Abstract: Embodiments of the present disclosure relate to a UAV comprising a fuselage, a rotor, and a patch antenna element. The patch antenna element, which is provided from a patch antenna stack-up, is conformally disposed on an outer surface of the UAV's fuselage. The patch antenna comprises a first substrate, patch conductor, intermediate substrate, bottom substrate, and ground plane. The patch conductor is disposed on a top surface of the first substrate. A first surface of the intermediate substrate, which is a magneto-dielectric material, is disposed on a bottom surface of the first substrate. A top surface of the bottom substrate is disposed on a second surface of the intermediate substrate. A ground plane conductor is disposed on a bottom surface of the bottom substrate.

Abstract: Systems and methods in accordance with various embodiments of the present disclosure provide high efficiency synthetic aperture radar satellite designs that achieve higher power efficiency and higher antenna aperture size to satellite mass ratios than the current state of the art. In various embodiments, a high efficiency synthetic aperture radar satellite includes a satellite bus and a parabolic reflector antenna coupled to the satellite bus. The satellite system may further include a traveling wave tube amplifier configured to drive the parabolic reflector antenna, and a body-mounted steering system configured to mechanically steer the satellite system to direct the parabolic reflector antenna. The satellite system may further include a processor configured to combine the pulse reflections and generate image data representing the region of interest, in which the image data is effectively obtained with a synthetic aperture greater than the actual antenna aperture.

Abstract: An antenna and radome assembly has an adapter plate engaging a first fitting configuration mounted to an aircraft fuselage. The adapter plate mechanically supports an antenna assembly wherein the antenna assembly is originally configured for a second fitting configuration. A radome is attached to the adapter plate enclosing the antenna assembly. The adapter plate has at least a nose portion providing reactive structure adapted to transform a longitudinal load on the radome into an induced downward vertical deflection.

Abstract: Improved designs for an antenna system that facilitates narrowband and wideband radio frequency (RF) communications in a rotary aircraft are disclosed. The antenna system includes a RF front-end and a RF back-end. The front-end includes multiple RF components structured to transmit or receive RF communications as electromagnetic waves into three-dimensional space. These RF components form parts of at least one of the aircraft's rotor blades. Moreover, some of the RF components are of differing types, thereby causing the rotor blade to include multiple different types of RF components. The back-end, on the other hand, is located at a position other than the rotor blades and is connected with the front-end via the aircraft's rotary hub, which is connected to the rotor blades.

Abstract: A satellite communication system for an aircraft communicates with multiple satellite constellations. The communication system includes a phased array antenna system and a transceiver. The transceiver is configured to communicate with a number of satellite constellations and configured to support simultaneously links to two or more constellations via the phased array antenna system. The satellite constellations can be micro-satellite, MEO, LEO, and GEO constellations.

Abstract: A support device for a radio equipment of an aircraft, radio system and aircraft are provided. The support device includes a fastening structure (31), intended to be secured to a lower surface of a fuselage of an aircraft, and a support platform (33) of the radio equipment (25). The support platform (33) is mounted pivoting on the fastening structure (31) around a pivot axis (A) between an operational position and a backup position. The support device comprises a locking mechanism (56), able to be actuated from a locked configuration, in which said locking mechanism (56) keeps the support platform (33) in its operational position while preventing any pivoting of the support platform (33), to an unlocked configuration, in which the locking mechanism (56) allows the support platform (33) to pivot relative to the fastening structure (31).

Abstract: A remote radio unit, which includes a housing, a ventilation air channel, and a circuit component, where the housing is a sealed hollow cavity; the ventilation air channel passes through the housing, a top end of the ventilation air channel is connected to a top end surface of the housing in a sealed manner, and a bottom end of the ventilation air channel is connected to a bottom end surface of the housing in a sealed manner; and the circuit component is disposed inside the cavity, and is in contact with an external surface of a side wall of the ventilation air channel, so that heat generated by the circuit component is dissipated through the ventilation air channel.

Abstract: A reduced radar cross section (RCS) antenna does not require housing the antennas in a radar-mitigating radome. Elements of the antenna are made from, or include, frequency selective surfaces that reduce reflection of radar or other signals. In some embodiments, the frequency selective surfaces are electrically tunable, thereby enabling a user or system to dynamically adjust the frequency or frequencies that are mitigated.

