Tactical high-power microwave antenna base

Abstract

The antenna system comprises a reflector subsystem, a rotatable support structure, and a support member. The reflector subsystem receives an input beam, reflects the input beam to generate an output beam, which is steered toward the target in the elevation direction by an elevation reflector and in the azimuth direction by an azimuth reflector. The rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector and configured to rotate them simultaneously. The support member comprises a longitudinal portion coupled to the rotatable support structure and an offset portion coupled to the elevation reflector, the offset portion configured to offset the elevation reflector from the longitudinal portion. The offset portion is configured to allow clearance of the elevation reflector during beam steering of the output beam toward the end of the elevation reflector's range of motion.

Description

[Technical Field]

[0001] Claim of Priority This patent application claims the benefit of priority from U.S. Patent Application No. 18 / 357,422, filed on July 24, 2023, which is incorporated herein by reference in its entirety.

[0002] Embodiments of the present disclosure generally relate to devices, systems, and methods for transmitting and receiving electromagnetic waves at microwave frequencies. More specifically, the present disclosure describes embodiments relating to devices, systems, and methods for implementing a high-power microwave antenna system having a shaped reflector optics and a mechanism optimized to provide improved stowage and transportability. [Background Art]

[0003] For some applications, it is desirable for high-power radio frequency (RF) transmitters operating in the microwave frequency band to provide high-power microwave (HPM) signals. For example, in HPM systems based on a high-power RF source, a waveguide is used to extract electromagnetic radiation from the RF source. At least some HPM systems are RF systems that can include the generation of high-peak power bursts of narrowband (coherent) electromagnetic radiation configured to spread across a frequency range of approximately 1 GHz to 100 GHz. Further versions of HPMs deal with ultra-broadband electromagnetic radiation, where the device's output frequency can span many frequency decades from the 10 MHz to the 10 GHz range. One application area that is increasing interest in HPM technology is the military, where there is interest in the development of non-lethal directed energy weapon (DEW) systems for electronic attack and / or electronic defense, and these systems use HPM technology to generate beams of energy for attack and / or defense. Directed energy weapons (DEWs) are electromagnetic systems capable of inflicting physical damage by converting chemical or electrical energy into radiant energy and focusing it on a target, thereby reducing, neutralizing, disabling, or destroying the capabilities of an enemy. Exemplary DEW systems include long-range weapons that, instead of using solid projectiles, damage or disable targets with highly focused energy, the energy of which can originate from sources that may include lasers, microwaves, particle beams, chemical reactions, and / or sonic beams. Depending on the weapon's power and intended use, DEWs can be used for both destructive and non-destructive purposes.

[0004] At least some DEW systems are attempting to implement HPM (High-Power Mechanism) technology using a peak-power narrowband source with a peak output power of around 1 GW at a frequency of around 1 GHz with the longest possible pulse duration. DEW systems (which may include not only HPMs but also high-energy lasers (HELs)) are being considered for various military applications on various platforms, such as space, air, and land systems. Possible applications of DEW technology include, but are not limited to, weapons targeting people, missiles, vehicles, and optical devices, which use high-energy beams (e.g., microwaves, lasers, or other high-energy sources) to damage or attack targets. [Overview of the project]

[0005] Below is a simplified overview to provide a basic understanding of one or more aspects of the embodiments described herein. This overview is not a comprehensive overview of all possible embodiments, nor is it intended to identify or limit the scope of any key or essential elements of an embodiment. Rather, the main purpose of this overview is to present some of the concepts of the embodiments described herein in a simplified form, serving as an introduction to the more detailed descriptions that will follow.

[0006] Figure 1 is a block diagram illustrating an exemplary prior art HPM system 100 that can be used as part of a DEW system. Pulsed power 102 is used to supply energy to a high-power microwave source 104. The pulsed power 102 includes a power supply 116 and a pulse generator 118, and in one embodiment, the pulsed power 102 is configured to supply an electrical pulse of about 1 megavolt with a pulse duration of less than 1 μs. The high-power microwave source 104 is implemented using either an impulse source 106 (e.g., a charging antenna, transmission line, tuning circuit, ultra-wideband source, etc.) or a linear beam source 108 (e.g., a magnetron, traveling wave tube (TWT), klystron, cross-field amplifier (CFA), gyrotron, etc.). One or more microwave components 110 (e.g., horn, feed, etc.) are used to convert the microwave radiation into a signal that can be coupled to the antenna 112.

[0007] Antenna 112 is advantageously a high-gain directional antenna system and, as understood, is configured to focus and concentrate microwave energy into a beam 113 of a desired size and radiation pattern in a desired direction. In lower frequency systems, the exemplary beamwidth of beam 113 is approximately 7°. For example, a narrowband HPM is configured to radiate all microwave energy within a few percent of the center frequency, which can be advantageous for certain types of targets, especially when the characteristics of the target (e.g., material and RF absorption) are known. In contrast, an ultra-wideband HPM is configured to radiate energy over a range of several hundred MHz to several GHz, which can be more advantageous for wider ranges of targets with less information available about them, but the radiated power is lower compared to a narrowband HPM, which can result in shorter ranges.

[0008] Figure 2 shows an exemplary prior art tactical HPM system, in this example being Raytheon's Phaser HPM System 200, which is configured to be mounted on a wheeled shelter 202. The system's antenna includes two beam steering reflectors, an elevation reflector 204 and an azimuth reflector 206, which are coupled to a prior art turret 210 that can rotate the elevation reflector 204 and the azimuth reflector. The elevation reflector 204 is coupled to a support arm 208 that supports the elevation reflector 204 during rotation. Inside the wheeled shelter 202 (also known as the transporter), there are basic HPM system components (for example, those shown in Figure 1) that provide the signals radiated by the Phaser System's antenna, although these are not visible in Figure 2.

[0009] DEW systems, particularly HPM DEW systems, can offer many advantages. For example, because radiation is invisible and silent, they can provide a quiet and invisible means of stopping and / or destroying targets. DEW weapons do not emit harmful chemicals or particles, making them safer to use in certain environments. Some types of DEW weapons (e.g., lasers and HPMs) operate at the speed of light, allowing them to operate faster than some other types of weapons. Atmospheric compensation is usually not a problem at microwave RF frequencies, so HPM weapons may be less affected by atmospheric or environmental concerns, and therefore, target tracking does not need to be precise enough to provide atmospheric compensation, accurate focusing, and precise engagement.

[0010] Furthermore, DEW systems such as HPM systems can offer advantages in magazine depth and magazine cost compared to conventional kinetic weapons. While kinetic weapons can have a cost per round that can reach millions of dollars per round, many HPM systems are implemented to have a significantly lower cost per round than kinetic weapons. Moreover, as is understood, kinetic weapons have a fixed magazine size and must be physically reloaded. In contrast, HPM-type DEW systems can have virtually unlimited magazines in a physical sense, which is more advantageous in tactical situations. In addition, unlike kinetic weapons, HPM systems can operate in a less lethal manner, so HPM systems can potentially neutralize certain types of targets (e.g., aircraft, vehicles) without directly harming the internal occupants.

[0011] HPM weapons may offer superior potential compared to other types of DEW systems, such as laser DEW systems, in countering certain types of operational challenges, such as drone swarms, or other situations involving engagement with multiple targets. A further advantage is that building and maintaining DEW systems may be less expensive than conventional weapons. In addition, some DEW systems may operate more easily in crowded environments, such as densely populated urban environments, where the safe and effective use of conventional (e.g., dynamic, explosive, chemical) weapon systems may be more difficult.

[0012] However, HPM DEW systems can also have challenges. For example, some DEW systems are implemented using HPM antennas composed of multiple reflectors (e.g., the conventional HPM DEW system in Figure 2). To maximize the antenna gain and efficiency (and thus increase the range and / or power of the HPM DEW system), the reflectors may need to be larger, precisely shaped, and spaced apart, which can make HPM transport and / or setup difficult and time-consuming. For example, some existing HPM weapon systems may have large reflectors that need to be disassembled for transport, requiring reassembly and complex adjustments in the field, which can take days or even weeks, making them undesirable as tactical weapon systems. Furthermore, some existing HPM systems may be inefficient (with a lot of spillover radiation off-target) and may only be able to operate at a single frequency, rather than having the flexibility to operate at a single frequency. However, operating at multiple frequencies may require increasing the size and complexity of the HPM system, as is understood. Furthermore, while precise beam aiming is crucial in HPM systems, it is extremely difficult, especially in high-frequency systems such as at least some embodiments described herein, where the beam width of beam 113 (Figure 1) may be less than 1°. However, handling the large reflectors required for precise aiming can be more difficult in HPM-type DEW systems than in other types of DEWs (e.g., rotating relatively small laser signals).

[0013] Furthermore, at least some existing HPM weapon systems have not been able to utilize all optical techniques to improve aperture efficiency. As is known in the art, a reflector antenna is an antenna designed to reflect incident electromagnetic waves originating from another source and is designed to operate at high microwave frequencies. One type of reflector antenna used in a prior art system like the one in Figure 2 is a dual reflector antenna, which consists of two steering reflectors, both of which are planar (i.e., non-focused) in the example in Figure 2. The system in Figure 2 has an axisymmetric Cassegrain reflector assembly in a wheeled shelter 202 (transporter) that focuses a statically vertically upward-directed beam. In this exemplary system in Figure 2, the secondary reflector of the Cassegrain reflector assembly is not hyperbolic, and the primary reflector of the Cassegrain reflector is not parabolic.

[0014] A pair of reflectors is sometimes used as part of a shaped reflector design. However, when using a shaped reflector design for power density redistribution to achieve high aperture efficiency, the aspect between the primary and secondary reflectors forming the shaped reflector pair must be fixed, which is preferable for optimal performance. Rotating either reflector in a shaped reflector pair can catastrophically disrupt the phase delay relationship between the reflectors, thus posing challenges to beam steering. Furthermore, when actually deployed and used, setting up and dismantling shaped reflectors can be extremely time-consuming (e.g., days to weeks) to ensure that the appropriate fixed aspect is maintained, which is impractical in at least some tactical environments. These limitations, and potentially other stringent limitations, prevent the use of shaped reflectors in beam steering reflectors that need to be easily stowed for ground and air transport.

[0015] It is advantageous to develop and provide HPM weapon systems that include specific optics, mechanisms, and designs that maximize antenna gain and efficiency, while enabling easy transport and storage (preferably automated storage), and reducing setup and deployment times. It is advantageous to develop and provide HPM weapon systems that can leverage the advantages of shaped reflector optics while enabling assembly, setup, and transport within the size and time constraints of challenging applications such as military environments. It is advantageous to provide high-power microwave weapon systems that can be configured for multiple frequencies, since known configurations are for single-frequency systems that do not require the increased size and complexity that may be necessary for multi-frequency systems.

[0016] At least some embodiments of this specification can help address at least some of these challenges.

[0017] In one embodiment, the antenna system comprises a reflector subsystem, a rotatable support structure, a first support member, and a second support member. The reflector subsystem is configured to receive an input beam and reflect the input beam to generate an output beam directed toward at least one target, and the reflector subsystem comprises an elevation reflector having a first range of motion and configured to steer the input beam in the elevation direction, and an azimuth reflector having a second range of motion and configured to steer the input beam in the azimuth direction, so that the output beam is steered toward the target in the elevation and azimuth directions. The rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector and is configured to rotate the elevation reflector and the azimuth reflector simultaneously. The first support member comprises a longitudinal portion coupled to the rotatable support structure and an offset portion coupled to the elevation reflector, the offset portion being configured to offset the elevation reflector from the longitudinal portion. The second support member has a first end coupled to the rotatable support structure and a second end coupled to the azimuth reflector. During beam steering of the output beam, the offset portion is configured to allow clearance of the elevation reflector during beam steering of the output beam to the end of the first movable range of the elevation reflector.

[0018] In some embodiments, the input beam includes an axisymmetric beam having a uniform power density distribution. In some embodiments, the first movable range includes an angular range of approximately -5° to +95°. In some embodiments, the elevation reflector is configured to have an extended position and a retracted position, in the retracted position, the offset portion of the first support member is configured to position the elevation reflector steering drive next to the longitudinal portion of the first support member, and in the retracted position, the arrangement of the elevation reflector is configured to minimize the height of the elevation reflector when it is retracted.

[0019] In some embodiments, the antenna system further comprises a linear actuator configured to raise the elevation reflector to an extended position and lower the elevation reflector to a retracted position. In further embodiments, the antenna system further comprises an elevation steering head tilt actuator operably coupled to the elevation reflector and a rotatable support structure, the elevation steering head tilt actuator configured to cooperate with the linear actuator to produce a movement of the elevation reflector configured to retract the elevation reflector to a horizontal position.

[0020] In some embodiments, the antenna system further comprises an elevation beam steering drive operably coupled to an elevation reflector and a rotatable support structure, the elevation beam steering drive being configured to rotate the elevation reflector about an elevation rotation axis when the elevation reflector is in the deployed position.

