Abstract: Unmanned aerial vehicles including wing capture devices and related methods are disclosed. An example unmanned aerial vehicle includes a fuselage and a wing assembly, the wing assembly including a shoulder coupled to the fuselage, the shoulder including a joint, the joint distal to the fuselage, a wing coupled to the joint, and a hook, the hook coupled to the shoulder, the hook including a groove to receive a cable to arrest flight of the unmanned aerial vehicle.

Abstract: An underwater communications system is provided that transmits electromagnetic and/or magnetic signals to a remote receiver. The transmitter includes a data input. A digital data compressor compresses data to be transmitted. A modulator modulates compressed data onto a carrier signal. An electrically insulated, magnetic coupled antenna transmits the compressed, modulated signals. The receiver that has an electrically insulated, magnetic coupled antenna for receiving a compressed, modulated signal. A demodulator is provided for demodulating the signal to reveal compressed data. A de-compressor de-compresses the data. An appropriate human interface is provided to present transmitted data into text/audio/visible form. Similarly, the transmit system comprises appropriate audio/visual/text entry mechanisms.

Abstract: Methods, systems, and devices for wireless communications are described. A first wireless device may receive, from a second wireless device and over a plurality of different beams, a set of reference signals as part of a beam management procedure. The first wireless device may select one or more bit values for indicating to the second wireless device a corresponding one or more individual beams of the plurality of different beams for communications between the first wireless device and the second wireless device, the one or more bit values selected based on a distribution of probabilities for switching between the plurality of different beams for the communications between the first wireless device and the second wireless device. The first wireless device may transmit control signaling indicating a ranking of the one or more individual beams for the communications between the first wireless device and the second wireless device.

Abstract: An antenna module is provided. According to an aspect of the present disclosure, an antenna module attached to a support surface provided in a vehicle radar sensor to transmit and receive radio waves may include an antenna body in which one surface is stacked on the support surface; a through path formed inside the antenna body and extending in one direction; at least one slot formed through the through path toward the other surface of the antenna body and extending in the one direction; and a first radio wave absorbing member extending in the one direction and disposed parallel to opposite sides of the through path.

Abstract: An integrated compact radio antenna system for receiving and transmitting 5G signals and receiving GNSS signals is described. The system comprises a high-precision GNSS antenna and a MIMO 5G multi-element antenna system. All the antennas within the proposed compact system are integrated with a shielded housing that enables electronic components of GNSS receiver and 5G modem to be arranged inside. The proposed integrated system has the following advantages: 1) compactness, 2) high efficiency of MIMO 5G antenna system, 3) a high degree of decoupling between 5G antennas, 4) a high degree of decoupling between 5G and GNSS antennas.

Abstract: An antenna apparatus is provided that allows cooling with a high heat dissipation effect even when the antenna apparatus is reduced in height. The antenna apparatus includes an antenna element, a mount on which the antenna element is provided, a radome to accommodate the antenna element, and a skirt provided on the mount. The mount on which the antenna element is provided has a side surface including a surface to which an inner circumferential surface of the radome is attached. A skirt provided on the mount has an outer circumferential surface on which a heat dissipation fin to dissipate heat to outside is formed. The heat is transmitted from the antenna element through the mount to the skirt.

Abstract: A radar device includes a radar base and a radar module. The radar module is mounted at the radar base and configured to rotate relative to the radar base around a rotation axis. The radar module includes an antenna assembly, a signal processing circuit board, and a rotation installation base. The antenna assembly and the signal processing circuit board are arranged oppositely at an interval and jointly enclose to form an accommodation space. The rotation installation base is connected to the antenna assembly and the signal processing circuit board and is located in the accommodation space. The radar base is at least partially located in the accommodation space and arranged opposite to the rotation installation base.

Abstract: There is disclosed a missile comprising an outer skin, an electronics unit, and a thermal link between the electronics unit and the outer skin. The thermal link comprises a jumping drop vapour chamber arranged such that, when the outer skin is at an elevated temperature relative to the electronics unit, the electronics unit is thermally insulated from the outer skin; and such that, when the outer skin is at a lower temperature relative to the electronics unit, the electronics unit is thermally linked to the outer skin.