Abstract: Disclosed is a wing leading edge antenna system (“WLEAS”). The WLEAS includes an upper leading edge (“LE”) of a wing of an aircraft, a two-dimensional non-gimbaled scannable antenna (“2D-NGSA”), and an adapter plate. The upper LE of the wing includes two LE ribs and a LE cavity formed by the two LE ribs and a lower LE surface of the wing and the adapter plate is attached to both of the LE ribs within the LE cavity. Moreover, the 2D-NGSA is attached to the adapter plate within the LE cavity.

Abstract: A wireless communication device includes a reflecting plate having a reflecting surface that reflects electromagnetic wave, a radome covering the reflecting plate so as to form an airflow path between the radome and the reflecting surface, and including an air inlet and an air outlet communicating with the airflow path, an array antenna provided on the reflecting surface and inside the airflow path, and including a plurality of antenna elements aligned on the reflecting surface with an interval from each other, and a communication circuit that transmits and receives a wireless signal by exciting the array antenna. The plurality of antenna elements each include an antenna pattern formed on a plate-shaped dielectric substrate extending from the reflecting surface in a direction orthogonal thereto. Dissipation effect of heat from the communication circuit can be improved, by causing air convection in the airflow path in the radome.

Abstract: An antenna system having reduced back radiation is disclosed. The antenna system includes an antenna and ground plane. The antenna includes electro-textiles and is configured to operate in at least the frequency range between 1.1-1.6 GHz. The ground plane includes electro-textiles and is configured to operate as a frequency selective surface with electronic band gap characteristics to suppress edge and curved surface diffraction effects. In this system, the antenna and ground plane are configured to be located on a curved surface and to radiate with a directional radiation pattern having attenuated back lobes.

Abstract: Core structures (120) for composite panels (75) of an aircraft (10), composite panels (75) and aircraft (10) including the core structures (120), and methods (200) of manufacturing the composite panels (75) are disclosed herein. The core structures (120) include a first side (140), a second side (150), and a connecting region (160) that interconnects an upper portion (142) of the first side (140) with an upper portion (152) of the second side (150). The first side (140), the second side (150), and the connecting region (160) at least partially define an antenna housing (62), which defines a housing volume (64) configured to contain an aircraft antenna (60) of the aircraft (10), and an electromagnetic wave transmission region (66) configured to permit electromagnetic waves to pass therethrough.

Abstract: An omni-directional antenna using a rotator is disclosed. The omni-directional antenna is installed on the rotator having at least one rotation blade, and includes an antenna carrier unit disposed on at least one of top and bottom surfaces of the blade, and an antenna pattern unit formed on the antenna carrier unit.

Abstract: The present invention provides an over the air, OTA, power sensor (1, 20, 50) for measuring power of a wireless signal (2, 21) with at least two different polarizations, the OTA power sensor (1, 20, 50) comprising a first power sensor (3, 4, 22, 23, 51, 52) for every polarization, every power sensor comprising a signal detector (5, 6, 25, 26, 27) for detecting the wireless signal (2, 21), wherein the signal detectors (5, 6, 25, 26, 27) are single polarized and wherein the polarization planes (7, 8, 28-30) of the signal detectors (5, 6, 25, 26, 27) are arranged at an angle of more than zero degree to each other and wherein the main radiation vectors (9, 10, 31-33) of the signal detectors (5, 6, 25, 26, 27) are parallel to each other, and the first power sensors (3, 4, 22, 23, 51, 52) each comprising a power measurement device (11, 12, 43-45), which is configured to measure the power of the detected wireless signal (2, 21) and output a respective measurement signal (13, 14, 46-48, 55-58).

Abstract: An antenna assembly including a support and antenna tiles disposed in the support. The antenna tiles form an external surface corresponding substantially in shape to lateral faces of a frustum. The frustum includes a central axis with the antenna tiles disposed around the central axis of the frustum and sloping away therefrom. Each antenna tile includes opposite ends, with one end narrower than the other end. A planar array of antenna elements is disposed on each antenna tile in which the antenna elements of each array are configured to operate as a phased array. A control system connects to the planar arrays of antenna elements in which the control system is configured to selectively activate and deactivate each of the planar arrays.

