Abstract: A contiguous radiating ring antenna structure suitable for a vehicle is disclosed. The antenna structure comprises a curved shape structure having a plurality of radiating rings, a plurality of sectors, a connecting unit, and a plurality of frequency barriers. The antenna structure has a phase variation of less than 2° degrees over 360° of azimuth coverage and about +/?85° of elevation coverage. The antenna structure has a thickness of less than 0.5 inches. The contiguous radiating ring antenna structure is design for demanding vehicular applications, including missiles, rockets, and aircraft. The contiguous radiating annular ring antenna comprises a beam forming network, which is configured to be incorporated into a printed antenna board for enhancing the vehicular communications.

Abstract: A UAV having a wireless-front end including propellers that are dual purposed to function as ground communication antenna elements. This design reduces weight and size of the UAV, hence enabling a compact design with the capability of handling a heavier payload.

Abstract: Multiband guiding structures for antennas and methods for using the same are described. In one embodiment, an antenna comprises: an antenna aperture with radio-frequency (RF) radiating antenna elements; and a center-fed, multi-band wave guiding structure coupled to the antenna aperture to receive a feed wave in two different frequency bands and propagate the feed wave to the RF radiating antenna elements of the antenna aperture.

Abstract: The disclosed invention provides a distributed directional aperture (DDA) system that is installed in a vertical lift aircraft that comprises a fuselage and a rotor system including rotary wings rotatably coupled to the fuselage. The DDA system provides capability to receive and/or transmit signals in one or more frequency bands, and provides communications, signals intelligence (SIGNINT), positional sensing, jamming, and offensive cyber on the vertical lift aircraft. The DDA system of the vertical lift aircraft includes a sensor and emitter array subsystem that includes a plurality of sensors and emitters distributed in the rotary wings, a beamformer subsystem that processes the sensor signals and emitter signals, and a telemetry subsystem that conveys signals between the sensor and emitter array subsystem and the beamformer subsystem.

Abstract: A datalink such as used on high-speed vehicles (missiles, guided-projectiles, manned or unmanned aircraft) includes an integrated conformal antenna array and out-of-band rejection filter for use with an RF radio. Integration of a single rejection filter between the EME power received by the antenna array and the coaxial RF connector effectively protects the connector as well as the radio. The connector can now be designed based solely on the transmit power requirements of the radio. The resultant connector is smaller and takes up less space inside the vehicle.

Abstract: A system of a machine includes a network of nodes distributed throughout the machine. Each of the nodes is operable to communicate using a plurality of electromagnetic signals. A controller is operable to communicate with the nodes using electromagnetic signals. The system also includes a plurality of waveguides configured to guide transmission of the electromagnetic signals between the controller and one or more of the nodes. A radio frequency-based repeater is coupled to at least two of the waveguides in the network between the controller and at least one of the nodes. The radio frequency-based repeater is configured to operate using power extracted from at least one of the electromagnetic signals when a signal-to-noise ratio is above a threshold, and the radio frequency-based repeater is configured to use energy stored in an onboard energy storage system when the signal-to-noise ratio is below the threshold.

Abstract: Antennas, systems and methods may be implemented using a feed network with optional balanced to unbalanced conductor (balun) structure printed on one or more varying surfaces (e.g., sides, faces, etc.) of antenna substrates of various shapes including, but not limited to, flat, cylindrical, hemispherical and conical-shaped antenna substrates. Both antenna element/s and feed network/s may be printed onto one or more varying surfaces of a single common antenna substrate, such as printed onto both interior and exterior surfaces of the same hollow antenna substrate.

Abstract: An endfire antenna structure is disclosed that is for use on aerodynamic systems. The antenna structure includes a first layer of patterned metal, a second layer of patterned metal, and a stack of material layers that includes the first layer of patterned metal and the second layer of patterned metal. The first layer of patterned metal includes a plurality of parallel slots etched through the metal. The second layer of patterned metal includes a tapered radio frequency (RF) feedline having a narrow end coupled to an input/output (I/O) antenna connection. The second layer of patterned metal is aligned over the first layer of patterned metal such that the tapered RF feedline has a length that extends across the plurality of parallel slots. The stack of material layers is flexible such that the stack of material layers is configured to wrap at least partially around the fuselage of an aerodynamic system.