[0021] In some embodiments, the antenna system further comprises a single-degree-of-freedom tilted rotary drive operably coupled to a second support member and configured to rotate the second support member along a first end of the second support member to position an azimuth reflector coupled to the second end in a retracted position and an extended position, wherein the retracted position of the azimuth reflector is configured to minimize the height of the azimuth reflector when it is retracted. In further embodiments, the antenna system further comprises an elevation beam steering drive operably coupled to an elevation reflector and a rotatable support structure, wherein the elevation beam steering drive is configured to rotate the elevation reflector about an elevation rotation axis when the elevation reflector is in the extended position, and the rotatable support structure is configured to rotate the azimuth reflector about an azimuth rotation axis when the azimuth reflector is in the extended position, and the elevation beam steering drive and the rotatable support structure are configured to cooperate so that the antenna system can direct the output beam to any point within a full hemispherical skydome when both the elevation reflector and the azimuth reflector are extended and an input beam is received. In a further embodiment, the input beam includes a high-power microwave signal, and the elevation reflector is configured to have a first deployed position and a first retracted position, wherein in the first retracted position of the elevation reflector, the offset portion of the first support member is configured to position the elevation reflector next to the longitudinal portion of the first support member, and in the first retracted position of the elevation reflector, the arrangement of the elevation reflector is configured to minimize the height of the elevation reflector when it is retracted.

[0022] In some embodiments, the input beam includes a high-power microwave (HPM) signal, and the output beam, which is steered toward a target, is configured to direct HPM energy toward at least one target as part of a directed energy weapon (DEW) system. In some embodiments, the antenna system operably communicates with a control subsystem, which is configured to receive information about at least one target and, based on the information about at least one target, is configured to automatically control at least one of the following: the characteristics of the input beam, the position of a rotatable support structure, the position of an elevation reflector, and the position of an azimuth reflector.

[0023] In some embodiments, the input beam includes a high-power microwave (HPM) input beam, the antenna system is sized to operate with the HPM input beam, a rotatable support structure is operably coupled to a movable structure, the movable structure having a recessed region sized to receive the elevation reflector and the first support member when the elevation reflector and the first support member are in a first stowed position. In further embodiments, the antenna system has a first height when the elevation reflector is in a first stowed position and the azimuth reflector is in a second stowed position, the movable structure has a second height, and the combination of the first and second heights corresponds to an overall height sized to fit within a C-17 aircraft. In further embodiments, the movable structure includes a beam generation subsystem configured to generate an HPM input beam for the antenna system.

[0024] In another embodiment, a method is provided for directing a high-power microwave (HPM) beam toward a target. A reflector subsystem is configured to receive a high-power microwave (HPM) input beam and reflect the HPM input beam to generate an HPM output beam toward at least one target, the reflector subsystem comprising an elevation reflector having a first range of motion and configured to steer the input beam in the elevation direction, and an azimuth reflector having a second range of motion and configured to steer the input beam in the azimuth direction, so that the HPM output beam is steered toward the target in the elevation and azimuth directions. A rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector. The rotatable support structure is configured to rotate the elevation reflector and the azimuth reflector simultaneously. The elevation reflector is coupled to the rotatable support structure via a first support member comprising a longitudinal portion coupled to the rotatable support structure and an offset portion coupled to the elevation reflector, the offset portion configured to offset the elevation reflector from the longitudinal portion. The first end of the second support member is coupled to a rotatable support structure, and the second end of the second support member is coupled to an azimuth reflector. The HPM output beam is steered toward the target, and during beam steering, the offset portion is configured to allow clearance of the elevation reflector during beam steering of the HPM output beam to the end of the first movable range of the elevation reflector.

[0025] In some embodiments, the method further includes receiving information about at least one target and automatically controlling at least one of the following based on the information about at least one target: the characteristics of the input beam, the position of the rotatable support structure, the position of the elevation reflector, and the position of the azimuth reflector.

[0026] In another embodiment, a method for housing a reflector in a high-power microwave (HPM) antenna system is provided. The reflector subsystem is configured to receive a high-power microwave (HPM) input beam and reflect the HPM input beam to generate an HPM output beam directed toward at least one target, and the reflector subsystem comprises an elevation reflector having a first range of motion and configured to steer the input beam in the elevation direction, and an azimuth reflector having a second range of motion and configured to steer the input beam in the azimuth direction, so that the HPM output beam is steered toward the target in the elevation and azimuth directions. A rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector. The rotatable support structure is configured to rotate the elevation reflector and the azimuth reflector simultaneously. The elevation reflector is coupled to the rotatable support structure via a first support member comprising a longitudinal portion coupled to the rotatable support structure and an offset portion coupled to the elevation reflector, the offset portion configured to offset the elevation reflector from the longitudinal portion. The first end of the second support member is connected to a rotatable support structure, and the second end of the second support member is connected to an azimuth reflector. The elevation reflector is configured to have a first deployed position and a first retracted position, in the first retracted position, the offset portion of the first support member is configured to position the elevation reflector next to the longitudinal portion of the first support member, and in the first retracted position, the arrangement of the elevation reflector is configured to minimize the height of the elevation reflector when it is retracted.

[0027] In some embodiments, the method further comprises: operably coupling a single-degree-of-freedom tilted rotary drive to the second support member, wherein the single-degree-of-freedom tilted rotary drive is configured to rotate the second support member along the first end of the second support member to dispose the azimuth reflector coupled to the second end in a second stowed position and a second deployed position, and the second stowed position of the azimuth reflector is configured to minimize the stowed height of the azimuth reflector. In some embodiments, the method further comprises operably coupling a rotatable support structure to a movable structure, wherein the movable structure is configured to have a recessed area sized to receive the elevation reflector and the first support member when the elevation reflector and the first support member are in the first stowed position.

[0028] It should be understood that individual elements of the different embodiments described herein may be combined to form other embodiments not specifically set forth above. Various elements described in the context of a single embodiment may be provided separately or in any suitable subcombination. It should also be understood that other embodiments not specifically described herein are also within the scope of the claims encompassed herein.

[0029] Further details regarding these and other embodiments are more fully described herein.

[0030] The advantages and aspects of the described embodiments, as well as the embodiments themselves, will be more fully understood in conjunction with the following detailed description and accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] [Figure 1] It is a simplified block diagram of a conventional high-power microwave (HPM) system. [Figure 2] It is an illustrative view of a prior art tactical HPM system. [Figure 3]This is a diagram of a first embodiment of a tactical HPM system including a support base mechanism, according to one embodiment. [Figure 4] This is a side view of one embodiment of the tactical HPM system assembly shown in Figure 3, according to one embodiment. [Figure 5] This is a perspective view of another embodiment of the assembly shown in Figure 4, according to one embodiment. [Figure 6] These are side views of the assembly shown in Figures 3 and 4 in the storage position, according to one embodiment. [Figure 7] This is a simplified functional block diagram of an HPM system having a molded reflector redistribution stage according to one embodiment. [Figure 8] This is a simplified functional block diagram of the tactical HPM system shown in Figure 3, according to one embodiment. [Figure 9] Figure 3 shows a simplified side cross-sectional view of a tactical HPM system, illustrating a simplified block diagram of a portion of the electronic assembly within a trailer enclosure, including an internal antenna system and an external antenna system, according to one embodiment, and showing an exemplary reflection pattern of the HPM beam. [Figure 10] This is a simplified top view of a portion of the electronic assembly inside the shelter shown in Figure 9, according to one embodiment. [Figure 11] Figure 3 shows an exemplary cross-sectional view of the tactical HPM system in a stowed configuration, coupled to a transporter vehicle and stored in a C-17 freighter aircraft. [Figure 12A] Figure 3 is an illustrative diagram of a tactical HPM system in which both reflectors are in the stowed position, according to one embodiment. [Figure 12B] This is an illustrative diagram of the tactical HPM system in a first position according to one embodiment. [Figure 12C] This is an illustrative diagram of the tactical HPM system in a second position according to one embodiment. [Figure 12D] This is an illustrative diagram of the tactical HPM system in a third position according to one embodiment. [Figure 12E]This is an illustrative diagram of the tactical HPM system in a fourth position according to one embodiment. [Figure 12F] This is an illustrative diagram of the tactical HPM system in a fifth position according to one embodiment. [Figure 12G] This is an illustrative diagram of the tactical HPM system in the sixth position according to one embodiment. [Figure 12H] This is an illustrative diagram of the tactical HPM system in the seventh position according to one embodiment. [Figure 12I] This is an illustrative diagram of the tactical HPM system in the eighth position according to one embodiment. [Figure 12J] This is an illustrative diagram of the tactical HPM system in the ninth position according to one embodiment. [Figure 12K] This is an illustrative diagram of the tactical HPM system in the tenth position according to one embodiment. [Figure 12L] This is an illustrative diagram of the tactical HPM system in the 11th position according to one embodiment. [Figure 13A] This is an illustrative diagram of the tactical HPM system in a first deployment position according to one embodiment. [Figure 13B] This is an illustrative diagram of the tactical HPM system in a second deployment position according to one embodiment. [Figure 13C] This is an illustrative diagram of the tactical HPM system in a third deployment position according to one embodiment. [Figure 13D] This is an illustrative diagram of the tactical HPM system in a fourth deployment position according to one embodiment. [Figure 13E] This is an illustrative diagram of the tactical HPM system of Figure 3 in a fifth deployment position according to one embodiment. [Figure 13F] This is an illustrative diagram of the tactical HPM system of Figure 3 in a sixth deployment position according to one embodiment. [Figure 13G] This is an illustrative diagram of the tactical HPM system of Figure 3 in a seventh deployment position according to one embodiment. [Figure 13H] This is an illustrative diagram of the tactical HPM system of Figure 3 in an eighth deployment position according to one embodiment. [Figure 14A] This is an illustrative diagram of the tactical HPM system of Figure 3 in a ninth deployment position according to one embodiment. [Figure 14B] This is an illustrative diagram of the tactical HPM system of Figure 3 in a tenth deployment position according to one embodiment. [Figure 14C] This is an illustrative diagram of the tactical HPM system in the 11th deployment position according to one embodiment. [Figure 14D] This is an illustrative diagram of the tactical HPM system in a twelfth deployment position according to one embodiment. [Figure 14E] This is an illustrative diagram of the tactical HPM system in a 13th deployment position according to one embodiment. [Figure 14F] This is an illustrative diagram of the tactical HPM system of Figure 3 in a 14th deployment position according to one embodiment. [Figure 14G] This is an illustrative diagram of the tactical HPM system of Figure 3 in a 15th deployment position according to one embodiment. [Figure 14H] This is an illustrative diagram of the tactical HPM system of Figure 3 in a 16th deployment position according to one embodiment. [Figure 14I] This is an illustrative diagram of the tactical HPM system of Figure 3 in a 17th deployment position according to one embodiment. [Figure 15] A is a side view of the elevation / polar reflector motion envelope of the elevation reflector of the tactical HPM system in Figure 3, according to one embodiment. B is a first rear view of the elevation / polar reflector motion envelope of the elevation / polar reflector of the tactical HPM system in Figure 3, according to one embodiment. C is an auxiliary diagram of the elevation / polar reflector motion envelope of the elevation / polar reflector of the tactical HPM system in Figure 3, according to one embodiment. [Figure 16] This is an illustrative diagram of the first motion envelope of the elevation / polar angle reflector of the tactical HPM system shown in Figure 3, according to one embodiment. [Figure 17]This is an illustrative diagram of the second motion envelope of the elevation / polar angle reflector of the tactical HPM system shown in Figure 3, according to one embodiment. [Figure 18] Figure 3 is an illustrative diagram of a tactical HPM system, illustrating the path of the RF beam from the elevation / pole angle reflector at the terminal depression position according to one embodiment. [Figure 19] Figure 3 is a first diagram showing the first RF beam envelope of the polar angle / elevation reflector of the tactical HPM system, in one embodiment where the polar angle / elevation reflector is configured at a depression angle of 0 degrees. [Figure 20] Figure 3 is a second diagram showing the second RF beam envelope of the polar angle / elevation reflector of the tactical HPM system, in one embodiment where the polar angle / elevation reflector is configured to have a beam elevation angle of 95 degrees from the horizon. [Figure 21] Figure 3 is a flowchart of the processes available in the tactical HPM system. [Figure 22] This is a block diagram of an exemplary computer system usable in at least some of the systems, apparatus, methods, and / or operations shown in Figures 3 to 25, according to one embodiment. [Modes for carrying out the invention]

[0032] The drawings are not to scale and instead emphasize that they illustrate the principles and features of embodiments of the present disclosure. Furthermore, in the drawings, similar reference numerals indicate similar elements.

