Description:TECHNICAL FIELD
[0001] The present disclosure relates to the field of spaceborne communication, astronomical observation and/or satellite systems. More particularly, the present disclosure relates to a rollable and/or Z-foldable reflector array antenna system designed for space antennas, enabling compact stowage, efficient deployment, and reliable operation in various radio frequency (RF) bands for satellite communication, astronomical observation, and other space applications.

BACKGROUND
[0002] Background description includes information that may be useful in understanding the present invention. It is not an admission that any of the information provided herein is prior art or relevant to the presently claimed invention, or that any publication specifically or implicitly referenced is prior art.
[0003] A reflector array antenna is a specialized system used on spacecraft or satellites, designed to handle radio frequency (RF) transmission and reception. These antennas are essential for enabling communication between the satellite and ground stations or other spacecraft, as well as for conducting earth and planetary observations from space.
[0004] The primary component of a reflector array antenna is its large reflective surface, known as the reflector. This surface is crucial because it directs RF electromagnetic waves, which are the carriers of communication signals. These RF waves are first generated by an RF source or generator aboard the satellite. The generated waves are then transmitted to the reflector array via an RF feeder, which directs the waves toward the reflector. The reflector’s purpose is to bounce these RF waves back in a focused direction, either towards Earth or towards other targets in space, depending on the satellite’s mission. The reflector performs an additional task of receiving signals from the Earth, or other spacecraft and reflecting them toward the RF receiver.
[0005] One of the significant challenges associated with reflector array antennas is their size. For optimal performance, these antennas need to be large, as a bigger reflector surface allows for better signal strength. However, a large size poses a problem during the satellite’s journey from the ground to space. The satellite must fit into a launch vehicle, where space is limited, and every component needs to be as compact as possible to ensure safe transport.
[0006] To address this, reflector array antennas are designed to be stowable. They are engineered to fold or roll into a small volume, making them easier to store, transport, and launch. Once the satellite reaches its designated orbit or position in space, the antenna can then be deployed to its full operational size. This deployment is a critical process, as the antenna must return to its precise operational shape and configuration to function correctly.
[0007] In its deployed state, the reflector array antenna enables the satellite to carry out the primary functions—transmitting and receiving RF signals. These signals are vital for communication, allowing the satellite to send data back to Earth or to relay information between different points in space. The antenna also plays a crucial role in observation missions, where it receives data from the Earth’s surface or other celestial bodies, contributing to scientific research, weather forecasting, and other applications.
[0008] There is, therefore, a need to address these challenges by introducing a rollable and Z-foldable reflector array system designed for space antennas, enabling compact stowage, efficient deployment, and reliable operation in various radio frequency (RF) bands for satellite communication.

OBJECTS OF THE PRESENT DISCLOSURE
[0009] Some of the objects of the present disclosure, which at least one embodiment herein satisfies are as listed herein below.
[00010] It is an object of the present disclosure is to develop a rollable and Z-foldable multi-layer reflector array antenna that can be stowed in a compact form for transportation, storage, and launch.
[00011] It is an object of the present disclosure to develop a deployment mechanism that passively (without the use of any actuators) deploys the reflector array antenna from the stowed configuration to the operational configuration.
[00012] It is an object of the present disclosure is to provide super-wideband performance in the proposed antenna design, allowing it to support high data rates and reliable connectivity for various IoT applications.
[00013] It is an object of the present disclosure is to provide a flexible design that allows the antenna to operate effectively across a wide range of RF bands, enabling versatile communication and observation capabilities.
[00014] It is an object of the present disclosure is to incorporate advanced materials and mechanisms that facilitate the antenna’s ability to withstand the harsh conditions of space, including extreme temperatures, radiation, and mechanical stress during deployment.
[00015] It is an object of the present disclosure to enhance the overall performance of the antenna system, including improved signal strength, accuracy, and durability, thereby increasing the efficiency and reliability of spaceborne communication and observation missions.

SUMMARY
[00016] The present disclosure relates to the field of spaceborne communication, astronomical observation, and satellite systems. More particularly, the present disclosure relates to a rollable and Z-foldable reflector array antenna system designed for space antennas, enabling compact stowage, efficient deployment, and reliable operation in various radio frequency (RF) bands for satellite communication, astronomical observation, and other space applications.