Abstract: An illustrative example sensor device includes a transmitter and a receiver having at least one lobe and at least null. A cover near the transmitter and the receiver includes a surface facing toward the transmitter and the receiver. The surface is at an angle relative to the receiver to direct at least some radiation transmitted by the transmitter and reflected from the surface toward the at least one null of the receiver.

Abstract: Technologies directed to cylindrical antenna structures. One metallic cylindrical antenna structure includes a first surface, a second surface, and a side wall with a first height. The cylindrical antenna structure can have a low profile with the first height being less than 20 millimeters (mm). The side wall includes first and second slots, the first being centered at a first point on the side wall at a second height and oriented longitudinally along an azimuthal direction of the cylindrical antenna structure and the second being centered at a second point on the side wall at the second height and oriented longitudinally along the azimuthal direction. A feed structure is located on the center axis and is physically separated from the first and second surfaces. The cylindrical antenna structure radiates electromagnetic energy in an omnidirectional radiation pattern, responsive to a radio frequency (RF) signal being applied to the feed structure.

Abstract: Antenna systems having adaptive antenna arrays for use in wireless communication devices are provided. In one example implementation, the antenna system includes a first antenna array include a plurality of antenna elements. The antenna system includes a second antenna array including a plurality of antenna elements. The first and second antenna arrays are each disposed about the periphery of the wireless device. At least one of the first and second antenna arrays is an adaptive antenna array having an active multi-mode antenna. The active multimode antenna can be adapted for configuration in one of a plurality of possible modes. The active multi-mode antenna is associated with a distinct radiation pattern when configured in each of the plurality of possible modes.

Abstract: Antenna modules for vehicles are disclosed. The antenna modules may be arranged on elongated bases and may be configured to be mounted in 5 cavities of top parts of vehicles. They may comprise a plurality of antennas distributed along the elongated bases. The plurality of antennas may comprise at least multiple-input multiple-output (MIMO) mobile communications antennas and global navigation satellite system (GNSS) antennas.

Abstract: A method for producing a radio frequency transmitting/receiving element comprising at least one radio frequency antenna and at least one radio frequency chip, and to a corresponding radio frequency transmitting/receiving element made by the method. The method comprises the following steps: providing a temporary rigid carrier; applying a conductor pattern structure comprising the antenna structure of the at least one radio frequency antenna and connection contacts—connected thereto via leads—for the at least one radio frequency chip; arranging the at least one radio frequency chip on the connection contacts of the conductor pattern structure; applying an electrically insulating layer on the conductor pattern structure, such that the at least one radio frequency chip is surrounded by the electrically insulating layer; and removing the temporary rigid carrier.

Abstract: An inverted F antenna for use in a projectile includes a ground plane and a radiating element oriented orthogonal to the ground plane and centered on the ground plane. The radiating element includes a ground stub trace having a relatively thick width, a meandering trace with a vertical orientation and a relatively high ground clearance and a feed trace having a tapered head.

Abstract: An apparatus and method are described for a leading and trailing edge antenna structure. The antenna disclosed, with optional director and reflector, can allow for greater RF and telecommunications capabilities on an aircraft, including operating at lower frequencies than previous solutions. The disclosure allows for greater capability with negligible effect on weight or drag of an aircraft.

Abstract: An antenna system may include a first antenna, and a second antenna opposite the first antenna, wherein the first antenna and the second antenna are configured to provide omnidirectional coverage.