[0033] Before describing the details of specific systems, devices, and methods, it should be noted that the concepts disclosed herein include, but are not limited to, new structural combinations of components and circuits, and are not necessarily limited to their specific detailed configurations. Accordingly, the structure, methods, functions, control, and arrangement of components and circuits are shown in the drawings by readily understandable simplified block diagrams and schematic diagrams, so as not to obscure the disclosure by structural details that would be readily apparent to those skilled in the art who benefit from the description herein.

[0034] Furthermore, the following detailed description is provided, in at least some examples, using a specific context of a target detection system (e.g., a radar system) configured to detect, track, monitor and / or identify a target, where the target may include (but is not limited to) aircraft (both unmanned and manned), unmanned aerial vehicles, unmanned autonomous vehicles, robots, ships, spacecraft, automatic vehicles, and celestial bodies, as well as birds, insects, and rain. At least some embodiments of this specification can be used in any system relating to any radar application, including but not limited to military radar, air traffic control radar, and weather observation radar. Those skilled in the art will understand that the embodiments described herein are also applicable to many types of systems, including but not limited to all kinds of radio communications, satellite systems, optical systems, any high-power microwave systems requiring ground and / or air transport, high-gain satellite communications, and any tactical or defensive applications where an unlimited magazine size is advantageous.

[0035] Furthermore, note that the following description and drawings illustrate various connections between elements. These connections may generally be direct or indirect unless otherwise specified, and this specification is not intended to limit them in this respect. In this disclosure, connections between entities may refer to direct or indirect connections. Understand that corresponding reference numerals indicate similar or corresponding parts and features throughout the drawings. As used herein, the terms module, unit, and / or component may be formed as a processing circuit that may include application-specific integrated circuit (ASIC), electronic circuit, processor (shared, dedicated, or group), and memory, combinational logic circuit, and / or other suitable components that run one or more software or firmware programs and provide the functions described.

[0036] Furthermore, the use of the term “signal” in relation to this disclosure is not limited to analog and / or digital signals, but is rather intended to also refer to (1) a mathematical description of any measurable phenomenon in natural or artificial systems, and (2) a mathematically described function of one or more variables that depend on one or more parameters. Examples of types of signals included in the embodiments described herein include, but are not limited to, light intensity, voltage, pressure, electromagnetic radiation (including radio waves), magnetic field strength, and electric field strength.

[0037] Embodiments of this disclosure include configurations of HPM systems that enable easy transport and storage, while reducing setup and deployment times, and include specific optical systems, mechanisms, and designs that maximize antenna gain and efficiency. The shaped reflector optical systems in at least some embodiments of this specification are configured to maximize antenna efficiency while minimizing energy spillover. Furthermore, embodiments of this specification help minimize the storage volume of HPM antennas, enabling transport on aircraft such as military cargo planes.

[0038] Figure 3 is a diagram of a first embodiment of a tactical HPM system 600, including a support base mechanism, according to one embodiment. The tactical HPM system 600 includes a trailer enclosure 602 (hereinafter, "trailer enclosure 602") which integrates a power supply and an RF source, and which houses internal antenna system components (further described herein in relation to Figures 7 to 9). The trailer enclosure 602 is merely illustrative, and in at least some embodiments, any movable enclosure can be used. In the deployed position shown in Figure 3, the trailer enclosure 602 is supported by both wheels 311 and a number of retractable outriggers 613 (which function as support legs). Furthermore, the trailer enclosure 602 is provided with an inclined edge 618, which is constructed and configured to provide an area for housing the elevation / pole angle reflector 604, the pole angle reflector deployment mechanism, and the elevation / pole angle support arm 608 when stowed, as shown in Figure 6, and which will be further described herein. In certain embodiments, the sloping edge 618 of the trailer enclosure 602 is part of a recessed area 603 (best visible in Figure 12G) on the upper / mounting side of the trailer enclosure 602, which provides space for the elevation / polar reflector 604 and its elevation / polar support arm 608 to "nest" when the elevation / polar reflector 604 is housed therein. In certain embodiments, the recessed area 603 does not need to provide space for the azimuth reflector 606 because, as shown in Figures 6 and 12A-12F, the azimuth support arm 614 of the azimuth reflector 606 can be rotated approximately 180 degrees (for example, pointed "down" as shown in Figure 6) so that the azimuth reflector 606 is as close as possible to the trailer enclosure 602.

[0039] The external antenna portion of the system visible in Figure 3 includes an elevation / polar reflector 604 (also referred to herein as an elevation reflector or polar reflector) and an azimuth reflector 606, each coupled to an azimuth beam steering turret mechanism 610, which is coupled to a rotatable support structure such as an azimuth turret 612, which itself is operably coupled to a trailer enclosure 602. The elevation / polar reflector 604 is coupled to a polar reflector deployment mechanism and a corresponding support member, such as an elevation / polar support arm 608, which together raises the elevation / polar reflector 604 to an operational position, a configuration further described herein in reference to Figure 4 and in reference to Figures 12A to 13H. In certain embodiments, the polar angle reflector deployment mechanism and the elevation / polar angle support arm 608 also include an elevation beam steering drive device 616.

[0040] The azimuth reflector 606 is operably coupled to the azimuth reflector deployment mechanism and the azimuth support arm 614, which will also be described further in reference to Figure 4 of this specification. In certain embodiments, the azimuth reflector 606 is coupled to each support member, such as the azimuth support arm 614, which is further coupled to a rotatable support structure (e.g., an azimuth turret 612). In certain embodiments, the elevation / polar reflector deployment mechanism and the elevation / polar support arm 608, as well as the azimuth reflector deployment mechanism and the azimuth support arm 614, are operably coupled to the azimuth beam steering turret mechanism 610 and / or the azimuth turret 612, respectively.

[0041] In certain embodiments, the azimuth turret 612 is operably coupled to an elevation / polar mechanical control subsystem 742 (further described herein in relation to Figure 8) and functions as its rotatable support structure, the elevation / polar mechanical control subsystem 742 includes at least an elevation / polar support arm 608, which includes a longitudinal portion 623 and an offset portion 621, and is operably coupled to the elevation / polar reflector 604, so that the azimuth turret 612 also functions as at least an indirect rotatable support structure for the elevation / polar reflector 604. As further illustrated and described in relation to Figure 8, the elevation / polar mechanical control subsystem 742 also includes, in certain embodiments, a drive and several actuators configured to control the movement and / or rotation of the elevation / polar reflector 604 in more detail.

[0042] Similarly, the azimuth turret 612 is operably coupled to an azimuth mechanical control subsystem 744 (further described herein in relation to Figure 8) and functions as its rotatable support structure, the azimuth mechanical control subsystem 744 includes at least an azimuth support member (e.g., an azimuth support arm 614) operably coupled to both the rotatable support structure and the azimuth reflector 606, and the azimuth turret 612 also functions as at least an indirect rotatable support structure for the azimuth reflector 606. As further illustrated and described in relation to Figure 8, the azimuth mechanical control subsystem 744 also includes, in certain embodiments, a drive and actuator configured to control the movement and / or rotation of the azimuth reflector 606 in more detail.

[0043] In certain embodiments, the azimuth turret 612 is also configured to maintain a desired orientation between the azimuth reflector 606 and the elevation / pole reflector 604 during at least one of operation and retraction. In certain embodiments, the azimuth turret 612 works in cooperation with the operational functions of one or both of the elevation / pole mechanical control subsystems 742 and azimuth mechanical control subsystems 744 to help maintain a desired orientation between the elevation / pole reflector 604 and the azimuth reflector 606. In certain embodiments, the support structure of the external antenna system 704 (i.e., the shaped reflector redistribution stage 704, also referred herein to as the shaped reflector redistribution subsystem 704 and / or reflector subsystem 704) corresponds to a combination of the azimuth turret 612, the pole reflector deployment mechanism and elevation / pole support arm 608, the azimuth reflector deployment mechanism and azimuth support arm 614, and the azimuth beam steering turret mechanism 610.

[0044] As further described herein, a mechanical beam steering drive (further described and illustrated herein in relation to Figures 4, 7, and 8) is configured to simultaneously rotate the azimuth beam steering turret mechanism 610, the azimuth reflector 606, and the elevation / pole reflector 604, thereby achieving mechanical beam pointing to any point within a complete hemispherical skydome (for example, an antenna system 704 can direct its output beam 727 to any point within a complete hemispherical skydome). The reflector support arm shapes of the pole reflector deployment mechanism and elevation / pole support arm 608 and the azimuth reflector deployment mechanism and azimuth support arm 614 are configured to provide clearance for the motion envelope during tracking of a full range of targets while maintaining the required orientation between the azimuth reflector 606 and the elevation / pole reflector 604. As further described herein, the arm shape and configuration of the elevation / pole angle reflector 604 includes an elevation / pole angle support arm 608 having an offset portion 621, the offset portion 621 also helps to minimize the height of the system 300 when retracted. In at least some embodiments, as further described herein, full elevation beam steering coverage (-5° to +95°) using a large 16-foot x 10-foot elevation / pole angle main reflector 604 is achieved by the unique offset portion 621 of the support arm 608 and the deployment mechanism described herein (for example, as illustrated and described herein in relation to Figures 15A, B, C and 18).

[0045] In certain embodiments, the overall structure of the tactical HPM system 600 shown in Figure 3 constitutes a tactical HPM antenna system including a tactical HPM antenna base (the base itself includes at least support structures, mechanisms, and drive devices to support the antenna components, such as a trailer enclosure 602, retractable outriggers 613, an azimuth turret 612, all support arms (e.g., elevation / polar support arms 608 and azimuth support arms 614), and drive mechanisms). As can be seen from Figure 3, and further from Figures 6, 11, and 12A (Figure 12A shows the assembly of Figure 3 in the stowed position), the shape of the base is optimized to minimize the height of the antenna when stowed and to maximize structural rigidity. Maximizing structural rigidity is important and advantageous as it allows the tactical HPM system 600 in Figure 3 to align the beam very quickly and accurately without vibration during target tracking operations, while also providing the stiffness necessary to maintain beam pointing accuracy in environmental conditions such as wind.

[0046] Furthermore, in certain embodiments, the target height of the stowed antenna is less than 142 inches for unrestricted C-17 transport (further described herein in relation to Figure 11). In embodiments where the stowed antenna height exceeds 142 inches, components (e.g., elevation / polar reflector 604) must be removed for air transport on vehicles such as C-17 aircraft. Those skilled in the art will understand that the devices, systems, methods, and designs described herein are expandable and applicable to minimize the stowed height of many different types of antenna and / or reflector configurations, as well as many different types of systems.

[0047] As shown in Figure 3, and further in Figures 6, 11, 12A to 14I, 15B and C, and 18 to 20 (further described herein), in certain embodiments, the elevation / polar angle support arm 608 is configured to include a longitudinal portion 623 coupled to the azimuth turret 612 and an offset portion 621 coupled to both the longitudinal portion 623 and the elevation / polar angle reflector 604, the offset portion 621 being configured to offset the elevation / polar angle reflector 604 from the longitudinal portion 623 of the elevation / polar angle support arm 608, thereby ensuring clearance (e.g., rotational clearance) for the elevation / polar angle reflector 604 at the terminal viewing angle. The offset portion 621 (see in particular A, B, C in Figure 15 and Figure 18) also helps to reduce the height when retracted, because offsetting the offset portion 621 of the elevation / polar angle support arm 608 of the elevation / polar angle reflector 604 allows the elevation steering drive unit 616 and elevation steering head tilt actuator 617 to be positioned to the side of the rest of the elevation / polar angle support arm 608 (i.e., next to the longitudinal portion 623) when retracted, eliminating the need to retract the elevation / polar angle reflector 604 on top of the elevation / polar angle support arm 608, which would increase the height when retracted and is undesirable when minimizing the height when retracted is a priority. As will become clear from the description herein, the beam steering and deployment mechanism provided in the tactical HPM system 600 offers a unique combination of rapid (e.g., within minutes, not days) "fire and move" gun mount functionality and large, high-gain HPM antenna performance. Furthermore, as will be discussed herein, the shaped reflector optics of at least some embodiments herein achieve high efficiency over a given beam pointing elevation range while also controlling RF spillover. In certain embodiments, full elevation beam steering coverage (e.g., a given beam pointing angle range corresponding to -5° to +95°) using a large 16-foot x 10-foot polar-angle primary reflector is achieved by a unique offset support arm and deployment mechanism (further described herein).

[0048] Furthermore, the configuration shown in Figure 3, including the trailer enclosure 602, the azimuth beam steering turret mechanism 610, the azimuth turret 612, the polar reflector deployment mechanism including the elevation / polar support arm 608, and the azimuth reflector deployment mechanism including the azimuth support arm 614, works together to provide a broad structural base for the elevation / polar reflector 604 and / or the azimuth reflector 606, thereby maintaining rigidity in environmental conditions (e.g., wind) during beam steering operation (i.e., operation along the azimuth and elevation axes). As understood, in at least some embodiments, the trailer enclosure 602 does not move during the operation of the external antenna system 704.