[00017] A reflector array antenna system with a deployable multi-layer structure may be configured to include one or more rollable booms that are partially and/or fully cylindrical composite members; a rigid or flexible frame configured to enable the one or more rollable booms to extend, unwinding a cylindrical mandrel and deploying the reflector array antenna system to the operational state; one or more layers including a top facesheet (housing conductive RF reflective patches) and a bottom facesheet (housing antenna ground plane), where the one or more layers are separated by predetermined distances, and the predetermined distances may be configured to allow the one or more layers to be collapsed and rolled onto a cylindrical mandrel or stored in an accordion fold, while maintaining the ability to operate in at least one RF band.
[00018] Furthermore, the reflector array antenna system includes a hold-down and release mechanism configured to secure one end of the cylindrical mandrel to the base frame, over which a reflector array assembly containing the one or more layers is positioned.
[00019] In an aspect, the flexible composite spacer members may be positioned between the two or more layers to maintain a fixed separation in a deployable configuration and are capable of collapsing during stowage and returning to their original shape and size as needed.
[00020] In an aspect, a hold down and release mechanism is configured to secure the deployable reflector array in a stowed configuration.
[00021] In an aspect, an electromechanically controlled release actuator configured to release the hold down and release mechanism, enabling the deployment of the reflector array when desired, upon satellite reaching the intended orbit of the satellite, or when the spacecraft attains a specific spatial location, where the reflector array antenna system may be configured to deploy in one or more directions; and the deployed angle of the reflector array antenna is 180°.
[00022] In an aspect, the deployable mechanism is further configured to fold along the width to minimize the stowed configuration.
[00023] In an aspect, the antenna may further include a combination of a reflector array and solar cell arrays, with the solar cell arrays positioned on one side of the bottom layer, and a continuous conductive layer that is co-cured/adhered/printed to the bottom layer on another side; and the antenna RF reflective patches on another adjacent/top layer.
[00024] In an aspect, one or more reflector arrays may be accommodated to face the same direction or one or more reflector arrays with a particular orientation.
[00025] In an aspect, the reflector array antenna system may be configured for a dual antenna setup, the dual antenna configuration can include one antenna on the one or more layers serving the earth-facing side, and a second antenna mounted on the opposite side of the one or more layers, serving the space-facing side with the satellites in higher orbits enabling inter-satellite link.
[00026] In an aspect, a monitoring device may be configured to indicate whether the reflector array is in any of the stowed or deployed configuration, with the ability to communicate the information to any or a combination of the satellite, spacecraft, or via telemetry.
[00027] Various objects, features, aspects and advantages of the present disclosure will become more apparent from the following detailed description of preferred embodiments, along with the accompanying drawing figures in which like numerals represent like features.
[00028] Within the scope of this application it is expressly envisaged that the various aspects, embodiments, examples and alternatives set out in the preceding paragraphs, in the claims and/or in the following description and drawings, and in particular the individual features thereof, may be taken independently or in any combination. Features described in connection with one embodiment are applicable to all embodiments, unless such features are incompatible.

BRIEF DESCRIPTION OF THE DRAWINGS
[00029] The accompanying drawings are included to provide a further understanding of the present disclosure, and are incorporated in and constitute a part of this specification. The drawings illustrate exemplary embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure. The diagrams are for illustration only, which thus is not a limitation of the present disclosure.
[00030] In the figures, similar components and/or features may have the same reference label. Further, various components of the same type may be distinguished by following the reference label with a second label that distinguishes among the similar components. If only the first reference label is used in the specification, the description is applicable to any one of the similar components having the same first reference label irrespective of the second reference label.
[00031] FIG. 1 illustrates an exemplary representation of a schematic view of a typical configuration in which a reflector array antenna in deployed configuration, in accordance with an embodiment of the present disclosure.
[00032] FIG. 1A & FIG. 1B illustrates exemplary representations of schematic views of the reflector array antenna in the stowed and deployed configurations, in accordance with an embodiment of the present disclosure.
[00033] FIGs. 1A-1C illustrate exemplary representations of the sequence of deployment of the deployable reflector array antenna system from the stowed to the deployed configuration, in accordance with an embodiment of the present disclosure.
[00034] FIG. 2 illustrates an exemplary representation of the details of cylindrical mandrel assembly, in accordance with an embodiment of the present disclosure.
[00035] FIG. 3 illustrates an exemplary representation of the details of the hold down and release mechanism (HDRM) assembly, in accordance with an embodiment of the present disclosure.
[00036] FIG. 4 illustrates an exemplary representation of the details of the hold down and release mechanism, in accordance with an embodiment of the present disclosure.
[00037] FIG. 5 illustrates an exemplary representation of the details of the reflector array assembly mounted on the circular mandrel, in accordance with an embodiment of the present disclosure.
