functions such as mission planning, event scheduling, actuator command sequencing, fault-detection and recovery logic, and communications link optimization. Program and data memory 506 may store executable code, cached telemetry, ephemeris data, predicted link budgets, antenna pointing profiles, and deployment constraints. The storage medium 514 may store longer-term records, including deployment event logs, actuator health history, environmental data, and performance measurements associated with the antenna and feed.

[0105] In some embodiments, the network interface 510 of one or more computing systems 502 is used to communicate with a ground-station network, a mission operations center, or an intermediate communications gateway that relays commands to and receives telemetry from the platform. In operation, the system 500 may generate a planned deployment timeline, including the expected time of release, the expected duration of deployment motion, and the expected time at which communications should switch from a low-gain stowed-antenna mode to a high-gain deployed- antenna mode. The cloud network 520 may disseminate this timeline to multiple computing systems 502 to provide redundancy and to enable parallel simulation or verification of the deployment sequence. For instance, one computing system 502-1 may compute and validate a deployment command sequence under nominal conditions, while another computing system 502-2 may compute alternative sequences for contingency conditions, such as reduced battery state-of-charge, elevated actuator current draw, or constrained attitude pointing. The distributed environment provided by the cloud network 520 permits these computations to occur concurrently, with results stored in the data-storage module 522 for retrieval by mission operators or automated uplink services.

[0106] In some embodiments, the cloud-computing system 500 is used to support communications during deployment by managing mode transitions and by scheduling communication windows to coincide with predicted deployment states. The system 500 may account for these expected dynamics by directing that the platform maintain a robust communications mode during deployment, such as using a fallback omnidirectional antenna, aAttorney Docket No. 23193.001W01lower data rate, a more robust modulation and coding scheme, or increased forward error correction, until sensors confirm that the deployed antenna has reached its operational geometry. In certain embodiments, the system 500 may compute a set of communications parameters, including transmit power, coding rate, frequency selection, and antenna pointing constraints, and provide those parameters to the platform prior to deployment, thereby enabling the platform to automatically change link settings at predetermined milestones during the deployment sequence.

[0107] In some embodiments, communications after deployment are managed by the cloud-computing system 500 by ingesting telemetry that confirms deployment completion and then coordinating a transition to high-performance communications using the deployed reflector antenna. For example, once the platform reports that an actuator has released a restraint and that the reflector has fully deployed based on sensor feedback, motor current profiles, latch-state indicators, or attitude response signatures, the system 500 may trigger subsequent operational steps. These steps may include commanding the platform to activate a feed element associated with the deployed reflector, scheduling a high-rate downlink session, updating pointing commands to align the deployed reflector with a target ground station or relay satellite, and initiating calibration procedures. Calibration procedures may include measuring received signal strength, evaluating bit-error rates, scanning pointing offsets to optimize peak gain, and characterizing wideband performance across multiple frequencies. The system 500 may store the resulting calibration data in the data-storage module 522 and may use virtualized servers 524-1 through 524-N to perform computationally intensive analytics, such as estimating reflector surface accuracy based on measured beam patterns, predicting degradation trends, or generating updated control parameters for subsequent deployments and re-stows.

[0108] In some embodiments, the cloud-computing system 500 may also support re-stow operations and associated communications. If mission requirements call for the antenna to be retracted, the system 500 may generate a re-stow command sequence and schedule uplink transmission during a communications window. Prior to re-stow, the system 500 may command the platform to enter a safe communications configuration that accounts for anticipated reduction in gain as the antenna folds. The platform may then execute actuator commands locally to fold and restrain the reflector, while continuing to provide telemetry through the best available communications path. Following re-stow, the cloud-computing system 500 may analyze actuatorAttorney Docket No. 23193.001WO1telemetry to detect anomalies, such as elevated torque, incomplete latching, or unexpected deployment rate, and may update future command sequences accordingly.

[0109] Although FIG. 12 depicts the cloud-computing system 500 as remote from the platform, in some embodiments one or more components of the system 500 may be instantiated on the platform itself. For example, a computing system 502 may be implemented as an onboard processing module that includes a processor 504, memory 506, and storage medium 514, configured to execute a subset of the same software modules described above. This onboard instance may perform local decision-making during periods of limited connectivity, such as determining whether to proceed with deployment based on locally sensed power, attitude, thermal conditions, and actuator health. In such embodiments, the onboard computing system may synchronize logs and telemetry to the remote cloud network 520 when connectivity becomes available. Similarly, portions of the data-storage module 522 may be mirrored or cached on-platform, enabling mission scripts and deployment parameters to be stored locally for later execution.