Abstract: An antenna assembly includes a plurality of active antenna elements disposed in a first linear array along a reference line and equidistant from each adjacent antenna element by a first linear distance, and a plurality of passive antenna elements disposed in a second linear array extending parallel to the reference line such that each passive antenna element is a second linear distance away from a corresponding one of the active antenna elements. The antenna assembly includes or is operably coupled to a phase control module configured to apply selected phase fronts to selected ones of the antenna elements to generate constructive and destructive interference patterns to define a directive beam in a desired direction in a range between about 0 and 180 degrees relative to the reference line.

Abstract: Disclosed is a method and apparatus for processing a radar signal by correcting a phase distortion. The method includes generating radar data based on a radar transmission signal transmitted through an array antenna of a radar sensor based on a frequency modulation model and a radar reception signal received through the array antenna as the radar transmission signal is reflected by a target, correcting the radar data using a correction vector for correcting a feedline error occurring due to a feedline delay difference between channels of the array antenna, and estimating a direction of arrival corresponding to the corrected radar data using a direction matrix reflecting a phase shift of the corrected radar data according to frequency modulation characteristics of the frequency modulation model.

Abstract: A filter component for an aircraft insert can include a non-conductive body having an outer surface and an inner surface. The inner surface can be configured to be hidden from view when installed on the insert. The filter component can include a surface filter disposed on the inner surface such that when the non-conductive body is installed on the insert the surface filter is not visible. The surface filter can be configured to filter out one or more predetermined filter frequencies.

Abstract: A vehicle communication system includes a network adaptor that communicates with a communication network, a communication interface that communicates with multiple vehicles via multiple satellites, each vehicle comprising an antenna system for coupling to the satellites. The vehicle communication system is configured receive route data of the vehicles, and, for each vehicle, determine a future position of the vehicle based on the route data; identify a satellite available for communications with the vehicle at the future position; predict whether an antenna blockage event will occur between the identified satellite and the antenna system of the vehicle at the future position; designate the identified satellite as having the antenna blockage event; and transmit instructions to the vehicle to not use the identified satellite.

Abstract: An avionics unit assembly for an aircraft can include an avionics unit (e.g., an underwater locator device, “ULD”), and a battery to power the avionics unit. The avionics unit assembly can further include a housing that encases the avionics unit and the battery. The housing includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit to a surface. A method integrating the avionics unit assembly onto a forward aircraft bulkhead at a mount location under an aircraft radome and for manufacturing the avionics unit, and an aircraft including the avionics unit are also described.

Abstract: A solar array structure, such as for a spacecraft, uses thin solar array panels that, when in a stowed configuration, are stiffened by being bent or curved in one direction to be shaped like a section of a cylinder and placed within a rigid structural frame. As a curved solar panel is not as efficient as a flat panel directly facing the sun, the solar array panels are curved in their stowed configuration for launch only, but flatten after deployment by use of a partially flexible structural frame, where a rectangular frame is made of two opposing rigid sides and two opposing flexible sides, with a thin flexible solar panel attached to rigid sides only. The rigid sides are compressed during stowage to curve the panel before hold-down tensioning. The structure and panels return to their flat free state configuration after release.

Abstract: Phased array antennas, such as a multi-function aperture, are limited in performance and reliability by traditional air-cooled thermal management systems. A fuel-cooled multi-function aperture passes engine fuel through heat exchangers that surround the multi-function aperture to provide better heat transfer than can be achieved through air cooling systems. The increased heat transfer and thermal management results in a multi-function aperture with improved performance and reliability.

Abstract: A beam search method using an active phased array antenna, in which the beam search method uses a single tile-type phased array antenna including a plurality of radiating elements arranged in a matrix form, and the phased array antenna includes a plurality of sub-arrays including the plurality of radiating elements and arranged in one direction, includes: calculating a beam coefficient application vector for each of the sub-arrays by using a received signal for each of the sub-arrays and a beam coefficient for each of the sub-arrays; determining, as an initial value, a beam coefficient of an effective sub-array corresponding to a maximum value from among absolute values of beam coefficient application vectors for each of the sub-arrays; and performing a monopulse algorithm based on the initial value, to obtain an extended beamwidth greater than a reference beamwidth, which is a range of a beam detected by the phased array antenna.

Abstract: The disclosed systems, structures, and methods are directed to antennas for integration with a display structure which has a plurality of pixels arranged in pixel rows with an inter-pixel spacing, and a feeding line located in the inter-pixel spacing. The display structure also has an antenna which comprises a slotted waveguide and a substrate. The slotted waveguide is located in the inter-pixel spacing and defines a plurality of slots configured to radiate electromagnetic waves. The substrate is attached to the slotted waveguide and is located between the feeding line and the slotted waveguide. The antenna may also include a plurality of slotted waveguides superposing on different feeding lines of the display structure.