[00038] FIG. 6 illustrates an exemplary representation of a Z-fold stowing method for the antenna in the second embodiment of the reflector array antenna system, featuring rigid panels, in accordance with an embodiment of the present disclosure.
[00039] FIG. 7 illustrates the sequence of deployment of the second embodiment from the stowed configuration to the deployed configuration, in accordance with an embodiment of the present disclosure.
[00040] FIG. 8 illustrates an exemplary representation of the reflector array assembly mounted on the extension link of the second embodiment, in accordance with an embodiment of the present disclosure.
[00041] FIGs. 9A-9B illustrates exemplary representations of solar cell arrays integrated with the deployable reflector array antenna system with flexible/rigid panel-based reflector array assembly respectively, in accordance with an embodiment of the present disclosure.
[00042] FIGs. 10A-10C illustrates exemplary representations of one or more configurations for mounting and deploying the reflector array antenna onto a spacecraft/satellite.

DETAILED DESCRIPTION
[00043] The following is a detailed description of embodiments of the disclosure depicted in the accompanying drawings. The embodiments are in such detail as to clearly communicate the disclosure. However, the amount of detail offered is not intended to limit the anticipated variations of embodiments; on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the scope of the present disclosure as defined by the appended claims.
[00044] In the following description, numerous specific details are set forth in order to provide a thorough understanding of embodiments of the present invention. It will be apparent to one skilled in the art that embodiments of the present invention may be practiced without some of these specific details. Embodiments of the present disclosure relates to the field of spaceborne communication, astronomical observation and/or satellite systems. More particularly, the present disclosure relates to a rollable and Z-foldable reflector array antenna system designed for space antennas, enabling compact stowage, efficient deployment, and reliable operation in various radio frequency (RF) bands for satellite communication, remote sensing, and other space applications.
[00045] The present disclosure relates to the development of deployable antennas specifically designed for space-based applications, such as communication and planetary observation from spacecraft or satellites. The disclosure addresses the need for antennas that can be stowed compactly during shipment and launch, and then deployed to their full operational configuration once in space.
[00046] The present features a rollable and/or Z-foldable reflector array antenna system, which includes one or more layers of a reflector patch layer and one or more layers of a conductive ground layer. These layers are separated by a specified distance and are crucial for the antenna’s functionality. The entire system, including the patch layer, ground layer, and deployment mechanism, is designed to be stowed in a compact configuration and deployed by unrolling or unfolding once the satellite/spacecraft in orbit or any desired spatial location.
[00047] A key innovation of the present disclosure is the deployment method, which relies on the unrolling of composite booms to achieve the operational configuration of the antenna. This deployment occurs without the use of motors, instead utilizing the strain energy stored in rolled composite cylindrical booms. This method ensures that the antenna deploys to the operational configuration without any actuators, thereby reducing overall weight and eliminating any power drawn from the satellite and therefore providing a compact, lightweight, reliable and efficient solution for space-based reflector array antennas.
[00048] FIG. 1 illustrates an exemplary representation of a schematic view of a typical configuration in which a reflector array antenna is in a deployed configuration, in accordance with an embodiment of the present disclosure.
[00049] In an embodiment, as referred from FIG. 1 a typical configuration in which a reflector array antenna system 100 (interchangeably referred to as an antenna system 100, hereinafter) may be shown in its deployed, operational state, mounted on a satellite or spacecraft 102 for communication and/or planetary and astronomical observation. In the configuration, radio frequency (RF) waves are generated by an RF generator and directed by an RF feed assembly 104 towards the antenna system 100. The antenna system 100 may be designed to reflect these RF waves toward the Earth’s surface or any astronomical object in deep space missions, enabling effective communication or observational operations as intended.
[00050] FIG. 1A & FIG. 1B illustrates exemplary representations of schematic views of the reflector array antenna in the stowed and deployed configurations, in accordance with an embodiment of the present disclosure.
[00051] In an exemplary embodiment, referring to FIG. 1A & FIG. 1B, the antenna system 100 in both its stowed FIG. 1A and deployed FIG. 1B configuration. During launch, large space components for example antennas may be stored in a compact configuration to optimize space and protect the components. Once the satellite reaches its designated orbit, the antenna is deployed to its operational configuration.