Abstract: Disclosed is the networking of the radar in manners and operating utilizing methods that result in increases in the radar coverage by adding to the possible collection of locations and thus potentially increasing the data to be analyzed—ultimately increasing the accuracy of the readings.

Abstract: An antenna device is provided. The antenna device includes an antenna part, a motor and a case. The antenna part has a transmission antenna configured to transmit a radio wave and a reception antenna disposed on one of an upper side and a lower side of the transmission antenna and configured to receive a radio wave. The motor rotates the antenna part. The case covers the antenna part. The case has a side wall. The side wall has two inclined portions inclined at different inclination angles with respect to a rotational axis of the antenna part. A boundary between the two inclined portions is located higher than half of a height of the case.

Abstract: A structural panel of an aircraft is constructed with a multiphase antenna embedded inside the structural panel between multiple sheets of fiberglass.

Abstract: A method for determining location information for an airborne target includes synthesizing a cyclic transmit signal, transmitting an electromagnetic beam corresponding to the cyclic transmit signal, providing a plurality of vertically offset return signals corresponding to at least two receive antennas that are vertically offset, down-converting the plurality of vertically offset return signals with the cyclic transmit signal to provide a corresponding plurality of baseband signals, determining magnitude and phase information for each vertically offset return signal as a function of range from the corresponding baseband signal, and determining elevation information for an airborne target from the magnitude and phase information. Azimuthal information for the airborne target may be determined by tracking amplitude variations in the return signal in response to azimuthal rotation of the receive antennas. A corresponding apparatus, system, and computer readable medium are also disclosed herein.

Abstract: A remote radio unit, which includes a housing, a ventilation air channel, and a circuit component, where the housing is a sealed hollow cavity; the ventilation air channel passes through the housing, a top end of the ventilation air channel is connected to a top end surface of the housing in a sealed manner, and a bottom end of the ventilation air channel is connected to a bottom end surface of the housing in a sealed manner; and the circuit component is disposed inside the cavity, and is in contact with an external surface of a side wall of the ventilation air channel, so that heat generated by the circuit component is dissipated through the ventilation air channel.

Abstract: Wireless wearable devices having self-steering antennas are disclosed. A disclosed example wearable device includes an antenna to be communicatively coupled to a wireless data transceiver of a base station. The disclosed example wearable device also includes a steering mount coupled to the antenna, where the steering mount is to adjust an orientation of the antenna towards a wireless coverage zone associated with the wireless data transceiver based on a movement of the wearable device.

Abstract: Example methods and systems for adjusting the beam width of radio frequency (RF) signals for purposes of balloon-to-ground communication are described.

Abstract: A control unit of an aircraft includes a computer that predicts the current position of a wingman aircraft based on a temporal change in wingman-aircraft position information indicating the position of the wingman aircraft; an antenna selector that selects, from among multiple antennas, an antenna with which the elongation ?t with respect to the center axis of the antenna at the predicted current position of the wingman aircraft predicted by the computer falls within a coverage angle ?; and a beam controller that executes communication with the wingman aircraft via the antenna selected by the antenna selector. Thus, the control unit of the aircraft can select an optimal antenna for communication with the wingman aircraft from among the multiple antennas.

Abstract: A method and apparatus for retrofitting an aircraft. Connection points for a reinforcement structure are located. The reinforcement structure is associated with the airframe during original manufacturing of the aircraft and accommodates forces from an antenna system attached to the reinforcement structure. The antenna system includes an antenna selected from a plurality of types of antennas. An antenna adapter plate in the antenna system is attached to the reinforcement structure connected to the airframe of the aircraft during the original manufacturing of the aircraft using the connection points. The antenna is attached to the antenna adapter plate, wherein the antenna adapter plate is configured to receive any one of the plurality of types of antennas. The reinforcement structure is configured to handle loads from any one of the plurality of types of antennas and the antenna adapter plate attached to the connection points.

Abstract: An antenna system having reduced back radiation is disclosed. The antenna system includes an antenna and ground plane. The antenna includes electro-textiles and is configured to operate in at least the frequency range between 1.1-1.6 GHz. The ground plane includes electro-textiles and is configured to operate as a frequency selective surface with electronic band gap characteristics to suppress edge and curved surface diffraction effects. In this system, the antenna and ground plane are configured to be located on a curved surface and to radiate with a directional radiation pattern having attenuated back lobes.