Abstract: A satellite dispenser and method of using same are disclosed. In various embodiments, a satellite dispenser as disclosed herein includes a dispenser body defining an interior cavity to accommodate a payload; and a plurality of externally adjustable restraints positioned within the interior cavity and configured to be extended further into the interior cavity by actuation of a manual interface external to the interior cavity.

Abstract: A system and method for applying an adaptive adjustment or taper to an electronically scanned array (ESA) weather radar based on feedback from the weather radar. To minimize ground clutter and enable the ESA to display hazardous weather phenomena, the system adaptively adjusts amplitude and phase of ESA elements to adjust the far field pattern shape and sidelobes to maintain a desirable signal to clutter ratio. The system identifies ground clutter as a strong ground return over several azimuths depending on the radar beamwidth. Once the system IDs the ground clutter, it adaptively adjusts on receive for for the upcoming azimuths. The system selectively suppresses sidelobe echoes while maintaining the signal to noise (SNR) for weather targets. The system adaptively adjusts in real time as well as adjusting using precomputed historically accurate tapers stored in memory.

Abstract: A method for inspecting a joining surface (14) of a substrate, wherein a component is to be adhered to the joining surface of the substrate by means of an adhesive material (27), wherein the method comprises the following steps: •—providing at least one planar test textile (20), which has a fiber material (21) and an adhesive primer (22), •—applying the planar test textile to at least one part of the joining surface of the substrate to which the component is to be adhered so that the adhesive primer of the planar test textile contacts the joining surface of the substrate, •—at least partially curing the adhesive primer of the planar test textile in order to integrally bond the planar test textile to the substrate by means of the adhesive primer, •—pulling off the planar test textile after at least partially curing the adhesive primer and inspecting the joining surface by means of a qualitative evaluation of the fracture pattern between the cured adhesive primer and the planar test textile and/or by means of a

Abstract: An antenna that comprises a dielectric body and a feed arrangement. The dielectric body includes a first portion operable as a dielectric lens and a second portion operable as a dielectric resonator. The feed arrangement is operably coupled with the dielectric body for operating the antenna as a dielectric lens antenna and a dielectric resonator antenna.

Abstract: An aircraft comprising a skin, a multiplicity of antenna arrangements, each of which is arranged in a different region of a corresponding multiplicity of mutually spaced regions of the skin and comprises an antenna element that is arranged and configured to emit radio waves into a surrounding area of the aircraft, and a multiplicity of visual indicators, each of which is assigned to a different antenna arrangement of the antenna arrangements. Each of the visual indicators is arranged on the skin or on the antenna arrangement in the region of the skin in which the assigned antenna arrangement is situated in such a manner that it is visible from outside the aircraft and emits light during operation in an on state.

Abstract: A heatsink shield with thermal-contact dimples can improve thermal-energy distribution in a radar assembly. The radar assembly includes a printed circuit board (PCB), the heatsink shield, a radome, and a housing. The PCB can include integrated circuits and other components, along with a thermally-conductive material that covers at least a portion of the PCB surfaces. The heatsink shield includes multiple dimples that thermally contact the thermally-conductive material. The heatsink shield is configured to distribute thermal energy produced at least in part by the PCB components to the housing. In this way, the described techniques and systems permit the radar assembly to better distribute thermal energy away from the PCB components to the rest of the PCB and through the housing.

Abstract: Methods, computer program products, and systems are presented. The method computer program products, and systems can include, for instance: examining one or more parameter characterizing a prospective connection of the mobile airborne article to first through Nth base stations, the one or more parameter including a Doppler shift; determining based on the examining that a criterion is satisfied, the criterion having one or more factor; and initiating handoff of the mobile airborne article to one of the first through Nth base stations based on the determining.

Abstract: An electronic device which includes a radome, a bottom cover connected to the radome, and a printed circuit board disposed between the radome and the bottom cover. The radome includes a top shell, an insulating member and at least one fastening members. The insulating member is made of expanded polystyrene and has at least one recess. The fastening member is embedded in the insulating member. The top shell covers the insulating member and includes polycarbonate.