[00052] The antenna system 100 can include a base structure 106 to which one or more components of the deployable antenna are affixed. A hold down and release mechanism 108 plays a crucial role by securing the deployable composite booms 112 (interchangeably referred to as a one or more rollable booms 112, hereinafter). The one or more rollable booms 112 are attached at one end to the hold down and release mechanism 108 and at the other end to a cylindrical mandrel 110. A flexible reflector array assembly 114 (interchangeably referred to as one or more layers 114, hereinafter), including a patch layer with reflective patches, flexible composite spacer members and a ground layer separated by a specified distance, is mounted on the cylindrical mandrel 110.
[00053] In an embodiment, the anti-blossoming frame 116 (interchangeably referred to as a rigid or flexible frame 116, hereinafter) can facilitate the deployment process by allowing the composite booms 112, initially rolled onto the cylindrical mandrel 110, to unroll. The frame 116 can be rigid or flexible (using links, chains, etc.). As the one or more rollable booms 112 unroll, they can cause the cylindrical mandrel 110 to unwind, which in turn deploys the one or more layers 114 into its full operational configuration, as illustrated in FIG. 1. The deployment mechanism can ensure that the antenna transitions from a compact stowed state to an expansive operational state efficiently and reliably.
[00054] FIGs. 1A-1C illustrate exemplary representations of the sequence of deployment of the deployable reflector array antenna system from the stowed to the deployed configuration, in accordance with an embodiment of the present disclosure.
[00055] In an exemplary embodiment, FIGs. 1A-1C illustrates the sequence of deployment of the deployable reflector array antenna, transitioning from the stowed to the deployed configuration (from left to right). Once the satellite is in orbit and the antenna is ready for deployment, a single pulse or signal is sent to the hold down and release mechanism 108, which activates the hold down and release mechanism 108. The activation releases the deployable one or more rollable booms 112 along with the cylindrical mandrel 110, on which the one or more layers 114 are mounted.
[00056] Furthermore, upon release, the strain energy stored within the deployable one or more rollable booms 112 can provide the necessary force to initiate the rollout of the cylindrical mandrel 110 and the one or more layers 114. The deployment force, generated by the one or more rollable booms 112, may be continuously applied as the antenna system 100 can progress from the stowed state to a partially deployed state, and ultimately to its fully deployed configuration. The deployment force ceases once the deployable one or more rollable booms 112 have fully extended or when the antenna system 100 reaches its fully deployed state.
[00057] FIG. 2 illustrates an exemplary representation of the details of cylindrical mandrel assembly, in accordance with an embodiment of the present disclosure.
[00058] In an exemplary embodiment, the proposed antenna system 100 may be configured to include the cylindrical mandrel assembly 200. The cylindrical mandrel 110 is a hollow or solid composite structure, typically constructed from materials including any or a combination of, but not limited to, carbon, Kevlar, glass fibres and metals. The cylindrical mandrel 110 can serve as the core over which the one or more layers 114 and the rigid or flexible frame 116 may be equipped with rollers 208, are mounted.
[00059] To harness the strain energy stored in the one or more rollable booms 112 and convert it into the torque or rotational force (referred to as the deployment force) required for deploying the antenna system 100, an anti-blossoming mechanism is employed. The anti-blossoming mechanism can include the rigid or flexible frame 116 with the rollers 208, an anti-blossoming boom bracket 206 with a boom bracket roller 214, and tensioning springs 212. The rigid or flexible frame 116 and the rollers 208 can prevent the deployable one or more rollable booms 112 from “blossoming” or expanding uncontrollably during both stowage and deployment phases. The tensioning springs 212 may be attached to the rigid or flexible frame 116 and the anti-blossoming boom bracket 206, apply the necessary force to the rollers 208 to inhibit any unwanted expansion of the one or more rollable booms 112.
[00060] The anti-blossoming boom bracket 206, in conjunction with the boom bracket roller 214 may generate a counter-torque or counter-rotational force that opposes the deployment force produced by the deployable one or more rollable booms 112. This counterforce is crucial in preventing the antenna assembly from rotating on its axis during deployment. The anti-blossoming boom bracket 206 and the boom bracket roller 214 are supported by a support frame 204, which is secured to C-brackets 202. The cylindrical mandrel 110 can also be attached to the C-brackets 202 via a mandrel mounting fixture 210.
[00061] In an exemplary embodiment, the support frame 204 and the mandrel mounting fixture 210 are typically fabricated from composites including any or a combination of, carbon, Kevlar, or glass fibers, or metals like titanium, aluminum or their alloys. The C-brackets 202 not only hold the cylindrical mandrel 110 and the support frame 204 in place but also play a key role in securing the antenna assembly in its stowed configuration and releasing it when deployment is triggered. The C-brackets 202 are typically made of metals including any or a combination of, but not limited to, titanium, aluminum or their alloys.