[0110] Accordingly, FIG. 12 illustrates a flexible computing architecture in which distributed computing systems 502-1 through 502-N, operating through the cloud network 520 with virtualized servers 524-1 through 524-N and a data-storage module 522, may cooperate with a remotely deployed platform to support communications and control associated with antenna deployment and retraction. The platform may execute actuator commands locally to physically release and deploy the antenna, while the cloud-computing system 500 provides planning, command packaging, telemetry ingestion, deployment verification, communications optimization, and post-deployment operational management. This division of responsibilities enables time-critical mechanical actions to remain onboard the platform while leveraging scalable remote computation to improve reliability, situational awareness, and communications performance during and after deployment

Claims

Attorney Docket No. 23193. OOlWOlClaimsWhat is claimed is:

1. A deployable antenna, comprising:a reflector configured to assume a predetermined three-dimensional curvature when in a deployed configuration; anda plurality of hinges disposed along the reflector and defining a crease pattern permitting the reflector to transition between the deployed configuration and a substantially flat stowed configuration.

2. The deployable antenna of claim 1, wherein the predetermined three-dimensional curvature comprises a parabolic geometry.

3. The deployable antenna of claim 1, wherein the reflector comprises a composite laminate including at least one structural fiber-reinforced layer.

4. The deployable antenna of claim 3, wherein the composite laminate further comprises a reflective layer selected from an electrically conductive material or an optically conductive material.

5. The deployable antenna of claim 1, wherein the reflector comprises a tessellated or faceted surface formed from a plurality of rigid panels connected by the hinges.

6. The deployable antenna of claim 1, wherein at least one hinge comprises a compliant material embedded within the reflector, the compliant material being configured from an aromatic polyamide fiber material.Attorney Docket No. 23193.001WO17. The deployable antenna of claim 1 , wherein the crease pattern comprises at least one of an Miura-Ori crease pattern, a Yoshimura crease pattern, or a fan fold pattern, a single fold pattern, a simple vertex pattern, a scroll fold pattern, a waterbomb fold pattern, a polygon bloom pattern, an even-gon twist pattern, a tri-fold taco pattern, or a flattening trough pattern.

8. The deployable antenna of claim 1, wherein transition from the stowed configuration to the deployed configuration is driven at least in part by strain energy stored in the reflector.

9. The deployable antenna of claim 1, further comprising an actuator configured to deploy or re-stow the reflector.

10. The deployable antenna of claim 1, further comprising a rate-limiting mechanism to control deployment speed.

11. The deployable antenna of claim 1 , further comprising a perimeter support structure configured to strengthen the reflector when deployed.

12. The deployable antenna of claim 1, further comprising a feed element positioned to receive or transmit electromagnetic energy reflected by the reflector.

13. The deployable antenna of claim 1, wherein the antenna is configured for radiofrequency communication.

14. The deployable antenna of claim 1, wherein the antenna is configured for use on a satellite.

15. The deployable antenna of claim 1, wherein the reflector is configured for repeated deployment and re-stow cycles without permanent deformation.

16. The deployable antenna of claim 1, further comprising one or more deployable structural supports affixed to the backside of the reflector.Attorney Docket No. 23193. OOlWOl17. A method of deploying a reflector antenna, the method comprising:providing a reflector having a plurality of hinges integrated into the reflector and defining a crease pattern, the reflector being configurable between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature;stowing the reflector in the substantially flat configuration by folding the reflector along the plurality of hinges;restraining the reflector in the substantially flat configuration on a platform; releasing the reflector from the restrained configuration; anddeploying the reflector from the substantially flat configuration to the deployed configuration by permitting the reflector to articulate along the plurality of hinges, wherein deployment is driven at least in part by strain energy stored in the reflector.

18. A non-transitory computer readable medium comprising instructions that, when executed by a controller, direct the controller to deploy a reflector antenna having a plurality of hinges integrated into the reflector and defining a crease pattern, the reflector being configurable between a substantially flat stowed configuration and a deployed configuration having a predetermined three-dimensional curvature, the instructions further directing the controller to:direct an actuator to restrain the reflector in a substantially flat configuration on a platform, wherein the reflector is folded along the plurality of hinges;direct the actuator to release the reflector from the restrained configuration to deploy the reflector from the substantially flat configuration to the deployed configuration by permitting the reflector to articulate along the plurality of hinges, wherein deployment is driven at least in part by strain energy stored in the reflector.

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