Abstract: An antenna device includes a ground conductor (1), a dielectric tube (2) containing an ionizing gas and passing through the ground conductor, whose folded-back portion (201) and both ends are disposed in different sides of the ground conductor, first electrodes (3, 4) disposed at both ends of the dielectric tube (2), a plasma excitation power supply connected to the first electrodes, bringing the ionizing gas into a plasma state; a second electrode (6) ring-shaped and disposed at the both ends side of dielectric tube (2) from the ground conductor (1), fitted to and in contact with the dielectric tube outer surface, a high frequency transmitter (7) supplying a high frequency signal to the second electrode (6), and a feed line (8) connecting the second electrode and the high frequency transmitter. Each end of the dielectric tube (2) is larger than the second electrode in the inner diameter.

Abstract: Antenna arrangement for a multi-radiator base station antenna, the antenna having a feeding network based on air filled coaxial lines (1, 2, 3), wherein each coaxial line comprises an outer conductor (8) and an inner conductor (4, 5, 6), wherein an adjustable differential phase shifter including a dielectric part (9) is arranged in the antenna and said dielectric part being movable longitudinally in relation to at least one coaxial line (1, 2, 3).

Abstract: A system for detecting radio frequency (RF) signals includes a radome including one or more phase change material (PCM) layers disposed on an inner surface thereof and a sensor at least partially disposed within the radome. The system also includes a heat source arranged such that it can direct heat toward the inner surface of the radome and a controller that causes the heat source to direct heat towards the inner surface of the radome such that a frequency selective surface (FSS) is formed thereon.

Abstract: An antenna element having a metal pattern with a three-dimensional profile. The metal pattern is at least one helix-loaded helix-loaded meandered loxodromic spiral. The profile is generally that of a domed top adjoined to a rotationally symmetric body such as a conical section. Typically, the metal antenna pattern is fabricated upon or otherwise supported by a dielectric medium.

Abstract: A monocone antenna includes a conical radiation element having a feed point at a vertex of the conical radiation element being connected to a feed transmission line and a capacitive ring radially outside of the conical radiation element and in proximity to the conical radiation element. The capacitive ring is connected to a ground plane of the monocone antenna. Optionally, a capacitive gap may be defined between the conical radiation element and the capacitive ring that is substantially filled with dielectric material.

Abstract: An adaptive electronically steerable array (AESA) system comprises a plurality of arrays, each comprising a plurality of radiating elements, each array configured for placement on a forward-facing surface of a different one of a plurality of aerodynamic control surfaces on an interceptor. A plurality of radio frequency (RF) transmissive radome elements, each having an aerodynamic shape complementary to the aerodynamic control surface, are placed over one of the arrays. Control circuitry configures the arrays, independently or in concert, for RF target engagement and communication. Additional arrays may be positioned on side or aft-facing surfaces of the aerodynamic control surfaces for RF communication. The AESA system may be paired with an IR system for dual-mode operation.

Abstract: A method and apparatus comprising a resin layer, a number of conductive elements, and a number of layers of reinforcement material. The number of conductive elements is on the resin layer. The number of conductive elements has a configuration that forms an antenna system. The number of layers of reinforcement material forms a reinforcement for a composite structure, and at least a portion of the resin layer forms a matrix for the composite structure.

Abstract: An antenna cover (1) for a radar (2) for a vehicle has a rectangular parallelepiped shape, having a flat cover top (10) that faces a microstrip antenna (21a, 21b) of the radar (2) and a sidewall (11) that covers the microstrip antenna (21a, 21b) sideways. The sidewall (11) is located out of the range where the electromagnetic waves to be received by the microstrip antenna (21a, 21b) are directly received. An inner face (11a) of the sidewall (11) is at a right angle to the cover top (10). An outer face (11b) of the sidewall (11) is at a constant angle ? larger than 0 degree but smaller than 90 degrees, to the inner face (11a) of the sidewall (11). The sidewall (11) is structured such that its thickness increases toward the side where the microstrip antenna (21a, 21b) is present.

Abstract: The invention provides circuitry integrated into a silicon chip that measures aspects of an RF signal on a transmission line in order to provide data that is ultimately used by an antenna tuner circuit to substantially match the impedance of the antenna with that of the transmission line providing the RF frequency to be transmitted.