[0049] Advantageously, the tactical HPM system 600 of Figure 3 can accommodate a very large antenna system inside an aircraft transport cargo plane (e.g., a C-17) by providing an HPM antenna pedestal configuration configured to minimize the stowed volume in certain embodiments. Briefly referring to Figure 6, Figure 6 is a side view 680 of the assemblies of Figures 3 and 4 in the stowed position according to one embodiment. Also, briefly referring to Figure 11, Figure 11 is an exemplary cross-sectional view 1100 of the tactical HPM system of Figure 3 in the stowed configuration, coupled to a transporter vehicle and stored in an exemplary C-17 cargo plane 1102. The internal height of the C-17 cargo plane 1102 is 148 inches, but a minimum clearance of 6 inches is required for safety, so the maximum stowed height that fits in the C-17 cargo plane is 142 inches. The unique and advantageous configurations of the elevation / polar reflectors 604 and azimuth reflectors 606, the reflectors and their housing configurations, such as the offset section 621, and the custom-shaped trailer enclosure 602 help ensure that the system 300 fits within the 142-inch limit of the C-17. This is further described herein.

[0050] Referring briefly to Figure 6, which is a side view 680 of the assembly of Figure 3 (and Figure 4) in the stowed position according to one embodiment. As shown in Figure 6, the elevation / polar reflector 604 utilizes the inclined edge 618 of the trailer enclosure 602 for storage, and the azimuth reflector deployment mechanism and azimuth support arm 614 are also configured to position the azimuth reflector 606 downward, so that in at least some embodiments, even in embodiments where the deployed height of the elevation / polar reflector 604 and / or the deployed height of the azimuth reflector 606 exceeds the 142-inch height limit, the stowed volume still meets the C17 transport height limit of 142 inches (11 feet 10 inches). For example, in some embodiments, the height of the elevation / polar reflectors when deployed is 22 feet 7 inches (271 inches), but the advantageous folding configuration of Figure 6 allows the elevation / polar reflectors 604 and azimuth reflectors 606 to be folded sufficiently to meet height restrictions while maintaining the required orientation (further described herein). It is also advantageous that the trailer enclosure 602 itself be designed to fit inside a freighter or other transport vehicle, together with the transport vehicle (for example, shown in Figure 11, which is well known in the art).

[0051] Minimizing the storage volume in this way is a key feature that, in certain embodiments, enables the tactical HPM system 600 of Figure 3 to function as a true tactical weapon system. As shown in Figure 6, in its stored configuration, the tactical HPM system 600 of Figure 3 efficiently reduces its size to support air, road, and sea transport by housing its large external reflectors (i.e., elevation / polar reflector 604 and azimuth reflector 606), along with their support and deployment mechanisms, within the design of the trailer enclosure 602.

[0052] Referring here to Figure 4, which is a side view of one embodiment of an assembly 650 of the tactical HPM system 600 of Figure 3, according to one embodiment. The side view of Figure 4 provides further details regarding the mechanism configured to move the elevation / polar reflector 604 and the azimuth reflector 606. As shown in Figure 4, the deployment mechanism cooperating to raise the elevation / polar reflector 604 to the working position includes a linear deployment actuator 642 that moves in the illustrated direction 609 and an elevation steering head tilt actuator 617 that rotates the elevation steering head (and elevation / polar reflector 604) in direction 605. In certain embodiments, the elevation steering of the beam is achieved by an elevation beam steering drive 616 that rotates perpendicular to the elevation steering head tilt actuator 617. The linear deployment actuator 642, in combination with the elevation steering head tilt actuator 617 (see Figure 14G), is operable to generate the necessary movement of the elevation / polar reflector 604 to achieve the retracted and deployed orientations at the ends of the range of motion of the elevation / polar reflector deployment support arm 608.

[0053] The elevation steering head tilt actuator 617 is not clearly visible in all figures, but is visible in selected figures such as Figures 14G, 14H, and 14I, and in certain embodiments is configured to provide a specific tilt of the elevation / polar reflector 604 for retraction, so that the elevation / polar reflector 604 is retracted to a horizontal position at the end of the movement. The elevation steering head tilt actuator 617 operates simultaneously with the linear deployment actuator 642 of the elevation support arm 608, and in certain embodiments, the elevation steering head tilt actuator 617 is used solely for retracting and deploying the elevation / polar reflector 604 and its elevation / polar support arm 608. Furthermore, the combination of linear and rotary action provides efficient stiffness characteristics combined with a relatively compact form factor. The deployment mechanism for lifting the azimuth reflector 606 includes a rotary deployment actuator 644, which is described further herein in relation to Figure 8.

[0054] The aforementioned mechanical beam steering drive system simultaneously rotates the azimuth beam steering turret mechanism 610, the azimuth turret 612, the azimuth reflector 606, and the elevation / polar reflector 604 to achieve mechanical beam pointing to any point within the perfectly hemispherical skydome. Refer to Figures 12A-12L, 13A-13F, and 14A-14I, which will be further described below, as these figures show the movement of the elevation / polar reflector 604 and the azimuth reflector 606 via the azimuth turret 612 and the azimuth beam steering turret mechanism 610.

[0055] For example, Figures 12A to 12L show the tactical system of Figure 3 in various operating positions, along with the elevation / polar reflector 604, azimuth reflector 606, azimuth turret 612, and azimuth beam steering turret mechanism 610 (Figure 12A shows the tactical system of Figure 3 in stowed position 1810 with both reflectors stowed, and is similar to Figure 3 and has been described above). Figure 12B is an exemplary figure 1812 of the tactical HPM system 600 of Figure 3 in a first position 1812 according to one embodiment, where the elevation / polar reflector 604 begins to rise and the azimuth reflector 606 begins to rotate for elevation. As can be understood, components including but not limited to the linear deployment actuator 642, the elevation / polar angle support arm 608, and the elevation steering head tilt actuator 617 may work together to begin raising the elevation / polar angle reflector 604 and / or rotating it to the desired orientation, and the rotational deployment actuator 644 may begin to act to begin rotating the azimuth reflector 606.

[0056] Figure 12C is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a second position 1820 according to one embodiment, where the elevation / polar reflector 604 is rising further and the azimuth reflector 606 is beginning to rise with rotation. The azimuth support arm 614 of the azimuth reflector 606 is acting in conjunction to begin raising the azimuth reflector 606. Figure 12D is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a third position 1828 according to one embodiment, where the elevation / polar reflector 604 is rising further and the azimuth reflector 606 is rising further with rotation. Figure 12E is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a fourth position 1830 according to one embodiment, where the elevation / polar reflector 604 is rising further and the azimuth reflector 606 is rotating and rising further.

[0057] Figure 12F is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a fifth position 1840 according to one embodiment, with the elevation / polar reflector 604 and azimuth reflector 606 both almost fully raised to their initial deployment positions. Figure 12G is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a sixth position 1845 according to one embodiment, with the elevation / polar reflector 604 fully raised and beginning to rotate along the elevation / polar axis (which will be further explained later), and the azimuth reflector 606 fully raised. Figure 12H is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a seventh position according to one embodiment, showing the azimuth beam steering turret mechanism 610 and azimuth turret 612 rotating along the azimuth rotation axis. Figure 12I is an illustrative diagram of the tactical HPM system 600 of Figure 3 at an eighth position 1852 according to one embodiment, showing the azimuth beam steering turret mechanism 610 and the azimuth turret 612 further rotating along the azimuth rotation axis.

[0058] Figure 12J is an exemplary diagram of the tactical HPM system 600 of Figure 3 at the ninth position 1860 according to one embodiment, showing the elevation / polar reflector further rotating along the elevation / polar axis and the azimuth beam steering turret mechanism further rotating along the azimuth rotation axis. Figure 12K is an exemplary diagram of the tactical HPM system 600 of Figure 3 at the tenth position 1870 according to one embodiment, showing the elevation / polar reflector further rotating along the elevation / polar axis and the azimuth beam steering turret mechanism further rotating along the azimuth rotation axis. Figure 12L is an exemplary diagram of the tactical HPM system 600 of Figure 3 at the eleventh position 1880 according to one embodiment. The 11th position 1880 shows the elevation / polar reflector 604 and azimuth reflector 606 rotated approximately 175 degrees from the initial deployment position in Figure 12F, and also shows the offset configuration of the polar / elevation reflector, including the offset portion 621 coupled to the elevation / polar support arm 608. As can be seen from Figures 12B to 12L, the distance and orientation between the elevation / polar reflector 604 and the azimuth reflector 606 are controlled by rotating the reflectors while moving them.

[0059] As shown in Figures 12B to 12L, in the configurations shown in these figures, the orientation and / or spacing between the elevation / polar reflector 604 and the azimuth reflector 606 is maintained even when the azimuth beam steering turret mechanism 610 and the azimuth turret 612 are rotated by approximately 185 degrees from the position shown in Figure 12F to the position shown in Figure 12L. In certain embodiments, the elevation / polar mechanical control subsystem 742 and the azimuth mechanical control subsystem 744 are constructed and configured so that the azimuth reflector 606 and the elevation / polar reflector 604 maintain a desired orientation and spacing regardless of rotation.

[0060] A brief reference to Figures 13A to 14I shows the individual movements of the elevation / polar angle reflector 604 and the azimuth angle reflector 606 in more detail.

[0061] Figure 13A is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a first deployment position 1300 according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated by approximately -5 degrees from the initial deployment position. Figure 13B is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a second deployment position 1310 according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated by approximately 0 degrees from the initial deployment position in Figure 12F. Figure 13C is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a third deployment position 1320, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated by approximately 15 degrees from the initial deployment position in Figure 12F.

[0062] Figure 13D is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a fourth deployment position 1330 according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated approximately 30 degrees from the initial deployment position in Figure 12F. Figure 13E is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a fifth deployment position 1340 according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated approximately 45 degrees from the initial deployment position in Figure 12F. Figure 13F is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a sixth deployment position 1350 according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated approximately 60 degrees from the initial deployment position in Figure 12F.

[0063] Figure 13G is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a seventh deployment position according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated approximately 85 degrees from the initial deployment position in Figure 12F. Figure 13H is an exemplary diagram of the tactical HPM system 600 of Figure 3 in an eighth deployment position according to one embodiment, where the azimuth reflector 606 is held in a fixed position at an azimuth of 0 degrees, and the elevation / polar reflector 604 is rotated approximately 95 degrees from the initial deployment position in Figure 12F.

[0064] Figure 14A is an exemplary diagram of the tactical HPM system 600 of Figure 3 at the ninth deployment position 1400 according to one embodiment, with the elevation / polar reflector 604 set to an angle of 45 degrees and the azimuth turret 612 rotated approximately -185 degrees from the initial deployment position in Figure 12F. Figure 14B is an exemplary diagram of the tactical HPM system 600 of Figure 3 at the tenth deployment position 1410 according to one embodiment, with the elevation / polar reflector 604 set to an angle of 45 degrees and the azimuth turret 612 rotated approximately -135 degrees from the initial deployment position in Figure 12F. Figure 14C is an exemplary diagram of the tactical HPM system 600 of Figure 3 at the eleventh deployment position 1420 according to one embodiment, with the elevation / polar reflector 604 set to an angle of 45 degrees and the azimuth turret 612 rotated approximately -90 degrees from the initial deployment position in Figure 12F.

[0065] Figure 14D is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a 12th deployment position 1430 according to one embodiment, where the elevation / polar reflector 604 is set to an angle of 45 degrees and the azimuth turret 612 is rotated by approximately -45 degrees from the initial deployment position in Figure 12F. Figure 14E is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a 13th deployment position 1440 according to one embodiment, where the elevation / polar reflector 604 is set to an angle of 45 degrees and the azimuth turret 612 is rotated by approximately 0 degrees from the initial deployment position in Figure 12F. Figure 14F is an exemplary diagram of the tactical HPM system 600 of Figure 3 at a 14th deployment position 1450 according to one embodiment, where the elevation / polar reflector 604 is set to an angle of 45 degrees and the azimuth turret 612 is rotated by approximately +45 degrees from the initial deployment position in Figure 12F.

[0066] Figure 14G is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a 15th deployment position 1460 according to one embodiment, with the elevation / polar reflector 604 set to an angle of 45 degrees and the azimuth turret 612 rotated approximately +90 degrees from the initial deployment position in Figure 12F. Figure 14H is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a 16th deployment position 1470 according to one embodiment, with the elevation / polar reflector 604 set to an angle of 45 degrees and the azimuth turret 612 rotated approximately +135 degrees from the initial deployment position in Figure 12F. Embodiments in Figures 14G and 14H also show that in certain embodiments, an offset configuration of the elevation / polar support arm 608 is realized using an offset portion 621 having two parts: an upper offset portion 621a operably coupled to the elevation steering head tilt actuator 617 and a lower offset portion 621b operably coupled to the azimuth turret 612. The upper offset portion 621a and the lower offset portion 621b are configured, as understood, to help provide stability and rigidity to the offset configuration.