Abstract: In one embodiment, an antenna system is described. The antenna system includes a primary antenna on an aircraft. The primary antenna is mechanically steerable and has an asymmetric antenna beam pattern with a narrow beamwidth axis and a wide beamwidth axis at boresight. The antenna system also includes a secondary antenna on the aircraft, the secondary antenna including an array of antenna elements. The antenna system also includes an antenna selection system to control communication of a signal between the aircraft and a target satellite via the primary antenna and the secondary antenna. The antenna selection system switches communication of the signal from the primary antenna to the secondary antenna when an amount of interference with an adjacent satellite reaches a threshold due to the wide beamwidth axis of the asymmetric antenna beam pattern.

Abstract: Apparatuses and methods are provided including radome designs with tailorable through thickness reinforcement (TTR) or transverse members that increase mechanical durability of the reinforced radomes against an applied forces while providing desired radar transmissive performance matched to a particular environment. Embodiments provided allow for greater mechanical durability while maintaining sensitive RF performance across the entire structure. TTR in the embodiments include composite rods, fibers, fiber bundles, tows, or a combination of these options. The TTR can be placed through the core or both the skins and the core, and the TTR can be continuous threads of materials.

Abstract: An aspect includes a method of kinematic motion planning includes accessing a list of a plurality of nodes defining a plurality of potential kinematic path locations between a starting position and an ending position of a vehicle. A plurality of constraint sets is determined that apply one or more vehicle motion constraints based on a plurality of spatial regions defined between the starting position and the ending position. The constraint sets are applied in determining a plurality of connections between the nodes to form a kinematic motion path based on locations of the nodes relative to the spatial regions. The kinematic motion path is output to a dynamic path planner to complete creation of a motion path plan for the vehicle.

Abstract: An antenna array includes a plurality of ½ flared notch radiators recessed within a missile nose cone and positioned in a circumferential arrangement around and extending radially from the payload's metal skin to contact an annular metal cover that provides a ground plane such that each ½ flared notch radiator is inclined towards the boresight axis. The payload's metal skin provides an image plane for each ½ flared notch radiator to launch RF energy with a radial polarization normal to the image plane forward through the annular RF radome. Each ½ flared notch radiator may be positioned within a 5½ sided waveguide to further improve directionality and isolation.

Abstract: A spacecraft communications payload includes a beam forming network (BFN), wherein the BFN includes a first feed waveguide and a first set of branch waveguides, each branch waveguide in the first set operating in a frequency band having a characteristic waveguide wavelength ?g1. A proximal portion of the first set of branch waveguides is communicatively coupled with the first feed waveguide. A distal portion of the first set of branch waveguides is communicatively coupled by way of an array of slots with a plurality of radiating elements. A separation distance between adjacent slots in the array is approximately equal to ?g, and the array of slots is configured as a honeycomb-like triaxial lattice. In some implementations, a compact BFN may be configured to simultaneously operate at two different polarizations (“dual-polarized”) and/or frequency bands (“dual-band”).

Abstract: Antenna systems and methods employing an axial metallic corrugated choke ring attached to an offset reflector assembly and circumscribing (without contacting) a stationary metallic conical feed horn.

Abstract: Various embodiments of a millimeter-wave antenna system configured to enhance the gain in a communication network, in which one or more slotted wave-guides produce radiating slot structures that form accurate high-gain millimeter-wave radiation patterns. The system comprises one or more slotted wave-guides to transport millimeter-waves, a PCB including a substrate lamina and an electrically-conductive lamina with two or more highly accurate slots, and an electrically-conductive metal cover that intersects the electrically-conductive lamina to form an enclosed wave-guide cavity. Various embodiments of methods for producing the millimeter-wave antenna system, including different techniques for creating the accuracy of the slots in the slotted wave-guides.

Abstract: An antenna electromagnetic radiation steering system may include an antenna for emitting electromagnetic radiation, and a radome disposed adjacent to and at least partially enclosing the antenna, the radome including a window to pass electromagnetic radiation from the antenna to outside the radome, wherein electromagnetic radiation is directed based on a position of the window relative to the antenna.