Abstract: In examples, systems and methods for direction finding of electromagnetic signals are described. The device includes a first antenna configured to receive electromagnetic energy. The device also includes a second antenna configured to separately receive the same electromagnetic energy. The device further includes a radome located in a receiving pathway of the first antenna, where the radome is configured to cause a predetermined phase shift that varies based on an angular position of the receiving pathway. The device includes 1 or more radio receivers to receive the signals independently from the antennas. Additionally, the direction finding device includes a processor configured to determine an angle of arrival of the electromagnetic energy based on a comparison of a phase of the electromagnetic energy received by the first antenna to a phase of the electromagnetic energy received by the second antenna.

Abstract: An aircraft with an aircraft structure that comprises a radome cover opening kinematic and a radome cover shell that is adapted to enclose equipment in a nose region of the aircraft in a closed position. The radome cover opening kinematic may enable movements of the radome cover shell between the closed position and an opened position and vice versa. The radome cover opening kinematic may include a guiding rail that is attached to the radome cover shell, and at least three rollers that are attached to the aircraft structure, wherein a first and a second roller are arranged on opposing sides of the guiding rail, and wherein the second and a third roller are arranged on the same side of the guiding rail.

Abstract: In the present invention a guide or carrier is used to assemble and position multiple AiPs (or Integrated Circuit packages) on a substrate and maintain spacing therebetween. In some examples, this reduces package size and maintains desired tolerances. The carrier or guard is to be thin and flexible so as to allow some movement but maintain tolerances at specific locations.

Abstract: A system of high-frequency (HF) antennas is disposed on various aircraft body panels. The antennas are configured for orthogonal polarization such that NVIS may be operable no matter the state of the ionosphere. The antennas are disposed on substantially perpendicular body panels so that, when operated in concert, the resulting signals have opposite polarization and at least one signal will bounce off the ionosphere.

Abstract: A pressure bulkhead for the pressure-tight axial closure of a pressurized fuselage of an aircraft or spacecraft that can be put under an internal pressure, comprises a pressure dome, which is designed with a concave inner surface and a convex outer surface; inspection hatches, which each form an aperture in the pressure dome from the inner surface to the outer surface; and pressure covers for pressure-tight closure of the inspection hatches, wherein the pressure covers each have a cover and a pressure seal, wherein the cover is designed for the repeatedly releasable fixing of the pressure cover on the concave inner surface over the inspection hatch and wherein the pressure seal is formed at the edge of the cover for the pressure-tight closure of the cover with the pressure dome.

Abstract: An additive manufacturing apparatus configured to produce a component layer by layer. The manufacturing apparatus includes a support structure, a stage that is positioned opposite the support structure. The stage is configured to hold a stacked arrangement of one or more cured layers of a resin. The apparatus also includes one or more actuators operable to move the stage away from the support structure, and a radiant energy apparatus is positioned opposite the stage such that the support structure is positioned between the radiant energy apparatus and the stage. The radiant energy apparatus is operable to generate and project radiant energy through the support structure on the resin in a predetermined pattern. a foil separation device that includes at least one holddown device is configured such that the foil contacts the at least one holddown device as the stage is moved away from the support structure.

Abstract: An antenna apparatus comprising at least one antenna array configured to produce a beam to facilitate wireless communication with at least one other antenna apparatus is described, in which the beam can be electronically steered in an associated beamforming plane by beamforming circuitry. The at least one antenna array has an associated antenna array plane, and an antenna array rotation mechanism is configured to rotate each antenna array in its associated antenna array plane to cause its beamforming plane to rotate. Methods for operating such an antenna apparatus, and for deploying an antenna apparatus in a wireless communication network, are also described.

Abstract: An antenna system and method includes or uses a set of M antenna structures and a cross bar beam former. The analog (or digital) cross bar beam former includes a set of M N to 1 (M(N×1)) interfaces, each of the M N to 1 interfaces having a first line coupled to a respective one of the set of the M antenna structures. The cross bar beam former also includes a set of N 1 to M (N(1×M)) interfaces, each of the N 1 to M interfaces having a set of M second lines, each of the M second lines being coupled to a respective one of the M N to 1 interfaces. Each of the N 1 to M interfaces includes a third line for a respective one of N independent beams.