[0067] Figure 14I is an exemplary diagram of the tactical HPM system 600 of Figure 3 in a 17th deployment position 1480 according to one embodiment, where the elevation / polar reflector 604 is set to an angle of 45 degrees and the azimuth turret 612 is rotated approximately +185 degrees from the initial deployment position in Figure 12F.

[0068] Referring again to Figure 4, it will be understood that in various embodiments, there may be various methods for keeping the reflectors (e.g., elevation / pole angle reflector 604 and azimuth reflector 606) in a fixed aspect ratio even while rotating (if necessary). For example, Figure 5 is a perspective view showing a side view 680 of another embodiment of the assembly of Figure 4 according to one embodiment. In the embodiment of Figure 5, instead of the reflector rotation deployment actuator 644 of Figure 3, this embodiment uses a type of linear actuator to house and deploy the azimuth reflector 606 and support structure 662. Comparing the embodiment of Figure 5 with the embodiment of Figure 3, the azimuth swivel ring and azimuth turret 612 are similar but slightly different in shape, however one of the differences in this embodiment lies in the azimuth reflector deployment mechanism.

[0069] Figure 7 is a simplified functional block diagram of an improved HPM system 700, according to one embodiment, with the addition of a shaped reflector redistribution stage / subsystem. Figure 7 helps illustrate how at least some embodiments of the disclosure herein are improvements over the exemplary prior art HPM system 100 of Figure 1. Figure 7 includes some elements similar to those shown in Figure 1, but is improved in several respects from Figure 1, which is achieved, for example, by providing a beam generation subsystem 710 configured to generate a vertically axisymmetric beam with a uniform power density distribution and high aperture efficiency, having the characteristics necessary to reach the target, based on target information 755 received by the control subsystem 708. This configuration is configured to improve the optics to enhance aperture efficiency and power density on the target. In at least some embodiments, the improved HPM system 700 of Figure 7 can also be used as part of a DEW system.

[0070] Referring to Figure 7, the input power and microwave source functions are provided in a manner similar to that described in Figure 1. In the HPM system 700 of Figure 7, pulsed power 102 is used to supply energy to the high-power microwave source 104. The pulsed power 102 includes a power supply 116 and a pulse generator 118, which in one embodiment is configured to supply an electrical pulse of at least 1 megavolt with a pulse duration of less than 1 μs. In the embodiment of Figure 7A, the high-power microwave source 104 is preferably provided via a linear beam source 108 such as a klystron, but is not limited thereto.

[0071] In a particular embodiment (for example, the tactical HPM system 600 in Figure 3), the pulsed power 102, the high-power microwave source 104, the beam generation subsystem 710, and the control subsystem 708 are constructed and configured to be located and operate internally, for example, within the trailer enclosure 602 (Figure 3), as part of the internal antenna system 702.

[0072] The output of the beam generation subsystem 710 (i.e., beam 723) is passed from the internal antenna system 702 to the external antenna system 704 (for example, through an opening in the trailer enclosure 602 such as an environmental window 722 (Figure 8), which may optionally be covered with RF-transmitting material or structure, i.e., a “window”), where the external antenna system 704 substantially includes a shaped reflector redistribution stage / subsystem 704, also referred to herein as the shaped reflector redistribution stage / subsystem 704.

[0073] The external antenna system 704 applies shaped reflector redistribution via a rotating azimuth reflector 606 (Figures 3 and 8), which functions as a sub-reflector in a shaped reflector pair consisting of the azimuth reflector 606 and the elevation / pole reflector 604. After a beam 723 with a uniform power density beam reaches the azimuth reflector 606, the azimuth reflector 606 is configured to limit beam expansion before the beam reaches the elevation / pole reflector 604. The azimuth reflector 606 and the elevation / pole reflector 604 work together to produce an output beam 727 that is output to the target 760 with axial symmetry in power density and phase, which helps to achieve invariance of equivalent isotropic radiated power (EIRP) in all beam directions. In certain embodiments, the beam 723 supplied to the external antenna system 704 is an HPM input beam used by the external antenna system 704 to form an output beam 727 containing HPM energy. In certain embodiments, the output beam 727, which is steered toward the target 760, is configured to direct the HPM energy toward the target 760 as part of the DEW system.

[0074] In certain embodiments, the stage / subsystem of this shaped reflector optics within the external antenna system 704 helps maximize antenna efficiency while minimizing RF energy spillover, particularly around the elevation / pole reflector 604, by more precisely limiting beam expansion between the azimuth reflector 606 (which also functions as a steering reflector) and the elevation / pole reflector 604. In certain embodiments, the stage / subsystem of this shaped reflector optics helps to deliver a 30-40% higher power density to a target with lower spillover radiation than many known systems. As will be understood by those skilled in the art, a higher power density on a target is advantageous not only for systems such as tactical HPM systems and DEW weapons, but also for any system that needs to provide a high power density during tracking and / or communication of a target or other entity (e.g., within a satellite communications system).

[0075] The structural, functional, and optical mechanisms by which all of this occurs are further explained below in relation to Figures 8 to 22.

[0076] Figure 8 is a simplified functional block diagram of a system 800 implementing the tactical HPM system 600 of Figure 3, according to one embodiment. Figure 8 shows how the functional block diagram of Figure 7 is implemented in the tactical HPM system 600 of Figure 3, and provides further functional details of its components. The simplified functional block diagram of system 800 in Figure 8 includes an internal antenna system 702 located within the trailer enclosure 602 in Figure 3, and an external antenna system 704 corresponding to the functional features shown outside the trailer enclosure 602, the external antenna system 704 including, but not limited to, an elevation / pole reflector 604, an azimuth reflector 606, an azimuth turret 612, and elevation / pole mechanical control subsystems 742 and 744.

[0077] The elevation / polar mechanical control subsystem 742 includes components configured to automatically control the movement of the elevation / polar reflector 604, including components that automatically raise and lower the elevation / polar reflector 604 in response to control signals and / or target information, as well as components that automatically rotate the elevation / polar reflector 604. In at least some embodiments, these components help maintain a fixed orientation between the elevation / polar reflector and the azimuth reflector 606 by automatically rotating the azimuth reflector 606 simultaneously with the elevation / polar reflector 604. As shown in Figure 8, in certain embodiments, a control subsystem 708 (which may be advantageously located inside the trailer enclosure 602, but may also be located outside the trailer enclosure 602) is configured to control the elevation / polar mechanical control subsystem 742, for example, via one or more elevation / polar control signals (e.g., elevation / control 709B). In certain embodiments, one or more elevation / pole angle control signals (e.g., elevation / pole angle control 709B) may include, where appropriate, commands to automatically move the elevation / pole angle reflector 604 to a retracted position (e.g., shown in Figures 6 and 18B herein) and / or to an extended position (e.g., shown in Figures 12B to 14I herein). In the exemplary embodiments of Figures 3 and 8, the elevation / pole angle mechanical control subsystem includes an elevation / pole angle reflector deployment mechanism and an elevation / pole angle support arm 608, a linear deployment actuator 642, an elevation beam steering drive 616, and an elevation steering head tilt actuator 617. Some of these components are illustrated and described more specifically in relation to Figure 4 (e.g., the elevation steering head tilt actuator 617, the linear deployment actuator 642, and the rotary deployment actuator 644), and their description will not be extensively repeated here.

[0078] As those skilled in the art will understand, in certain embodiments, the control subsystem 708 operably communicates with the computer network 815, thereby enabling the control subsystem 708 to receive target information 755 and / or other messages that the control subsystem 708 may use and / or process to control one or both of the internal antenna system and the external antenna system 704. Although not specifically shown in Figure 8, in certain embodiments, the control subsystem 708 is implemented separately and / or remotely from the internal antenna system 702 and is configured to wirelessly communicate with one or more of the components shown in system 800 (including, but not limited to, one or more of the power and microwave sources 706, beam generation subsystem 710, dual azimuth drive assembly 902, azimuth mechanical control subsystem 744, and elevation / pole mechanical control subsystem 742). In certain embodiments, the control subsystem 708 is located within the trailer enclosure 602 and is configured to wirelessly transmit one or more of its control signals 709 (for example, one or more of azimuth control 709A, elevation / pole angle control 709B, beam generation control 709C, and azimuth drive control 709D). In certain embodiments, the control subsystem 708 is operably coupled via one or more wired connections to transmit one or more of the aforementioned control signals 709. In certain embodiments, the control subsystem 708 is configured to communicate via a combination of wired and wireless communication. Furthermore, as can be understood, in certain embodiments, there may be multiple control subsystems 708, whether located within the trailer enclosure 602 or remotely from the trailer enclosure, and each control subsystem 708 provides specific control signals 709.

[0079] In certain embodiments, the control subsystem 708 is configured to automatically control the beam generation subsystem 710 based on target information 755 (for example, via beam generation control 709C), and the beam generation control 709C is configured to control one or more characteristics of the beam 723 supplied to the external antenna system 704. In certain embodiments, the control subsystem 708 is configured to automatically control the position of the azimuth turret 612 (or the position of any rotatable support structure used in the system 800) via turret control 709E, etc. In certain embodiments, the control subsystem is configured to automatically control at least one of the positions of the elevation reflector 604 (for example, via elevation / pole angle control 709B) and the azimuth reflector 606 (for example, via azimuth control 709A and / or azimuth drive control 709D).

[0080] In certain embodiments, one or more components of the elevation / polar mechanical control subsystem 742 are operably coupled to the azimuth turret 612. For example, in certain embodiments, the elevation / polar support arm 608 is operably coupled to the azimuth beam steering turret mechanism 610, which includes the azimuth turret 612 (for example, as shown in Figures 3 and 4, and Figures 8 and 18B-18I), to help the elevation / polar reflector 604 maintain the correct orientation both when retracted and deployed. In certain embodiments, the elevation / polar reflector 604 is operably coupled to the azimuth turret 612 via a polar reflector deployment mechanism and the elevation / polar support arm 608, as shown in Figures 3 and 9 herein, for example. Similarly, in certain embodiments, the azimuth reflector 606 is operably coupled to the azimuth turret 612 via an azimuth reflector deployment mechanism and the azimuth support arm 614, as shown in Figures 3 and 9 herein.

[0081] The linear deployment actuator 642, in combination with the elevation steering head tilt actuator 617 (also referred to herein as the elevation beam steering head tilt actuator 617), helps deploy the elevation / polar reflector 604 (for example, as shown in Figure 4 and Figures 18B to 18I further described above), and helps to achieve the retracted and deployed orientations of the elevation / polar reflector 604 at the ends of the range of motion. The elevation beam steering drive 616 operates to rotate the elevation / polar reflector 604 to achieve mechanical beam pointing to any point within the full hemispherical skydome. For example, in certain embodiments, the elevation steering head tilt actuator 617 rotates the elevation / polar reflector 604 and its drive around an axis different from the axis realized by the linear deployment actuator 642, driving the elevation / polar reflector 604 to its final operating and final retracted positions. In certain embodiments, the elevation beam steering drive unit 616 is implemented using an elevation drive assembly having a direct drive motor (not shown in Figure 8).

[0082] As is understood, direct-drive motors are selected and configured based on the weight and mass distribution of the components they move, as well as environmental loads such as wind forces and moments.

[0083] Referring further to Figure 8, the azimuth mechanical control subsystem 744 controls the movement of the azimuth reflector 606 in response to one or more azimuth control signals (e.g., azimuth control 709A) (from the control subsystem 708). In certain embodiments, one or more azimuth control signals (e.g., azimuth control 709A) may include, where appropriate, a command to automatically move the azimuth reflector 606 to a retracted position (e.g., as shown in Figures 6 and 18B herein). The azimuth mechanical control subsystem 744 includes an azimuth reflector deployment mechanism and azimuth support arm 614, a rotary deployment actuator 644, and an azimuth beam steering turret mechanism 610 (which is operably coupled to the azimuth turret 612). In certain embodiments, the rotary deployment actuator 644 is implemented using a single-degree-of-freedom tilted rotary drive unit 611 that operably communicates with a dual azimuth drive assembly 902 located within the trailer enclosure 602 in certain embodiments. This configuration provides the azimuth reflector 606 with a favorable bearing reaction load, resulting in higher rigidity of the azimuth reflector 606 compared to conventional hinged mechanisms with a comparable range of motion. For example, in certain embodiments, the deployment of the azimuth reflector 606 is performed using a large-diameter slewing bearing in an atypical tilted configuration, which provides excellent rigidity during deployment and low-profile storage capability in a single-degree-of-freedom mechanism. The movement of this large-diameter slewing bearing in an atypical tilted configuration is shown in Figures 12A to 12F, which are further described herein, and these figures illustrate the movement of the azimuth reflector 606 achieved by its single-degree-of-freedom tilted rotary drive unit 611. In certain embodiments, a dual azimuth drive assembly 902 responds to azimuth drive control 709D from a control subsystem 708.