Abstract: Various embodiments of the present invention include assemblies and methods for utilizing antennas with high gain in small satellites. In one embodiment, a satellite comprising a payload configured for transmitting data is provided. The payload may include various components of the satellite, such as the attitude control system, electrical power system, and/or communication system. The satellite may be configured to communicate with one or more ground stations. The satellite includes a support structure comprising at least one deployable panel, wherein the support structure houses the payload. The satellite also includes at least one antenna coupled to the support structure, wherein the deployable panel is configured to cover the antenna in a non-deployed state and to expose the antenna in a deployed state.

Abstract: An antenna includes a planar ground plane, a planar exciter, and a plurality of passive elements. The planar ground plane and the planar exciter are disposed orthogonal to a longitudinal axis of the antenna. The planar exciter is spaced apart from the ground plane. The planar exciter is configured to excite right-hand circularly-polarized electromagnetic radiation. The planar exciter is configured to excite first currents orthogonal to the longitudinal axis and substantially no current parallel to the longitudinal axis. The plurality of passive elements is symmetrically disposed azimuthally about the longitudinal axis and spaced apart from the planar exciter. The plurality of passive elements is electromagnetically coupled to the planar exciter. The plurality of passive elements is configured to excite second currents parallel to the longitudinal axis and third currents orthogonal to the longitudinal axis.

Abstract: This disclosure is directed to broadband polarization diversity antennas. In one aspect, a polarization diversity antenna includes a baseboard with a baseboard-feed line located on a first surface. The baseboard-feed line includes a serpentine meander-line portion. The antenna also includes an antenna-array board with two or more antenna elements arranged in a series. The antenna-array board is attached to the first surface with the serpentine meander-line portion located between an edge of the antenna-array board and the baseboard. Each antenna element is connected to the serpentine meander-line portion via an antenna-feed line located on the antenna-array board. The antenna array provides two dimensional polarization broadcasting and receiving of electromagnetic radiation. In another aspect, a notch antenna is formed on an opposing second surface of the baseboard opposite the antenna-array board in order to provide three-dimensional polarization broadcasting and receiver of electromagnetic radiation.

Abstract: An airframe component is provided and includes first and second components having respective first and second opposite surfaces and edge portions, the first component defining a plane and the second component being attachable to the first surface of the first component as a protrusion from the plane, a first conductive layer disposed to wrap around the edge portion of the first component from the first surface to the second surface, a second conductive layer disposed on the first surface of the second component to extend beyond the edge portion and an insulation layer interposable between the first and second conductive layers and between a periphery of the first surface of the second component and the second conductive layer.

Abstract: An antenna cover of an aircraft including: a cover that protects an antenna mounted in the aircraft; a conductive layer having conductivity that is provided on an outer side of the cover; and a rain erosion boot that covers one region of the conductive layer, wherein the rain erosion boot includes a main material having an insulating property, is given conductivity, and is grounded to an airframe via the conductive layer, or the rain erosion boot includes a main material having an insulating property, and is given hydrophilicity.

Abstract: A multi-band blade antenna with an open sleeve and slanted design housed within a blade antenna housing. The blade antenna has three resonant bands with one very high frequency (VHF) band and two ultra-high frequency (UHF) bands.

Abstract: An integrated, externally-mounted Automated Dependent Surveillance-Broadcast (ADS-B) device comprising in one embodiment a 1030 MHz transmitter, a 1030 MHz antenna, a 1090 MHz receiver, a 1090 MHz antenna, a GNSS receiver, at least one GNSS antenna, a 978 MHz transmitter, and a 978 MHz antenna, wherein these components are integrated into a single enclosure, and wherein the GNSS antenna is placed at least partially into a projection extending out from the main enclosure body, such that the GNSS antenna has improved visibility to GNSS signals originating from altitudes above the current altitude of aircraft when the ADS-B device is mounted on the bottom of an aircraft.

Abstract: An antenna assembly for aircraft including: a vertical tail of the aircraft including a front spar, a leading edge skin covering a leading portion of the front spar and a rib extended between the front spar and the leading edge skin; an antenna radiating element extending a length of the vertical tail and positioned between the leading edge skin and the front spar; a first metallic element included with or attached to the front spar; a second metallic element, wherein the second metallical element is electrically coupled to the antenna radiating element and to the first metallic element; an antenna coupler in electrical electrically connected to the antenna radiating element and the first metallic element, and wherein a closed looped electrical circuit is formed by the antenna radiating element, the first metallic element, the second metallic element and the antenna coupler.