Abstract: An unmanned aerial vehicle (UAV) includes at least one passive reflective device having an elongated configuration defining a long axis and comprising a material configured to reflect radio signals. The UAV also includes a control system configured to control the UAV along a flight path that orients the at least one passive reflective device such that the long axis remains substantially tangential to an ellipsoid whose foci are at two points between which radio communication is desired.

Abstract: A low drag TCAS antenna includes a plurality of broadband antenna elements in a housing having at least three fins. L band radios in the aircraft may utilize the broadband antenna elements, thereby reducing power consumption, cost and aerodynamic inefficiency due to a plurality of antennas protruding from the aircraft.

Abstract: A communication device (20) for communication between a movable piece of equipment (101) of a rotary rotor (5) and a stationary piece of equipment (102). Said communication device (20) is fitted with a set (10) of controlling swashplates including a rotary swashplate (11) and a non-rotary swashplate (12), the communication device (20) comprising a movable transfer unit (21) and a stationary transfer unit (22) for exchanging information respectively with the movable equipment (101) and with the stationary equipment (102). Each transfer unit (21, 22) is connected to a respective transmit-and-receive antenna (31, 32), including a movable antenna (31) connected to the movable transfer unit (21) and fastened to the rotary swashplate (11) and a stationary antenna (32) connected to the stationary transfer unit (22) and fastened to the non-rotary swashplate (12), the movable antenna (31) and the stationary antenna (32) being suitable for communicating with each other wirelessly.

Abstract: A thermal management system and method for active cooling of high speed seeker missile domes or radomes comprising bonding to an IR dome or RF radome a heat pipe system having effective thermal conductivity of 10-20,000 W/m*K and comprising one or more mechanically controlled oscillating heat pipes, employing supporting integrating structure including a surface bonded to the IR dome or RF radome that matches the coefficient of thermal expansion the dome or radome material and that of said one or more mechanically controlled oscillating heat pipes, and operating the heat pipe system to cool the IR dome or RF radome while the missile is in flight.

Abstract: An aircraft communications system may include a RF-transparent enclosure, a plasma antenna element and a controller. The RF-transparent enclosure may be disposed substantially conformal with a portion of the aircraft. The plasma antenna element may be housed within the RF-transparent enclosure. The controller may be operably coupled to the plasma antenna element to provide control of operation of the plasma antenna element. The plasma antenna element may include one or more RF-conductive plasma devices that are selectively ionized to a plasma state under control of the controller.

Abstract: The present invention relates to an antenna (7) for an aircraft (1), the antenna being fitted with a coaxial cable provided with a coaxial connector (25) comprising a core (26) and shielding (27), the coaxial cable (24) being suitable for being connected to a source (40) for co-operating with the antenna (7). The antenna comprises a cable-cutter device (10) having a frame (12) carrying two sharp edges (11), said antenna (7) including an impedance-matching system (35) connecting said frame (12) to said core (26), said frame being a radiating member of the antenna.

Abstract: A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.

Abstract: A low-radar cross section antenna structure for an active electrically scanned antenna including an active electrically scanned antenna enclosure and at least two antenna elements. The antenna elements are arranged to be mounted on a front surface of the active electrically scanned antenna enclosure and embedded in a lightweight structure. The front surface and side surfaces of the active electrically scanned antenna enclosure and the antenna elements are arranged to be covered with the lightweight structure. A thin laminate is arranged to cover an outer top surface and an outer side surface of the lightweight structure. Parts of the lightweight structure are arranged to be doped with a lossy material having dielectric, magnetic and/or resistive losses, thus making these parts of the lightweight structure absorbing for electromagnetic radiation.

Abstract: The present invention relates to panel array antennas, and more particularly to a cooling system for an antenna such as a jet stream conformal panel array antenna. In one embodiment, a panel array antenna for an aircraft includes a closed-loop fluid flow path that passes through the panel array assembly and dissipates heat to the jet stream outside the aircraft. A fluid such as pressurized air passes through this closed-loop path, flowing through strategically-placed openings in the layers of the panel array assembly and flowing over and around the hot electrical components in the panel assembly. The air is heated by these electrical components, and the heated air then flows through the flow path under the top sheet, dissipating the heat to the jet stream outside. In one embodiment, a panel array antenna includes a panel assembly having a top layer through which the antenna radiates or receives a signal, and a fluid flow path through the panel assembly.