[00062] FIG. 3 illustrates an exemplary representation of the details of the hold down and release mechanism (HDRM) assembly, in accordance with an embodiment of the present disclosure.
[00063] In an exemplary embodiment, referring to FIG. 3, the details of the hold down and release mechanism (HDRM) assembly 300. The HDRM assembly 300 may be housed on the base structure 106 along with the hold down and release mechanism 108, the cylindrical mandrels 110 and the C-brackets 202. The primary purpose of the HDRM assembly 300 is to provide the required force to securely hold the entire antenna assembly during stowage and release the assembly when deployment is initiated. The signal to deploy the antenna initiates a pyrotechnic/non-pyrotechnic based release actuator 302, which is holding down the hold down and release mechanism 108 by pulleys 308 and metallic connecting cables 304. A pre-tensioning canister 306 is used to provide the necessary force/tension to the metallic connecting cables 304 such that the hold down and release mechanism 108 can hold the antenna system 100 in stowed condition. Once the pyrotechnic/non-pyrotechnic based release actuator 302 can initiate, the metallic connecting cables 304 under tension are released, thereby releasing the hold down and release mechanism 108 and subsequently the antenna system 100.
[00064] FIG. 4 illustrates an exemplary representation of the details of the hold down and release mechanism 108, in accordance with an embodiment of the present disclosure.
[00065] In an exemplary embodiment, referring to FIG. 4 shows the details of the hold down and release mechanism 400. All the elements of the hold down and release mechanism 108 may be housed in the hold down and release mechanism frame 412, which is held together by the hold down and release mechanism front plate 402 and hold down and release mechanism back plate 420. The purpose of the hold down and release mechanism 108 is to securely hold the entire antenna assembly [C-bracket 202, cylindrical mandrels 110, one or more rollable booms 112 and one or more layers 114] during stowage and then release the antenna assembly when the metallic connecting cables 304 by the way of pulleys 308 have been released.
[00066] During stowage condition, the C-brackets 202 along with the cylindrical mandrel 110, one or more rollable booms 112 and one or more layers 114 may be locked in stowed position by the latching pins 414. The force required to keep the holding pins in locked position may be provided by the pre-tensioned metallic connecting cables 304 by the way of the pulley 308 connected to the retraction shaft 406, which in-turn is connected to the latching pins bracket 418. During deployment, when the metallic connecting cables 304 are released by the pyrotechnic/non-pyrotechnic based release actuator 302, the retraction shaft 406, which is connected to the pulley 308, becomes free to move.
[00067] Now the free retraction shaft 406 may be pushed out by the compressed retraction spring 404. This causes the latching pin bracket 418 may be connected to the retraction shaft 406 to also move out. As the latching pins 414 are housed in the latching pin bracket 418, the pins move out of stowed position and release the C-bracket 202. The free C-brackets 202 are then pushed out by the compressed kickoff springs 408 housed in the kickoff spring housing bracket 416. The kickoff springs 408 can provide the push out force to the C-bracket 202 by the way of kickoff pins 410, thereby initiating the deployment of the rolled up one or more rollable booms 112, cylindrical mandrel 110 and one or more layers 114.
[00068] FIG. 5 illustrates an exemplary representation of the details of the reflector array assembly 114 mounted on the circular mandrel, in accordance with an embodiment of the present disclosure.
[00069] In an exemplary embodiment, referring to FIG. 5 the details of the reflector array assembly mounted on the mandrel 500. The reflector array assembly 114 (also known as one or more layers 114) can consist of a top facesheet 502, that acts as an active reflector plane consists of regions of conductive RF reflective patches 508, bottom facesheet 504, that acts as a ground plane that consists of a continuous conductive layer that is adhered/co-cured/printed to the bottom facesheet 504. The RF reflective patches 508 are typically made of a material with high electrical conductivity and are adhered/co-cured/printed on the top facesheet 502. The top facesheet 502 representative of active reflector plane and bottom facesheet 504 representative of ground plane may be separated/spaced by a predetermined distance using a composite lenticular spacer 506. While FIG. 5 shows a composite lenticular spacer aligned along the length of the antenna system 500, the spacer can be a thin flexible composite structure that maintains a predetermined distance (gap) between the top facesheet 502 and the bottom facesheet 504 including any or a combination of, but not limited to, omega booms, lenticular boom, flattened lenticular boom, and S-springs aligned along the length of the antenna, width of the antenna, any arbitrary orientation or a combination of the above. Additionally, the bottom facesheet 504 can be a passive conducting ground plane, a conductive mesh, or an active component such as a flexible solar cell array 902.