Abstract: An aircraft multi-purpose shoulder panel system having a shoulder panel insert is disclosed. The system features a circumferential base connected to the shoulder panel insert, an antenna compartment positioned on top of the circumferential base, and a removable antenna mounting plate positioned above, and connected to, the antenna compartment. The system also features an overall structure that provides unprecedented ruggedness, and enables aircraft antennae/sensor versatility, adaptability and reversibility.

Abstract: An end cover includes an end cover plane perpendicular to a longitudinal axis of a radome and passes through a connection part of the end cover and the radome. Outlines of a cross section of the end cover includes a first spline curve between a first end point and a first intermediate point having at least one first curvature, and a second spline curve between a second intermediate point and a third intermediate point having at least one second curvature. The first intermediate point and the second intermediate point are not in the end cover plane. A distance between the first intermediate point and the end cover plane and a distance between the second intermediate point and the end cover plane are equal and not less than a distance between any point on the cross section of the end cover and the end cover plane.

Abstract: An antenna includes at least one antenna element mounted on a substrate and extending normally thereto. The at least one antenna element is constructed from a plurality of antenna components, one of which is an upper antenna component that is furthest from the substrate. A support material surrounds the at least one antenna element and is disposed between the antenna components. A material layer is disposed on the upper antenna component and the support material. Heating elements may be interposed between the upper antenna component and the material layer, and an additional material layer, such as an ablative layer, may be disposed on the material layer.

Abstract: Aspects of the present disclosure provide wireless devices, apparatuses, methods, processing systems, and computer readable mediums for adapting inter-antenna element spacings. An example method generally includes activating a first subset of antenna elements from within a set of antenna elements, communicating with at least a second wireless device with the first subset of antenna elements activated, receiving feedback from at least the second wireless device, and activating a second subset of antenna elements from within the set of antenna elements, based on the feedback, wherein the second subset of antenna elements has at least one different inter-antenna element spacing than the first subset of antenna elements in at least one dimension.

Abstract: An antenna arrangement for an aircraft for fastening to an outer side of an exterior skin of the aircraft has a body and side wall sections and a connecting section. The body is U-shaped or H-shaped if viewed from a predefined direction and can be flowed through with a low aerodynamic drag by a flow along the predefined direction. The antenna arrangement has one or more antennas in the form of a printed circuit board and of which each is fastened to the body and is fastenable directly to the outer side of the aircraft exterior skin at two first edges of the side wall sections which form two free ends of the U-shape or H-shape on a first side of the connecting section or, for the U-shape, on the connecting section and/or regions of the side wall sections, which regions adjoin the connecting section directly as the predefined direction is parallel to the flow direction during flight.

Abstract: An aerial vehicle includes a body and an antenna assembly mounted to the body. The antenna assembly includes a fairing component comprising a hollow body, a conductive coating formed on at least an inner surface of the fairing component, a plurality of antenna elements formed in the conductive coating, each antenna element including a first slot line defining a first transmission line and a second slot line defining a second transmission line, an insulator sleeve disposed within the fairing component, wherein an outer surface of the insulator sleeve at least substantially matches an inner surface of the fairing component, and a plurality of cable assemblies operably coupled to the plurality of antenna elements, wherein each cable assembly is coupled to a respective antenna element.

Abstract: A hypersonic harmonic exciter system to enable hypersonic speed, including a hypersonic harmonic exciter body having a plurality angled sides forming exciter body hollow structure with an access aperture, vibration inducing wave apparatus configured to produce and project vibration harmonic waves that converge on a convergence harmonic point forward of the hypersonic harmonic exciter body, the vibration inducing wave apparatus having vibration apparatus hollow structure with a series of exterior concentrically positioned vibration inducing bands, the vibration inducing wave apparatus inserted in the exciter body hollow structure, and harmonic sound projecting apparatus configured to produce and project harmonic sound waves that converge on the convergence harmonic point forward of the hypersonic harmonic exciter body, the harmonic sound projecting apparatus having sound apparatus hollow structure with a series of exterior concentrically positioned sound emitter bands, the harmonic sound projecting apparatus i

Abstract: A small cell base station antenna includes a first backplane, a first linear array of radiating elements extending forwardly from the first backplane, a second backplane that is opposite the first backplane and a second linear array of radiating elements extending forwardly from the second backplane. The first backplane is inclined at a first oblique angle with respect to a vertical axis and the second backplane is inclined at a second oblique angle with respect to the vertical axis.