Abstract: A radome includes a shell defining an internal volume. A track is coupled to the shell, and the track allows the shell to move axially between an open position and a closed position. A support structure is coupled to the shell, and the support structure moves from a collapsed position to an expanded position.

Abstract: An antenna system includes a dual-polarized antenna, a main reflector, and an auxiliary reflector. The dual-polarized antenna includes a first antenna element and a second antenna element. The first antenna element and the second antenna element operate in a low-frequency band and a high-frequency band. The first antenna element and the second antenna element have different polarization directions. The main reflector is configured to reflect the electromagnetic waves in the low-frequency band. The auxiliary reflector is positioned between the dual-polarized antenna and the main reflector, and is configured to reflect the electromagnetic waves in the high-frequency band.

Abstract: A fin-shaped multi-band antenna module, e.g., for vehicles, includes an antenna printed circuit board and a plate arranged thereupon. In a lower region the plate is mechanically connected to the antenna printed circuit board. A first monopole extends in an essentially vertical direction on the plate and is connected to the antenna printed circuit board in a lower region by a feed point. The first monopole is inductively extended in the vertical direction in an upper region of the first monopole in order to enable transmission and reception of electromagnetic waves in a lower telephone frequency range.

Abstract: An antenna system having a transmit assembly with a first set of antenna elements for transmitting signals. Each antenna element in this first set may be disposed from a respective adjacent antenna element by a predetermined azimuthal increment and by a predetermined altitudinal increment. The antenna system further includes a receive assembly having a second set of antenna elements for receiving signals. Each antenna element in this second set may be disposed from a respective adjacent antenna element by a predetermined azimuthal increment and by a predetermined altitudinal increment. The predetermined azimuthal and altitudinal increments of the first set may be substantially similar to the predetermined azimuthal and altitudinal increments, respectively, of the second set.

Abstract: An antenna includes a conductive antenna body having first and second opposing ends with an enlarged width medial portion therebetween. A slot extends from at least adjacent the first end to at least adjacent the second end, and first antenna feed points are adjacent the slot for a first polarization. A conductive antenna member is adjacent the second end of the conductive antenna body and has a planar shape and a second antenna feed point for a second polarization.

Abstract: A phased array antenna for a mobile platform combines transmit and receive antennas within a common, low profile enclosure. Transmit and receive functions, a power supply, up and down frequency converters, and an antenna controller are integrated into closely packaged layers within the enclosure.

Abstract: An apparatus (e.g., a communication assembly) includes a waveform detector operable to detect a waveform. The apparatus also includes a membrane encircling the waveform detector. The membrane has a first portion that is at least partially transparent to the waveform and has a second portion that is at least partially reflective of the waveform. The apparatus also includes a support member coupled to the waveform detector. The support member is configured to moveably support the waveform detector within the membrane at a location that enables the waveform detector to detect a portion of the waveform that is reflected by the second portion of the membrane.

Abstract: According to some embodiments, an unmanned vehicle includes a power supply configured to supply an electrical power signal to a motor for propelling the unmanned vehicle, a wireless communication device configured to transmit or receive a radio frequency (RF) signal, and a motor feed antenna coupled to the power supply and the wireless communication device, the motor feed antenna configured to conduct the electrical power signal from the power supply to the motor, and to transmit or receive RF signals as an antenna for the wireless communication device.

Abstract: The present invention is directed to a tool having a wrist mechanism that provides pitch and yaw rotation in such a way that the tool has no singularity in roll, pitch, and yaw. A positively positionable multi-disk wrist mechanism includes a plurality of disks or vertebrae stacked in series. Each vertebra is configured to rotate in pitch or in yaw with respect to each neighboring vertebra. Actuation cables are used to manipulate and control movement of the vertebrae. In specific embodiments, some of the cables are distal cables that extend from a proximal vertebra through one or more intermediate vertebrae to a distal vertebra, while the remaining cables are medial cables that extend from the proximal vertebra to one or more of the intermediate vertebrae. The cables are actuated by a pivoted plate cable actuator mechanism.