[0084] In certain embodiments, the elevation / polar mechanical control subsystem and the azimuth mechanical control subsystem 744 are constructed and configured to obtain maximum rigidity in the deployed positions of the elevation / polar reflectors 604 and azimuth reflectors 606. In certain embodiments, the rotation of the elevation / polar reflectors 604 and azimuth reflectors 606 is controlled using adjustable hard stops that set play-free, repeatable endpoints. Thus, in certain embodiments, some or all of the design of the mechanisms of the elevation / polar mechanical control subsystem 742 and the azimuth mechanical control subsystem 744 is configured to emphasize stiffness, which helps to ensure a repeatable and consistent orientation between the elevation / polar reflectors 604 and azimuth reflectors 606, and helps to ensure a high aperture efficiency (e.g., 80-90%) of the pair of reflectors (i.e., elevation / polar reflectors 604 and azimuth reflectors 606) that rotate to steer the beam. In certain embodiments, one or more azimuth drive assemblies (e.g., a dual azimuth drive assembly 902) are provided within the trailer enclosure 602, alongside or as part of the internal antenna system 702, to drive the azimuth mechanical control subsystem 744. As those skilled in the art will understand, the dual azimuth drive assembly 902 is operably connected to the azimuth mechanical control subsystem 744.

[0085] Referring further to Figure 8, the external antenna system 704 receives the incoming beam through an opening in the trailer enclosure 602 that houses the internal antenna system 702. For example, in the embodiment shown in Figure 8, the beam passes through an environmental window 722 that is transparent to RF and can withstand the power contained within the beam. For example, in some embodiments, the environmental window 722 is made from materials similar to those used for the radome of the microwave antenna, such as certain thermoplastics and / or plastics such as polyurethane, polyurethane foam, composite materials such as fiberglass, quartz, and aramid fibers bonded with other resins, glass, and any material with a low dielectric constant that can withstand high-power microwave signals.

[0086] The internal antenna system 702 in Figure 8 includes one or more power and microwave sources 706, a beam generation subsystem 710, a dual azimuth drive assembly 902, an elevation / pole angle mechanical control subsystem 742, and a control subsystem 708 that operably communicates with the azimuth mechanical control subsystem 733. In certain embodiments, the control subsystem 708 provides azimuth control 709A to the azimuth mechanical control subsystem 744, elevation / pole angle control 709B to the elevation / pole angle mechanical control subsystem 742, beam generation control 709C to the beam generation subsystem 710, and azimuth drive control 709D to the dual azimuth drive assembly 902. In certain embodiments, the control subsystem 708 is implemented using one or more computer systems, for example, as illustrated and described in Figure 22 of this specification (further described below). The one or more power and microwave sources 706 are implemented in certain embodiments as described above in relation to Figure 7. In the embodiment shown in Figure 8, one or more power and microwave sources 706 are configured to route and distribute power to the beam generation subsystem 710 and its components (for example, one or more microwave components 110, and the beam shaping and beam focus control subsystem 716).

[0087] As those skilled in the art will understand, the spacing between reflectors and / or the shape of the reflectors are determined by the RF characteristics required for a given application and will have different three-dimensional (3-D) curvatures depending on the specific design. The beam 723 output through the environmental window 722 then reaches the external antenna system 704, where the beam 723 first reaches the azimuth reflector 606 (which, together with the elevation / pole angle reflector 604, acts as a steering reflector for the received beam 723). As shown in Figures 9 and 12A to 14I (mentioned above), in certain embodiments, the azimuth reflector 606 and the elevation / pole angle reflector 604 rotate simultaneously in their respective ways while maintaining the required orientation. Furthermore, as shown in Figures 9 and 12A to 14I, in certain embodiments, one of the azimuth reflector 606 and the elevation / pole angle reflector 604 can rotate (for example, around their respective axes), while the other reflector may or may not rotate around its respective axes. As shown in Figure 11, the azimuth reflector 606 is configured to rotate around a first rotation axis, indicated in Figure 9 as the azimuth rotation axis 1404. The elevation / polar reflector 604 is configured to rotate around a second rotation axis, the polar / elevation rotation axis 1402, which in certain embodiments is orthogonal to the azimuth rotation axis 1404 (although this is not required). In certain embodiments, two reflectors rotating on orthogonal axes (e.g., the elevation / polar reflector 604 and the azimuth reflector 606) have been found to be the simplest physically possible configuration to achieve complete skydome coverage. For example, in certain embodiments, the beam 727 to the target is configured to rapidly scan the entire skydome with minimal beam degradation in any direction.

[0088] As described above, when the external antenna system 704 steers the azimuth of the final beam (and both the elevation / pole reflector 604 and the azimuth reflector 606) toward the target 760, as shown in Figures 14B to 14H, the azimuth turret rotates around the azimuth rotation axis 1404, for example, the Y-axis. The azimuth reflector 606 rises and falls during rotation until it reaches its operational position when deployed, and does not detect RF energy until it is in the deployed configuration (for example, the configuration shown in Figure 14D). Similarly, the elevation / pole reflector rises and rotates around the azimuth rotation axis 1404. These rotations can be best illustrated in these figures by comparing the relative positions of the elevation / pole reflector 604 and the azimuth reflector 606 in Figure 12J with the positions of these same reflectors in Figure 12K, using the rotation reference point A 1805 in both figures. In these examples, we assume that in the xy coordinate system, the y-axis runs vertically and flatly to the page, and the x-axis runs horizontally and flatly to the page, so that rotations around the x and y axes (as shown, for example, with respect to the axes in Figure 9) both appear to partially move off-page and back. Comparing Figures 12J and 12K, the azimuth reflector 606 moves approximately 60 degrees counterclockwise in the direction of rotation toward the reader along the azimuth rotation axis 1404, which roughly corresponds to the y-axis in the image. Also, comparing the rotation reference point A 1805 from Figure 12J to Figure 12K, we can see that the elevation / polar angle reflector 604 rotates toward the reader in a counterclockwise direction along the x-axis, moving off-page. Figures 13A to 13H, mentioned earlier in this specification, illustrate the movement of the elevation / polar angle reflector 604 in more detail. Figures 14A to 14I, mentioned earlier in this specification, illustrate the azimuth rotation in more detail.

[0089] Another advantage of the aforementioned rotations of the azimuthal reflector 606 and the elevation / pole angle reflector 604 is that the elevation / pole angle output beam 727 (i.e., the beam to the target 760) achieves axial symmetry in both power density and phase, thereby ensuring an invariant equivalent isotropically radiated power (EIRP) in all beam directions. This will be further discussed in relation to Figure 12, which will be described further in this specification.

[0090] Herein, we briefly refer to Figures 9 to 11, which show exemplary embodiments of the system configurations of Figures 3, 7, and 8 according to one embodiment. For example, Figure 9 is a simplified side section view 900 of the tactical HPM system of Figures 3, 7, and 8 according to one embodiment, showing a simplified block diagram of part of the electronic assembly within the trailer enclosure 602, including the internal antenna system 702 and the external antenna system 704, and showing an exemplary reflection pattern of the HPM beam 850. Figure 9 also shows a simplified side section view 900 of the layout of an exemplary system implementation of the system of Figures 7 and 8. As shown in Figure 9, the internal antenna system 702 (mentioned earlier in relation to Figure 8) is housed within the trailer enclosure 602. The components shown in Figure 9 are numbered and correspond to the same elements shown in Figures 3, 7, and 8, and therefore will not be repeated here. Figure 9 helps to better illustrate the movement of the beam from the internal antenna system 702 to the external antenna system 704. As shown in Figure 9, integrating the internal antenna structure into the trailer enclosure 602 helps minimize redundant structures and reduce the size and weight of the system.

[0091] For example, referring to Figure 9, the beam generation subsystem 710 is an axisymmetric beam with high aperture efficiency and a uniform power density distribution, along with the characteristics necessary to reach the target based on target information 755, and is configured to be reflected by the azimuthal reflector 606, then directed to the elevation / pole-angle reflector 604, and then directed to the target at three locations via the beam 727, as shown in Figure 9. The three beam paths, indicated by dotted lines (path sections 834, 836, and 838), short dashed lines (beam path sections 828, 830, and 832), and long dashed lines (beam path sections 820, 822, and 824), are exemplary examples of the beam path as it is output to the target as beam 727, from the output of the internal antenna system 702 through the external antenna system 704 and its shaping reflector stage / subsystem (formed by the azimuthal reflector 606 and the elevation / pole-angle reflector 604).

[0092] Advantageously, the layout of the components within the internal antenna system 702 is chosen to share the volume within the trailer enclosure 602 with other mechanical structures, making efficient use of space and meeting the aforementioned height requirements.

[0093] Figure 10 is a simplified top view 1000 of a portion of the electronic assembly inside the shelter of Figure 9, showing the position of the beam generation subsystem 710 relative to the opening 1002 of the environment window 722, which is also the position of the dual azimuth drive assembly 902, which occupies a corner of the assembly in this exemplary embodiment. In certain embodiments, these dual azimuth drive assemblies 902 can operably communicate with the azimuth mechanical control subsystem 744.

[0094] In certain embodiments, as further described herein, the novel approach to shaped reflector design described herein, as well as the improved stiffness / rigidity of the reflector support, can help enable the rotating beam-steering reflector to achieve an aperture efficiency of 80–90%. In addition to enabling the rotation of the reflector by a non-Gaussian beam, the design of the shaped reflector design stage / subsystem enhances the control of spillover radiation in the external antenna system 704 around the elevation / pole-angle reflector 604 by more precisely restricting the beam. As a result, a mobile HPM antenna design with a retractable beam-steering reflector is realized, resulting in a 30–40% increase in power density on the target with lower spillover radiation than previously possible.

[0095] Figure 15A is a side view 1900 of the elevation / polar reflector motion envelope of the elevation / polar reflector 604 of the tactical HPM system 600 of Figure 3, according to one embodiment; Figure 15B is a rear view 1950 of the elevation / polar reflector motion envelope of the elevation / polar reflector 604 of the tactical HPM system 600 of Figure 3, according to one embodiment; and Figure 15C is an auxiliary diagram 1975 of the elevation / polar reflector motion envelope of the elevation / polar reflector 604 of the tactical HPM system 600 of Figure 3, according to one embodiment. Figures 15A-C help to illustrate in more detail certain components that help move the elevation / polar reflector 604 during operation, deployment, and / or retraction, such as the elevation / polar support arm 608 and the elevation beam steering drive unit 616, as well as the linear deployment actuator 642, etc. Figures 15B-C also show the unique offset portion 621 of the elevation / polar angle support arm 608, which provides the support arm with several advantageous operational features. The offset portion 621 ensures clearance for the elevation / polar angle reflector 604 even at the terminal viewing angle. The offset portion 621 is configured to beside the elevation / polar angle reflector 604 rather than below it when folded and stored, so the offset portion 621 also reduces the height of the elevation / polar angle reflector 604 when stored (for example, as shown in Figure 6 and especially in Figure 14A).

[0096] As shown in Figures 15A, B, and C, the elevation / polar reflector 604 has a motion envelope 2004 of -5° to +95°, which restricts the polar / elevation motion to one side. In certain embodiments, restricting the elevation to one side (i.e., -5° to 95°) provides full hemispherical coverage. By restricting the movement of the elevation / polar reflector 604, the tilt joint in the elevation / polar mechanical control subsystem (e.g., elevation steering head tilt actuator 617) can move toward the azimuth axis (see Figure 11), thus increasing the space for housing the elevation / polar reflector 604. Furthermore, restricting the elevation to only one side allows for a more adequate base structure. If, instead, the movement of the elevation / polar reflector 604 were allowed from 0° to 180°, the movement of the elevation / polar reflector 604 would pass through most of the elevation / polar support arm structure 609. Therefore, the -5° to +95° movable range of the elevation / polar angle reflector 604 provides optimal structural support while minimizing the height when stored.

[0097] Figure 16 is an exemplary figure of the first motion envelope 1605 of the elevation / polar angle reflector 604 of the tactical HPM system 600 of Figure 3, according to one embodiment. As shown in Figure 16, the first motion envelope 1605 is a small envelope and indicates the area covered when the elevation / polar angle reflector 604 is rotated -5 degrees. Figure 17 is an exemplary figure of the second motion envelope 607 of the elevation / polar angle reflector 604 of the tactical HPM system 600 of Figure 3, according to one embodiment. The second motion envelope 607 indicates the area covered when the elevation / polar angle reflector 604 is rotated +95 degrees.