[00070] During stowage, the top facesheet 502, having regions of conductive RF reflective patches 508 and the bottom facesheet 504, having a continuous conductive layer collapse onto each other and are wound around the cylindrical mandrel 110 which are then held in that condition during stowage. Upon the signal to the hold-down release mechanism to release, which then releases the hold down and release mechanism 108 causing the rolled deployable booms to deploy by rolling out and thereby rolling out the cylindrical mandrel 110, the reflector array assembly opens out by unrolling from the cylindrical mandrel 110. As the reflector array assembly 114 opens out, the composite lenticular spacer 506 causes the facesheets (502 and 504) to separate by a predetermined distance. At the end of the deployment process, the entire area of the facesheets are unrolled and separated by a predetermined distance. While the illustration shows two facesheets, a reflector array antenna can have multiple facesheets separated by predetermined distances between them.
[00071] FIG. 6 illustrates an exemplary representation of a Z-fold stowing method for the antenna in the second embodiment of the reflector array antenna system, featuring rigid panels, in accordance with an embodiment of the present disclosure.
[00072] In an exemplary embodiment, FIG. 6 shows a second embodiment of the reflector array antenna 600 with rigid panels. The embodiment features a Z-fold stowing method for the antenna, distinguishing it as the second embodiment in the present disclosure. The embodiment consists of the base structure 106 on which the components of the deployable antenna are attached. The hold down and release mechanism 108 is a key component to which the one or more rollable booms 112 may be attached. The other end of the one or more rollable booms 112 may be attached to an extension link 602 at the extremities and the central slender portion of the extension link 602 is attached to the rigid panel-based reflector array assembly 604. The rigid panel-based reflector array assembly 604 can consist of multiple sandwich panels. The rigid or flexible frame 116, similar to the first embodiment consisting of flexible reflector array assembly 114, can enable the one or more rollable booms 112, rolled onto the cylindrical mandrel 110 to roll out, and in the process translate the extension link 602 thereby unfolding the rigid panel based reflector array assembly 604 to its operational configuration.
[00073] FIG. 7 illustrates the sequence of deployment of the second embodiment from the stowed configuration to the deployed configuration, in accordance with an embodiment of the present disclosure.
[00074] In an exemplary embodiment, FIG. 7 shows the sequence of deployment of the second embodiment from the stowed configuration 700 to the deployed configuration. In the stowed configuration, the multiple panels making up the rigid panel reflector array assembly 604 are stored in an accordion fold or Z-fold for compact stowage. When the antenna is to be deployed, a single pulse/signal is given to the pyrotechnic/non-pyrotechnic based release actuator 302 that releases the hold down and release mechanism 108. This releases the one or more rollable booms 112 along with the extension link 602 to which the rigid panel based reflector array assembly 604 is attached. As soon as the one or more rollable booms 112 are released, the strain energy stored in these booms provide the deployment force necessary to roll-out the extension link 602. As the extension link 602 rolls out, the slender part of the extension link extends. The end panel of the rigid panel based reflector array assembly 604, connected via hinges to each other and to the extension link 602 is extended thereby unfolding the rigid panel based reflector array assembly 604. The deployment force from the one or more rollable booms 112 is continuously provided as the antenna system 100 goes from stowed to partially deployed to fully deployed configuration at which point the accordion folded panels of the rigid panel based reflector array assembly 604 are completely unfolded to a planar configuration. The deployment force from the one or more rollable booms 112 can stop when the one or more rollable booms 112 have reached their full length or when the antenna system 100 reaches fully deployed configuration.
[00075] FIG. 8 illustrates an exemplary representation of the reflector array assembly mounted on the extension link of the second embodiment, in accordance with an embodiment of the present disclosure.
[00076] In an exemplary embodiment, FIG. 8 shows the details of the reflector array assembly 604 mounted on the extension link 602 of the second embodiment 800. The reflector array assembly 604 can consist of multiple rigid panels which are joined to each other by rotary hinges or composite hinges to form the entire assembly. The end panels of the rigid panel based reflector array assembly 604, on either ends, are connected via hinges to the slender member of the extension link. Each panel consists of RF reflective patches 508 that are adhered/co-cured/printed on a top facesheet 802 and continuous conductive material that are adhered/co-cured/printed on a bottom facesheet 804. The top facesheet 802 with the RF reflective patches 508 are separated from the bottom facesheet 804 by a predetermined spacing using foam/honeycomb material 806. The structure, apart from providing the spacing, also gives structural rigidity to the reflector array assembly 604.