Abstract: A method and apparatus for transmitting wireless signals. An apparatus comprises a stringer having a channel and a waveguide located within the channel. The waveguide is capable of carrying a number of wireless signals.

Abstract: A wireless communication device for an aircraft that includes at least one antenna, for example a wide-band antenna, and a transparent multilayered substrate, for example a side glazing, a front glazing or a porthole of the aircraft, adapted for receiving the at least one antenna. At least a portion of one layer of the substrate is at least partially reflective to electromagnetic waves transmitted or received by the at least one antenna, wherein the at least one portion of the layer of the substrate is located at least partially opposite the at least one antenna. The at least one portion of the layer of the substrate can be a de-icing or defogging heating film.

Abstract: A stabilized field sensor apparatus collects field data, in particular magnetic field data, with reduced motion noise. The apparatus includes a tear drop shaped housing, a tow frame in the housing, a plurality of vibration isolating dampers spaced around the frame, a base assembly mounted to the dampers, a support pedestal having a bottom end fixed to the base assembly and an upper free end, a single spherical air bearing connected to the upper free end of the pedestal, an instrument platform with a lower hollow funnel having an upper inside apex supported on the air bearing for a one point support, principal and secondary gyro stabilizers for maintaining pivotal and rotational stability, and at least one field sensor mounted to the instrument platform for collecting the field data while being stabilized against motion noise including vibration, pivoting and rotation from the base assembly, from the tow frame and from the housing.

Abstract: A dual function composite system includes a first electronic subsystem, a second electronic subsystem, and a composite member between the first and second electronic subsystems. The composite member includes plies of fabric, and resin impregnating the plies of fabric. At least one ply of the fabric includes signal transmission elements integrated therewith and interconnecting the first electronic subsystem with the second electronic subsystem.

Abstract: The present invention relates to an antenna (7) for an aircraft (1), the antenna being fitted with a coaxial cable provided with a coaxial connector (25) comprising a core (26) and shielding (27), the coaxial cable (24) being suitable for being connected to a source (40) for co-operating with the antenna (7). The antenna comprises a cable-cutter device (10) having a frame (12) carrying two sharp edges (11), said antenna (7) including an impedance-matching system (35) connecting said frame (12) to said core (26), said frame being a radiating member of the antenna.

Abstract: Multifunctional structures and methods of manufacturing multifunctional structures which function as both electronic devices and load-bearing elements are disclosed. The load-bearing elements are designed to have electronic functionality using electronics designed to be load-bearing. The method of manufacturing the multifunctional structure comprises forming an electronic element directly on at least one ply of arbitrarily shaped load-bearing material using conventional lithographic techniques and/or direct write fabrication techniques, and assembling at least two plies of arbitrarily shaped load-bearing material into a multifunctional structure. The multifunctional structure may be part of an aerospace structure, part of a land vehicle, part of a watercraft or part of a spacecraft.

Abstract: A broadband antenna includes a first antenna element having first and second ends spaced apart by a surface thereof. A second antenna element is substantially co-planar with the first antenna element, the second antenna element having first and second ends spaced apart by a surface thereof. The first end of the second antenna element is spaced apart from the second end of the first antenna element by a first air gap. A conductive structure is spaced apart from the first end of the first antenna element by a second air gap, the conductive structure being configured to provide for structural excitation of the antenna over a lower frequency range of an available broadband antenna bandwidth, such as may be a continuous operating bandwidth.

Abstract: A communication system includes a first communication module within a rotating frame of reference and a second communication module within a fixed frame of reference. The first communication module and the second communication module in wireless communication at least partially through a hollow shaft.