[0098] Figure 18 is an exemplary Figure 2200 of the tactical HPM system of Figure 3, showing the path of the RF beam 2202 from the elevation / pole angle reflector 604 at the terminal depression position according to one embodiment. Figure 18 (and Figures 15B and C) also shows how the elevation / pole angle reflector 604 is positioned offset from the support arm by the elevation / pole angle support arm 608 and the elevation beam steering drive 616 (see offset portion 621). This offset portion 621 of the elevation / pole angle support arm 608 ensures clearance for the elevation / pole angle reflector at terminal line-of-sight angles such as the terminal depression in Figure 18. This offset portion 621 (also shown in Figures 15B and 15C) helps to allow the elevation / pole angle reflector 604 to have enough space to rotate without having to collide with other equipment, which is a challenge as the elevation / pole angle reflector 604 is often a fairly large reflector that requires space to move. Furthermore, the offset portion 621 of the elevation / pole angle support arm 608 also provides a unique and important advantage in at least some embodiments, for this reason that the offset portion 621 of the elevation / pole angle support arm 608 allows for efficient storage of the elevation beam steering head tilt actuator 617, which is stored laterally rather than on top of the elevation / pole angle support arm 608 (as shown in Figure 14A, for example), and reduces the overall envelope when stored.

[0099] Figure 19 is a first figure 2300 showing the first RF beam envelope 2302 of the elevation / pole angle reflector 604 of the tactical HPM system 600 of Figure 3, when the elevation / pole angle reflector 604 is configured at a depression angle of 0 degrees according to one embodiment. Figure 20 is a second figure 2400 showing the second RF beam envelope 2402 of the elevation / pole angle reflector 604 of the tactical HPM system 600 of Figure 3, when the elevation / pole angle reflector 604 is configured at a beam elevation angle of 95 degrees from the horizon, according to one embodiment.

[0100] As shown and described in Figures 3 to 20, at least some embodiments of the HPM systems, including the HPM antenna pedestals described herein, are configured to minimize stowed volume, allowing very large antenna systems (e.g., the molded reflector stage / subsystem 704 in Figure 3) to be housed in cargo vehicles such as military C-17 aircraft, enabling air transport and allowing the HPM system to be quickly transported where it is needed. As shown at least in Figures 3, 6, and 14A, at least some embodiments provide a stowed configuration in which large external reflectors (e.g., elevation / pole reflectors 604 and azimuth reflectors 606, as well as reflectors included within the internal antenna system) are housed in a trailer enclosure 602, efficiently reducing size to support air, road, and sea transport. As shown in Figures 14A to 14h, the tactical HPM system 600 in Figure 3 is easily deployable and provides a rapid "fire and move" capability not shown in existing HPM systems. The implementation of several new mechanisms enables a low-profile stowed volume.

[0101] As previously shown in Figures 14a to 20, complete elevation beam steering coverage (-5° to +95°) using a large 16-foot x 10-foot polar-angle primary reflector is achieved by the unique offset portion 621 of the elevation / polar-angle support arm 608, and by the deployment mechanism for the elevation / polar-angle reflector 604 (e.g., elevation / polar-angle mechanical control subsystem 742) and the deployment mechanism for the azimuth reflector (e.g., azimuth mechanical control subsystem 744). In at least some embodiments of this specification, as described above, the deployment of the azimuth reflector 606 uses a large-diameter slewing bearing in an atypical inclined configuration that provides excellent rigidity and low-profile storage capability during deployment in a single-degree-of-freedom mechanism. Furthermore, the stage / subsystem of the molded reflector optics maximizes the antenna efficiency of the tactical HPM system 600 while minimizing RF energy spillover, as described above, particularly in relation to Figures 7 to 9 and 11 to 13.

[0102] Those skilled in the art will understand that some or all of the functions and operations described herein can be controlled automatically as part of one or more computer implementations, with or without user intervention. For example, Figure 21 is a flowchart of process 2500 available for use in the tactical HPM system of Figure 3, and process 2500 can be implemented using a computer system such as the one further described herein in relation to Figure 22.

[0103] First, referring to the systems in Figures 21 and 3, and the simplified functional block diagrams of HPM system 700 in Figure 7 and system 800 in Figure 8, at startup (block 2505), the system receives target information 755 regarding the beam orientation and / or the orientation of transmission by the system (block 2515). Note that if operation is in progress, this may correspond to updated target information and / or orientation (see below in relation to block 2580). Based on the received information, control signals 709 (for example, one or more of the azimuth control 709A, elevation / pole angle control 709B, beam generation control 709C, and azimuth drive control 709D) are transmitted to the corresponding components (for example, the azimuth and elevation mechanisms (for example, the elevation / pole angle mechanical control subsystem 742 and / or azimuth mechanical control subsystem 744), the elevation / pole angle mechanical control subsystem 742, the beam generation subsystem 710, and the dual azimuth drive assembly 902, respectively) to position the azimuth reflector 606 and the elevation / pole angle reflector 604 to receive the beam for operation (block 2520). As described herein, in response to the received target information, appropriate high-power microwave radiation for propagation within the waveguide is generated and provided to the waveguide (or other appropriate microwave component) for transmission via a corresponding horn (e.g., within the beam generation subsystem 710) or other microwave component (block 2530) for propagation from the internal antenna system 702 to the external antenna system 704.

[0104] Suitable high-power microwave radiation is generated (e.g., in a power and microwave source(s) 706) to propagate within the waveguide and supplied to the waveguide for transmission. A horn (or other suitable component) converts the EM power into high-purity linearly polarized free-space radiation (e.g., wide-angle radiation) to form an axisymmetric perpendicular beam with a uniform power density distribution, high aperture efficiency, and (optionally) other properties required for the target (block 2535).

[0105] The beam is supplied / reflected to the azimuth reflector 606 via the environment window 722 (block 2560). The beam is received by the azimuth reflector 606, which functions as an azimuth steering reflector, and reflects the beam toward the elevation / pole reflector 604 in the desired direction (block 2565). The beam is received from the azimuth reflector 606 (azimuth steering reflector) at the elevation / pole reflector 604 (which functions as an elevation steering reflector) and reflected in the desired direction (e.g., toward a target) (block 2570). During operation, in certain embodiments, the control subsystem 708 automatically and continuously controls and steers the azimuth reflector 606 and / or the elevation / pole reflector 604 during deployment to direct the beam as needed (block 2575). For example, in certain embodiments, a check is performed to determine whether updates related to target information and / or beam orientation have been received (block 2580). If there is an update (the answer to block 2580 is "YES"), the process returns to block 2515. If there is no update, a check is performed to determine whether the operation is complete or not (block 2585). If the answer to block 2585 is "NO", the process moves to block 2575. If the answer to block 2585 is "YES", the process moves to block 2590.

[0106] In block 2590, the tactical HPM system 600 controls the deployment of the azimuth and elevation reflectors so that these reflectors are positioned for retraction for movement and / or transport (block 2590). The process then ends (block 2595). Figure 22 is a block diagram of an exemplary computer system usable in at least some of the systems, apparatus, methods, and / or operations of Figures 3 to 25, according to one embodiment. As understood, at least some parts of the tactical HPM system 600 and the corresponding system of Figure 3, the HPM system 700 of Figure 7, and / or the system 800 of Figure 8, together with other calculations and controls explicitly and implicitly described herein, may be implemented in certain embodiments using one or more processors and / or computer systems. Figure 22 is a block diagram of an exemplary computer system 2600 usable in at least some of the systems, apparatus, and methods of Figures 2 to 15, according to one embodiment. For example, in some embodiments, the computer system 2600 of Figure 22 may be usable to implement some or all of the processing related to the transmit channel processing block 446 or the receive channel processing block 456 of Figure 4, as understood. The computer system 2600 may also be used to implement all or some of any of the methods, formulas, and / or calculations described herein.

[0107] As shown in Figure 22, the computer 2600 may include a processor / CPU 2602, volatile memory 2604 (e.g., RAM), non-volatile memory 2606 (e.g., one or more hard disk drives (HDDs), one or more solid-state drives (SSDs) such as flash drives, one or more hybrid magnetic and solid-state drives, and / or one or more virtual storage volumes, e.g., cloud storage, or a combination of physical and virtual storage volumes), a graphical user interface (GUI) 2610 (e.g., a touchscreen, display, etc.), and input and / or output (I / O) devices 2608 (e.g., a mouse, keyboard, etc.). The volatile memory 2604 stores, for example, journal data 2604a, metadata 2604b, and a pre-allocated memory area 2604c. In some embodiments, the non-volatile memory 2606 may include an operating system 2614, computer instructions 2612, and data 2616. In certain embodiments, computer instruction 2612 is configured to provide several subsystems, including a routing subsystem 2612A, a control subsystem 2612b, a data subsystem 2612c, and a write cache 2612d. In certain embodiments, computer instruction 2612 is executed by the processor / CPU 2602 from volatile memory 2604 to implement and / or execute at least a portion of the systems and processes shown in Figures 1-15. The program code is also applicable to data input using an input device or GUI 2610, or data received from an output I / O device 2608.

[0108] The systems, architectures, and processes of Figures 1-22 are not limited to use with the hardware and software described and illustrated herein, but can find applicability in any computing or processing environment, and in any kind of machine or set of machines capable of running computer programs and / or implementing radar systems (including software-defined radar in some embodiments). The processes described herein can be implemented in hardware, software, or a combination of both. The logic for performing the methods described herein can be embodied as part of the system shown in Figure 22. The processes and systems described herein are not limited to the specific embodiments described, nor are they specifically limited to the specific processing order shown. Rather, any block of the process can be rearranged, combined, or removed in parallel or series as necessary to achieve the results described herein.

[0109] The Processor / CPU2602, or any processor used to carry out the embodiments described herein, may be implemented by one or more programmable processors that execute one or more computer programs to perform the functions of the system. As used herein, the term “processor” means an electronic circuit that performs a function, operation, or sequence of operations. The function, operation, or sequence of operations may be hardcoded in the electronic circuit or softcoded by instructions held in a memory device. The “processor” may perform a function, operation, or sequence of operations using digital values ​​or analog signals. In some embodiments, the “processor” may be implemented in one or more application-specific integrated circuits (ASICs). In some embodiments, the “processor” may be implemented in one or more microprocessors with associated program memory. In some embodiments, the “processor” may be implemented in one or more separate electronic circuits. The “processor” may be analog, digital, or mixed signal. {2} In some embodiments, the “processor” may be one or more physical processors or one or more “virtual” (e.g., remotely located processors or “cloud”) processors.

[0110] Various functions of a circuit or system element may also be implemented as processing blocks of a software program. Such software may be used, for example, in one or more digital signal processors, microcontrollers, or general-purpose computers. The embodiments described can be implemented in hardware, a combination of hardware and software, software, or software executed by one or more physical or virtual processors.

[0111] Some embodiments can be implemented in the form of methods and apparatus for carrying out such methods. The embodiments described above can also be implemented in the form of program code stored, for example, in a storage medium, loaded and / or executed by a machine, or transmitted via some transmission medium or carrier, for example, via electrical wiring or cables, via optical fibers, or via electromagnetic radiation. Non-temporary machine-readable media may include, but are not limited to, tangible media such as hard drives, floppy disks, and magnetic tape media, optical recording media such as compact discs (CDs) and digital multipurpose discs (DVDs), flash memory, solid-state memory such as hybrid magnetic and solid-state memory, non-volatile memory, volatile memory, etc., but do not include temporary signals themselves. When program code is incorporated into a non-temporary machine-readable medium and loaded into a machine such as a computer and executed by that machine, the machine becomes an apparatus for carrying out the method.

[0112] When implemented in one or more processing devices, a program code segment, in combination with a processor, provides a unique device that operates similarly to a specific logic circuit. Such processing devices may include, for example, general-purpose microprocessors, digital signal processors (DSPs), reduced instruction set computers (RISCs), composite instruction set computers (CISCs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), programmable logic arrays (PLAs), microcontrollers, embedded controllers, multicore processors, and / or others, including one or more combinations of those described above. The embodiments described above may also be implemented in the form of a bitstream or other sequence of signal values ​​transmitted electrically or optically through a medium, magnetic field fluctuations stored on a magnetic recording medium, etc., generated using the method and / or apparatus described in the claims.

[0113] For example, when program code is loaded into a machine such as the computer in Figure 22 and executed by the machine, the machine becomes a device for implementing one or more of the embodiments described above. When implemented in one or more general-purpose processors, the program code, in combination with such processors, provides a unique device that operates similarly to a specific logic circuit. Thus, a general-purpose digital machine can be transformed into a dedicated digital machine. Figure 22 shows program logic 2624 embodied in a computer-readable medium 2620, as illustrated, which is coded in computer-executable code configured to perform the reservation service process of the present invention and thereby form a computer program product 2622. The logic may be the same logic in memory loaded into the processor. The program logic can also be embodied in a software module as a module or as a hardware module. The processor may be a virtual processor or a physical processor. The logic may be distributed across multiple processors or virtual processors to execute the logic.

[0114] In some embodiments, the storage medium may be a physical or logical device. In some embodiments, the storage medium may consist of physical or logical devices. In some embodiments, the storage medium may be mapped across multiple physical and / or logical devices. In some embodiments, the storage medium may reside in a virtual environment. In some embodiments, the processor may be a virtual or physical embodiment. In some embodiments, the logic may be executed through one or more physical or virtual processors.