[00077] FIGs. 9A-9B illustrates exemplary representations of solar cell arrays integrated with the deployable reflector array antenna system with flexible/rigid panel-based reflector array assembly respectively, in accordance with an embodiment of the present disclosure.
[00078] In an exemplary embodiment, FIGs. 9A can represent the solar cell arrays integrated with the deployable reflector array antenna system with flexible reflector array assembly 900A and FIGs. 9B can represent the solar cell arrays integrated with the deployable reflector array antenna system with rigid panel-based reflector array assembly 900B. The present disclosure incorporating solar cells arrays 900A & 900B in conjunction with the continuous conductive ground layer may be positioned on one of the facesheets. In the embodiment featuring the one or more layers 114, the bottom facesheet 504 can include a continuous conductive ground layer on one side, while the opposing side is equipped with flexible solar cell arrays 902.
[00079] Moreover, in the Z-fold embodiment which is the solar cell arrays integrated with the deployable reflector array antenna system with rigid panel-based reflector array assembly 900B, can include multiple rigid panels, the bottom facesheet 804 similarly features a continuous conductive ground layer on one side and either flexible or rigid solar cells arrays 902 on the other side. The electrical leads from the solar cells arrays 902 are electrically connected to the satellite 102 or spacecraft, enabling the transfer of electrical power generated by the solar cell arrays 902 when subjected to solar irradiance.
[00080] FIGs. 10A-10C illustrates exemplary representations of one or more configurations for mounting and deploying the reflector array antenna onto a spacecraft/satellite.
[00081] In an exemplary embodiment, FIG. 10A - 10C show some typical configurations for mounting and deploying the antenna system 100 onto a spacecraft/satellite 102. While some configurations enable direct deployment of the reflector array antenna (FIG.10A and FIG.10C), some configurations such as the one shown in FIG. 10B may require the antenna to be initially rotated by an angle prior to deployment. The antennas are mounted onto the spacecraft/satellite 102 by custom mounts/yokes that are either connected to the spacecraft/satellite 102 and hold the reflector array antenna in a predetermined orientation relative to the satellite or connected to an orientation mechanism that can modify the orientation of the reflector array antenna relative to the satellite.
[00082] In summary, the present disclosure addressed the challenges of high weight, low stowage efficiency, reduced reliability, and power consumption for deployment inactively deployed reflector array antennas, which typically rely on electric motors for deployment. The present disclosure overcomes the issues by employing a passive deployment mechanism that eliminates the need for motorization. The passive deployment is achieved through the use of fibre-reinforced, high-strain flexible composite material booms. The materials are key to the deployable mechanism, allowing for significant deformation during stowage, which stores strain energy within the material. Upon deployment, the stored strain energy is released in a controlled manner, effectively deploying the reflector array antenna to its operational configuration. As a result, the antenna is more compact, lightweight, and self-deployable, with increased reliability due to fewer components. The antenna also eliminates the need for additional hold down and release mechanisms, reducing overall mass and part count, and operates without drawing power from the satellite or spacecraft, making it an efficient and robust solution for space applications.
[00083] Moreover, in interpreting the specification, all terms should be interpreted in the broadest possible manner consistent with the context. In particular, the terms “comprises” and “comprising” should be interpreted as referring to elements, components, or steps in a non-exclusive manner, indicating that the referenced elements, components, or steps may be present, or utilized, or combined with other elements, components, or steps that are not expressly referenced. Where the specification claims refer to at least one of something selected from the group consisting of A, B, C ….and N, the text should be interpreted as requiring only one element from the group, not A plus N, or B plus N, etc.
[00084] While the foregoing describes various embodiments of the invention, other and further embodiments of the invention may be devised without departing from the basic scope thereof. The scope of the invention is determined by the claims that follow. The invention is not limited to the described embodiments, versions or examples, which are included to enable a person having ordinary skill in the art to make and use the invention when combined with information and knowledge available to the person having ordinary skill in the art.

ADVANTAGES OF THE DISCLOSURE
[00085] Some of the advantages of the present disclosure, which at least one embodiment herein satisfy are as listed herein below.
[00086] The proposed disclosure provides an antenna system which is essential in space applications due to the size constraints of satellite launch vehicles.
[00087] The proposed disclosure provides the design of space deployable mechanisms typically requires advanced education and specialized knowledge, ensuring the antenna’s reliability and efficiency in space.