Abstract: A space-fed conformal array for a high altitude airship includes a primary array lens assembly adapted for conformal mounting to a non-planar airship surface. The lens assembly includes a first set of radiator elements and a second set of radiator elements, the first set and the second set spaced apart by a spacing distance. The first set of radiators faces outwardly from the airship surface to provide a radiating aperture. The second set of radiators faces inwardly toward an inner space of the airship, for illumination by a feed array spaced from the second set of radiators.

Abstract: An antenna is provided for use with a vehicle that includes a body that is encased by a thermal protection system (TPS). An opening extends through the TPS and the vehicle body, and an antenna assembly and a seal member are positioned within the opening. The seal member extends about the antenna assembly and is radio frequency (RF) opaque. A window extends across the opening to retain the antenna assembly and seal member within the opening. The window is RF transparent.

Abstract: The present invention is directed to a High Frequency (HF) shunt antenna which promotes improved performance over currently available antenna solutions. The HF shunt antenna may include a shunt plate structure which includes multiple shunt plates configured in a parallel orientation relative to each other and provides an expansive surface area which may promote reduced inductance and lower equivalent parallel resistance of the HF shunt antenna, thereby allowing the HF shunt antenna to be spec-compliant and tunable by a HF coupler, without increasing the footprint of the HF shunt antenna and without reducing radiation efficiency of the antenna.

Abstract: Antenna embodiments are illustrated that are particularly suited for use in aircraft navigation, identification and collision avoidance systems. An exemplary antenna embodiment operates about a center wavelength and in association with a ground plane and comprises first and second grounded, shortened, and top loaded monopoles. These monopoles are spaced apart above a ground plane and each of them includes a feed post, a shorted post, and a top load wherein the shorted post is spaced from the feed post, is coupled to the ground plane, and has a length less than one fourth of the center wavelength. In addition, the top load is coupled to the feed post and the shorted post and is configured along orthogonal minor and major axes of the top load to have a width along the minor axis and a length along the major axis that exceeds the width.

Abstract: There is described a Passive Intermodulation (PIM) shield for use with an aircraft for reducing PIM sources, the PIM shield comprising: a conductive material adapted to be placed between an antenna and a fuselage of the aircraft for preventing undesired Radio Frequency (RF) signals resulting from a combination of RF signals transmitted from and to the antenna and generated by non-linear junctions or material between the antenna and the fuselage of the aircraft, the conductive material having a thickness based on an RF skin-depth related to an operating frequency of the antenna. There is described a method for determining an operating frequency of an antenna, determining an RF skin-depth related to the operating frequency of the antenna, and providing the PIM shield.

Abstract: An aircraft antenna, an antenna system, and a method of providing an antenna are disclosed. A conductive plate is configured to conform to an area on an outer surface of a fuselage of an aircraft. The conductive plate is configured to be positioned in direct and intimate contact with a conductive portion of the fuselage. A conductive rib is configured to be electrically coupled to the conductive plate and to extend toward a first point adjacent an inner surface of a structure of the aircraft that extends from the fuselage. A conductive spine configured to extend along the inner surface of the structure between the first point and a second point. The conductive spine is electrically coupled to the conductive rib at the first point and is configured to receive a conductive feed line at the second point. An antenna coupler mount is configured to receive an antenna coupler. The antenna coupler mount is physically coupled to a surface of the conductive plate and is electrically coupled to the conductive plate.

Abstract: An antenna array for use in an aviation application setting comprises an external covering and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. A deposit of phosphor material is also disposed beneath this covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering can be fixed to an exterior surface of an aircraft. The four radio frequency antennas are electrically discrete from one another though also being configured as an integral mechanical structure. The phosphor material, in turn, can serve to facilitate detection of a parameter of interest, such as temperature or airspeed.

Abstract: The present invention is a multi-element anti-jamming (A/J) antenna array. The antenna array includes a first antenna assembly configured for being fuse-mounted a first distance from an aft end of at least one of an artillery shell and a munition. The antenna array further includes a second antenna assembly configured for being fuse-mounted a second distance from an aft end of at least one of the artillery shell and the munition, the second distance being lesser than the first distance. Further, the antenna array includes multi-band functionality.