Abstract: An onboard sensor cover includes a cover body that includes front and rear bases and a decorative layer. The front base is made of a transparent plastic material that permits passage of an infrared ray and a millimeter wave and includes a rear surface in the transmission directions of the infrared ray and the millimeter wave that is configured by a first uneven surface. The rear base is made of a plastic material that permits passage of the infrared ray and the millimeter wave and includes a front surface in the transmission directions that is configured by a second uneven surface. The decorative layer is made of a material that reflects visible light and permits passage of the infrared ray and the millimeter wave and is in contact with the first and second uneven surfaces. The front and rear bases are made of the same type of plastic material.

Abstract: In one embodiment, a first antenna element has a substantially vertical axis. An array of second antenna elements is configured to radiate or receive an aggregate radially polarized electromagnetic signal component. The array defines a substantially horizontal plane that is generally orthogonal to the substantially vertical axis of the first antenna element. The aggregate radially polarized electromagnetic signal is derived from radially polarized electromagnetic signal components associated with corresponding ones of the second antenna elements. The aggregate radially polarized electromagnetic signal is derived from radially polarized electromagnetic signal components associated with corresponding ones of the second antenna elements.

Abstract: A system for detecting a vehicle includes a light source configured to emit a light signal. The system also includes a receiver sensor configured to receive a reflected light signal based at least in part on the light signal reflected from a plurality of reflectors. The system also includes a controller, the controller configured to identify an arrangement pattern of the plurality of reflectors based at least in part on the reflected light signal and determine that plurality of reflectors are coupled to another vehicle based at least in part on an identification of the arrangement pattern.

Abstract: An interface matrix arrangement for multi-beam, multi-port antenna is described.

Abstract: A device for launching an object is described. The device comprises a frame affixed to the launch pad, a push element for pushing an object detached from the launch pad, and a flexible force storing element for turning the push element in relation to the frame. The device has a casing fixed to the frame at a fixing point for holding the object in place against the push element. The device has a lock element for locking the casing in standby position. The frame and the push element are superposed and connected to each other at one edge of the device. The frame and the push element are substantially parallel. Force stored in the force storing element is releasable for displacing the push element at a moment of launch. The force storing element may be at least one spring or elastic band or an extension spring.

Abstract: An aircraft radar assembly (200) comprising: a radome (202); a radar antenna (100) housed within the radome (202), the radar antenna (100) having a surface for transmitting and/or receiving radar waves; and rotation means (204) configured to rotate the radar antenna (100) within the radome (202) about an axis of rotation (206); wherein the surface is oblique to the axis of rotation (206).

Abstract: An avionics unit assembly for an aircraft includes an avionics unit such as an underwater locator device (ULD) having a transmitter configured to output a radio frequency pulse and a battery configured to power the device. The avionics unit assembly can further include a housing that encases the transmitter and the battery and includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit assembly to a surface. The suppressor can include a plurality of channels, where each channel includes at least one blind alley that can capture/filter a particulate component and/or a liquid component from the emission and/or break up the particulate component.

Abstract: A system for mitigating radio frequency interference includes a multiple patch antenna array including a multiplicity of patch antenna elements. The multiple patch antenna array is positioned relative to an interfering antenna such that signals from the interfering antenna cause interference with the multiple patch antenna array. The system also includes an auxiliary antenna positioned relative to the multiple patch antenna array. The system additionally includes a device to generate a spatial null in a direction to the interfering antenna from the multiple patch antenna array in response to a first signal from the auxiliary antenna and a second signal from the multiple patch antenna array. The first signal and the second signal are generated in response to a transmitted signal being received by the auxiliary antenna and the multiple patch antenna array. The spatial null permits simultaneous operation of the multiple patch antenna array and the interfering antenna.

Abstract: In one embodiment, an antenna assembly is described. The antenna assembly includes an antenna and an antenna positioner coupled to the antenna. The antenna positioner includes a single drive interface and a plurality of gears. The plurality rotate in a first manner in response to a first drive direction applied through the single drive interface, and rotate in a second manner in response to a second drive applied through the single drive interface. The antenna positioner also includes a threaded rod that moves in a first rod direction and a second rod direction in response to rotation of the plurality of gears in the first manner and the second manner respectively. The antenna positioner also includes a tilt plate contacting the threaded rod. The tilt plate tilts about a pivot line in response to movement of the threaded rod to move a beam of the antenna in a spiral pattern.