[00088] The proposed disclosure achieves deployment passively, eliminating the need for motors by harnessing the strain energy stored in flexible high-strain composite material booms.
[00089] The proposed disclosure of the design and fabrication require advanced education, domain specific expertise, and specialized skills, ensuring that the antenna system is both lightweight, compact and highly reliable.
[00090] The proposed disclosure provides the deployment mechanism intricately designed to house the flexible high-strain composite material booms, ensuring that the antenna remains securely stowed without accidental deployment.
[00091] The proposed disclosure guarantees that the reflector array deploys to its operational configuration when needed, preventing undesirable responses during deployment, and maintains the reflector array in its operational state.
[00092] The proposed disclosure of the mechanism demands deep domain expertise and specialized skills, contributing to the overall reliability and performance of the antenna system in space missions.
[00093] The proposed disclosure integrates solar cells into the reflector array antenna, enabling the system to perform both power generation and RF transmission/reception, thereby enhancing the overall functionality of the spacecraft/satellite without the need for additional components.
[00094] In space-based applications, optimizing available surface area is crucial. By incorporating solar cells on the surface of the reflector array, the disclosure ensures that otherwise unused surface area is effectively utilized for power generation, thereby maximizing overall system efficiency.
, Claims:1. A reflector array antenna system (100) with a deployable multi-layer structure, comprising:
one or more rollable booms (112) configured with partially and/or fully cylindrical composite members;
a rigid or flexible frame (116) configured to enable the one or more rollable booms (112) to extend, unwinding a cylindrical mandrel (110) and deploying the reflector array antenna system (100) to the operational state;
one or more layers (114) comprising a top facesheet (502) and a bottom facesheet (504),
wherein the one or more layers (114) are separated by predetermined distances by using flexible or rigid composite spacer members/foam/honeycomb structures (such as 506 and 806) and the predetermined distances are configured to allow the one or more layers (114) to be any of:
collapsed and rolled onto a cylindrical mandrel (110); and
collapsed and stored in an accordion/z-fold, while maintaining the ability to operate in at least one RF band.
a hold down and release mechanism (108) configured to secure one end of the one or more rollable booms (112) to the cylindrical mandrel (110).

2. The reflector array antenna system (100) as claimed in claim 1, wherein the flexible composite spacer members 506 are positioned between the two or more layers (114) to maintain a fixed separation in a deployable configuration and are capable of collapsing and returning to their original shape and size as needed.
3. The reflector array antenna system (100) as claimed in claim 1, wherein a hold down and release mechanism 108 is configured to secure the deployable reflector array system (100) in a stowed configuration.

4. The reflector array antenna system (100) as claimed in claim 3, comprises an electromechanically controlled release mechanism configured to release the hold down and release mechanism 108, enabling the deployment of the reflector array 114 when desired, upon satellite (102) reaching the intended orbit of the satellite (102), or when the spacecraft attains a specific spatial location, wherein:
the reflector array antenna system (100) is configured to deploy in one or more directions; and
the deployed angle of the reflector array antenna is 180°.

5. The reflector array antenna system (100) as claimed in claim 1, wherein the deployable mechanism is further configured to Z-fold along the width to minimize the stowed configuration.

6. The reflector array antenna system (100) as claimed in claim 1, wherein the antenna further comprises a combination of a reflector array and a solar cell arrays 902, with the solar cells arrays 902 positioned on one side of the bottom facesheet (504 or 804), and a continuous conductive layer that is co-cured/adhered/co-cured/printed to the bottom facesheet (504 or 804) on another side; and the antenna RF reflective patches 508 on another adjacent layer/top facesheet (502 or 802).

7. The reflector array antenna system (100) as claimed in claim 1, wherein one or more reflector arrays are accommodated to face the same direction or one or more reflector arrays with a particular orientation.

8. The reflector array antenna system (100) as claimed in claim 1, wherein the reflector array antenna is configured for dual antenna setup.

9. The reflector array antenna system (100) as claimed in claim 8, the dual antenna configuration further comprises one antenna on the one or more layers (114) serving the earth-facing side, and a second antenna mounted on the opposite side of the one or more layers (114), serving the space-facing side with the satellites (102) in higher orbits enabling inter-satellite link.

10. The reflector array antenna system (100) as claimed in claim 1, further comprises a monitoring device configured to indicate whether the reflector array is in any of the stowed or deployed configurations, with the ability to communicate the information to any or a combination of the satellite, spacecraft, or via telemetry.