[0115] Furthermore, any or all of the embodiments described herein and / or shown in Figures 1 to 22 herein are, - U.S. Patent No. 11,233,306, issued on January 25, 2022, titled "Duo-quad wideband waveguide combiner / mode-converter transforming two rectangular waveguides in the TE10 rectangular mode to a single circular waveguide output in the TE01 mode," - U.S. Patent No. 11,245,172, issued on February 8, 2022, titled "Wideband waveguide combiner / mode-converter transforming N rectangular waveguides in the TE10 rectangular mode to a single circular waveguide output in the TE01 mode." - It is intended that this may be adapted to be combined with and / or work in conjunction with the technologies described in one or more U.S. patent applications and patents of the same applicant, including but not limited to U.S. Patent No. 7,443,573, issued on 28 October 2008, titled "Spatially-fed high-power amplifier with shaped reflectors," and U.S. Patent No. 6,243,047, issued on 5 June 2001, titled "Single Mirror Dual Axis Beam Waveguide Antenna System."

[0116] The patents and publications of the same applicant described herein are incorporated herein by reference. However, it should be understood that the disclosed embodiments are not limited to use in the exemplary systems described herein. The embodiments described herein have numerous uses and are not limited to the exemplary uses described herein. It should be recognized that such references and examples are made in an effort to enhance the clarity of the explanation of the concepts disclosed herein. Such references are not intended, and should not be construed as limiting the use or application of the concepts, systems, arrangements, and techniques described herein to use only with them or in any other system.

[0117] For the purpose of illustrating this embodiment, the disclosed embodiment is described as being embodied in a particular configuration using a special logical configuration; however, those skilled in the art will recognize that the device is not limited to a particular configuration and is limited only by the claims contained herein. Furthermore, it is anticipated that many related technologies will be developed while the patent maturing from this application remains in effect, and the scope of the corresponding terms is intended to a priori include all such novel technologies.

[0118] In this disclosure, the terms “comprises,” “comprising,” “includes,” “including,” and “having,” and their variations, mean at least “including, but not limited to.” Where used herein, unless clearly indicated otherwise in context, the singular forms “a,” “an,” and “the” include multiple references. Various elements described in the context of a single embodiment may be provided separately or in any suitable partial combination. Furthermore, it will be understood that various modifications in the details, materials, and arrangement of the parts described and illustrated herein can be made by those skilled in the art without departing from the following claims.

[0119] Throughout this disclosure, unless explicitly indicated otherwise in the context, individual elements described may be singular or plural. For example, the terms “circuit,” “circuit configuration,” and “module” may include either a single component or multiple components, which may be active and / or passive, connected or coupled together to provide the described function. In the drawings, similar or related elements have similar or related letter, numeral, or alphanumeric designations. Furthermore, while the disclosed embodiments have been described in the context of implementations using separate components, including several components, including one or more integrated circuit chips, alternatively, the function of any component or circuit may be implemented using one or more appropriately programmed processors, depending on the signal frequency or data rate to be processed and / or the function to be achieved. Furthermore, similarly, the total number of elements or components shown in the drawings for this application is not intended to be limiting, and a person skilled in the art will recognize that the number of particular components may, in some cases, be selected to suit the requirements of a particular user.

[0120] In describing and illustrating embodiments of this specification, certain terms (e.g., languages, phrases, product brand names, etc.) may be used in the text and drawings for clarity. These names are merely examples and not limiting. Embodiments described herein are not limited to the specific terms thus selected, and each specific term includes at least all grammatical, literal, scientific, technical, and functional equivalents, as well as any other equivalents that operate in a similar manner to achieve similar purposes. Furthermore, in the drawings, figures, and text, certain features, elements, circuits, modules, tables, software modules, systems, etc., may be given specific names. However, such terms used herein are for illustrative purposes only and are not limiting.

[0121] While embodiments included herein are described and illustrated in a favorable manner with a certain degree of detail, it should be understood that this disclosure is merely illustrative, and many modifications can be made to the details of configurations, component combinations, and arrangements without departing from the spirit and scope of the embodiments described. While at least some principles of the art are described and illustrated with reference to specific embodiments, it should be recognized that the art and embodiments described herein can be implemented in many other different forms and in many different environments. The art and embodiments disclosed herein can be used in combination with other arts. Furthermore, all publications and references cited herein are expressly incorporated herein by reference in their entirety. Individual elements of different embodiments described herein can be combined to form other embodiments not specifically described herein. Various elements described in the context of a single embodiment may be provided separately or in any suitable partial combination. Other embodiments not specifically described herein should be understood to be within the scope of the following claims.

Claims

1. It is an antenna system, A reflector subsystem configured to receive an input beam and reflect the input beam to generate an output beam directed toward at least one target, wherein the reflector subsystem comprises an elevation reflector having a first range of motion and configured to steer the input beam in the elevation direction, and an azimuth reflector having a second range of motion and configured to steer the input beam in the azimuth direction, wherein the output beam is steered toward the target in both the elevation and azimuth directions, A rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector, and configured to rotate the elevation reflector and the azimuth reflector simultaneously. A first support member comprising a longitudinal portion coupled to the rotatable support structure and an offset portion coupled to the elevation reflector, wherein the offset portion is configured to offset the elevation reflector from the longitudinal portion, A second support member having a first end connected to the rotatable support structure and a second end connected to the azimuth reflector, Equipped with, An antenna system in which, during beam steering of the output beam, the offset portion is configured to allow clearance of the elevation reflector to the end of the first movable range of the elevation reflector during beam steering of the output beam.

2. The antenna system according to claim 1, wherein the input beam includes an axisymmetric beam having a uniform power density distribution.

3. The antenna system according to claim 1, wherein the first movable range includes an angular range of approximately -5° to +95°.

4. The antenna system according to claim 1, wherein the elevation reflector is configured to have an deployed position and a retracted position, and in the retracted position, the offset portion of the first support member is configured to position the elevation reflector steering drive device next to the longitudinal portion of the first support member, and in the retracted position, the arrangement of the elevation reflector is configured to minimize the height of the elevation reflector when it is retracted.

5. The antenna system according to claim 1, further comprising a linear actuator configured to raise the elevation reflector to an deployed position and lower the elevation reflector to a retracted position.

6. The antenna system according to claim 1, further comprising an elevation beam steering drive device operably coupled to the elevation reflector and the rotatable support structure, wherein the elevation beam steering drive device is configured to rotate the elevation reflector about an elevation rotation axis when the elevation reflector is in the deployed position.

7. The antenna system according to claim 1, further comprising a single-degree-of-freedom inclined rotary drive device operably coupled to the second support member and configured to rotate the second support member along a first end of the second support member to position the azimuth reflector coupled to the second end in a retracted position and an extended position, wherein the retracted position of the azimuth reflector is configured to minimize the height of the azimuth reflector when it is retracted.

8. The system further comprises an elevation beam steering drive device operably coupled to the elevation reflector and the rotatable support structure, The elevation beam steering drive device is configured to rotate the elevation reflector around the elevation rotation axis when the elevation reflector is in the deployed position, and when the azimuth reflector is in the deployed position, The rotatable support structure is configured to rotate the azimuth reflector around an azimuth rotation axis, The antenna system according to claim 7, wherein when both the elevation reflector and the azimuth reflector are deployed and the input beam is received, the elevation beam steering drive and the rotatable support structure are configured to cooperate so that the antenna system can direct the output beam to any point within a complete hemispherical skydome.

9. The aforementioned input beam includes a high-power microwave signal. The elevation reflector is configured to have a first deployed position and a first retracted position. In the first storage position of the elevation reflector, the offset portion of the first support member is configured to position the elevation reflector next to the longitudinal portion of the first support member. In the first storage position of the elevation reflector, the arrangement of the elevation reflector is configured to minimize the height of the elevation reflector when it is stored. The antenna system according to claim 8.

10. The antenna system according to claim 5, further comprising an elevation reflector and an elevation steering head tilt actuator operably coupled to the rotatable support structure, wherein the elevation steering head tilt actuator is configured to cooperate with the linear actuator to produce movement of the elevation reflector such that the elevation reflector is retracted into a horizontal position.

11. The antenna system according to claim 1, wherein the input beam includes a high-power microwave (HPM) signal, and the output beam, which is steered toward the target, is configured to direct HPM energy toward the at least one target as part of a directed energy weapon (DEW) system.

12. The antenna system is configured to communicate operably with a control subsystem, the control subsystem is configured to receive information about the at least one target, and based on the information about the at least one target, Characteristics of the aforementioned input beam, The position of the rotatable support structure, The position of the aforementioned elevation reflector, and The position of the aforementioned azimuth reflector, The antenna system according to claim 1, configured to automatically control at least one of the following.

13. The antenna system according to claim 1, wherein the input beam includes a high-power microwave (HPM) input beam, the antenna system is sized to operate with the HPM input beam, the rotatable support structure is operably coupled to a movable structure, the movable structure is configured to have a recessed area sized to receive the elevation reflector and the first support member when the elevation reflector and the first support member are in a first stowed position.

14. The antenna system has a first height when the elevation reflector is in the first storage position and the azimuth reflector is in the second storage position. The aforementioned movable structure has a second height, The combination of the first height and the second height corresponds to the overall height sized to fit inside a C-17 aircraft. The antenna system according to claim 13.

15. The antenna system according to claim 14, wherein the movable structure comprises a beam generation subsystem configured to generate the HPM input beam for the antenna system.

16. A method for directing a high-power microwave (HPM) beam towards a target, A reflector subsystem is configured to receive a high-power microwave (HPM) input beam and reflect the HPM input beam to generate an HPM output beam directed toward at least one target, wherein the reflector subsystem comprises an elevation reflector having a first range of motion and configured to steer the input beam in the elevation direction, and an azimuth reflector having a second range of motion and configured to steer the input beam in the azimuth direction, and the HPM output beam is steered toward the target in both the elevation and azimuth directions. A rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector, The rotatable support structure is configured to rotate the elevation reflector and the azimuth reflector simultaneously, The method of connecting the elevation reflector to the rotatable support structure via a first support member comprising a longitudinal portion connected to the rotatable support structure and an offset portion connected to the elevation reflector, wherein the offset portion is configured to offset the elevation reflector from the longitudinal portion, The first end of the second support member is connected to the rotatable support structure, and the second end of the second support member is connected to the azimuth reflector, Steering the HPM output beam toward the target, wherein during the beam steering, the offset portion is configured to allow clearance of the HPM output beam from the elevation reflector to the end of the first movable range of the elevation reflector during the beam steering. Methods that include...

17. Receiving information about at least one of the aforementioned targets, Based on the information relating to at least one target, Characteristics of the aforementioned input beam, The position of the rotatable support structure, The position of the aforementioned elevation reflector, and The position of the aforementioned azimuth reflector, To automatically control at least one of the following, The method according to claim 16, further comprising:

18. A method for housing a reflector in a high-power microwave (HPM) antenna system, A reflector subsystem is configured to receive a high-power microwave (HPM) input beam and reflect the HPM input beam to generate an HPM output beam directed toward at least one target, wherein the reflector subsystem comprises an elevation reflector having a first range of motion and configured to steer the input beam in the elevation direction, and an azimuth reflector having a second range of motion and configured to steer the input beam in the azimuth direction, and the HPM output beam is steered toward the target in both the elevation and azimuth directions. A rotatable support structure is operably coupled to the azimuth reflector and the elevation reflector, The rotatable support structure is configured to rotate the elevation reflector and the azimuth reflector simultaneously, The method of connecting the elevation reflector to the rotatable support structure via a first support member comprising a longitudinal portion connected to the rotatable support structure and an offset portion connected to the elevation reflector, wherein the offset portion is configured to offset the elevation reflector from the longitudinal portion, The first end of the second support member is connected to the rotatable support structure, and the second end of the second support member is connected to the azimuth reflector, The elevation reflector is configured to have a first deployed position and a first retracted position, wherein in the first retracted position, the offset portion of the first support member is configured to position the elevation reflector next to the longitudinal portion of the first support member, and in the first retracted position, the arrangement of the elevation reflector is configured to minimize the height of the elevation reflector when it is retracted. Methods that include...

19. A single-degree-of-freedom tilted rotary drive device is operably coupled to the second support member, wherein the single-degree-of-freedom tilted rotary drive device is configured to rotate the second support member along the first end of the second support member to position the azimuth reflector coupled to the second end in a second storage position and a second deployed position, the second storage position of the azimuth reflector being configured to minimize the height of the azimuth reflector when it is stored. The method according to claim 18, further comprising:

20. The rotatable support structure is operably coupled to a movable structure, wherein the movable structure is configured to have a recessed area sized to receive the elevation reflector and the first support member when the elevation reflector and the first support member are in the first storage position. The method according to claim 19, further comprising:

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