Abstract: Reflector antennae and related structures and methods are described. The reflector antennae may have a deep f/D ratio and use an offset corrugated horn. Pivoting feed arms may be included for connecting a feed horn to a dish of the antenna. Radomes are also described, which may be formed of two or more pieces.

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: Antenna apparatus and methods of using the same that employ a broadband, planar, single feed ultra high frequency satellite communication (UHF SATCOM) antenna device which may be mounted on composite or other non-metallic and non-electrically conductive surfaces. The antenna apparatus may be implemented using a single antenna feed and impedance matching network with a low profile antenna shape that optimizes over-the-horizon gain, with no requirement for a ground plane. The antenna apparatus may also be implemented to cover the entire UHF SATCOM frequency band using a single antenna feed.

Abstract: A lightning protection device (25) for an antenna receiver, includes a shield (40, 70) for a coaxial cable (35, 65) connected to the antenna, and a high-pass filter mounted in series relative to the shield and capable of limiting the low-frequency power flowing in the coaxial cable, including a capacitor (30, 50, 55) and an inductor lower than 1 ohm at the lowest frequency used by the receiver, the capacitor including at least one layer of a conductive material embedded in a printed circuit. In some embodiments, the capacitor is made of a printed circuit (30) including at least two floor plans (50, 55), each of which is connected to the ground of a connector (80, 85) of the coaxial cable. The printed circuit may e.g. include at least one layer of a highly pervious material sandwiched between two layers of a conductive material.

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: 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: Described are a notch antenna and an array antenna based on a low profile stripline feed. The notch antenna includes a planar dielectric substrate having upper and lower surfaces. Each surface has a conductive layer with an opening therein. A notch antenna element is disposed on the conductive layer of the upper surface at the opening. A stripline embedded in the planar dielectric substrate extends under the notch antenna element. The stripline is adapted to couple an RF signal between the stripline and the notch antenna element. A conductive via is electrically coupled to the stripline and extends from the stripline to the opening in the conductive layer on the lower surface so that the RF signal is accessible at the lower surface.

Abstract: According to one embodiment, a cover comprising a higher dielectric constant layer disposed outwardly from a lower dielectric constant layer is coupled to a rectenna operable to convert microwave power to electrical power. The cover receives microwave power, provides a substantial impedance match for a plurality of angles of incidence, and directs the microwave power to the rectenna. The impedance match is selected to broaden a receive pattern of the rectenna.

Abstract: An antenna system includes a heptagonal antenna array having one center antenna element and seven circumferentially surrounding antenna elements offering improved near and far sidelobe rejection, which is well suited for mechanically-gimbaled and time delayed electrical steering antenna applications.

Abstract: The present invention provides a high-performance and lightweight helical antenna element and array thereof for use in an aircraft communication system or the like, where stringent spatial restrictions and gain requirements generally apply. The RF performance of the array is enhanced by using ribs and sleeves to reduce the dielectric volume of the support structures of the antenna elements, and by providing apertures within the sleeves of the support structures and between the ribs thereof.

Abstract: An antenna may include an enclosure formed by a front wall and a back wall opposite to the front wall, and a front face and a back face opposite to the front face. Both the front face and the back face extend between the front wall and the back wall to form a cavity within the enclosure. The enclosure further includes a slot formed in the front face to form a cavity backed slot. A radio frequency (RF) connector is mounted in the front wall. A shaped feed line is mounted within the cavity and is electrically connected to the RF connector to transmit and receive RF energy. The shaped feed line extends across the slot to couple the RF energy between the slot and the shaped feed line. The shaped feed line has a predetermined structure to substantially reduce an electric field strength to improve power handing 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: The invention relates to a mobile telecommunication device (100) for establishing a telecommunication connection in the radio frequency range with a base station (102; 104; 1100), the mobile telecommunication device comprising; at least a first (106) and a second antenna (108), an electromagnetic shield (110) located between the first and the second antenna, a logic component (1000), wherein the first and the second antenna are adapted to transmit and receive telecommunication signals of the same frequency band, and wherein the logic component selects whether the first or the second antenna is used for the telecommunication connection with the base station.

Abstract: A method for reducing interference in a mobile network is provided. The method includes determining locations of a plurality of nodes in the mobile network; steering at least one antenna at a node in the plurality of nodes in the mobile network; estimating intensity of signals from the at least one antenna at each of the plurality of nodes; determining optimal direction to steer the at least one antenna to reduce interference; and steering the at least one antenna in the optimal direction.

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 antenna assembly for installation to a mobile platform includes a base portion and an antenna module capable of being removably coupled to the base portion. The base portion includes a longitudinal axis and defines a channel extending along at least part of the longitudinal axis. The antenna module includes a mount and an antenna element coupled to the mount. The mount and antenna element can be received into the channel of the base portion, in electrical contact with the base portion, and then subsequently removed from the channel of the base portion as desired. Further, the base portion of the antenna assembly is configured to accommodate multiple different antenna modules as desired.

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: 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: A technique employing one or more conformal, spiral antenna for use in a vehicle such as a missile. The technique includes both an apparatus and a method. The apparatus includes a radome or missile body and a conformal, spiral antenna mounted in the radome or missile body. The method is one for use in operating a missile, comprising transmitting and receiving signals through a plurality of conformal, spiral antennae mounted in a radome or missile body. This may include in some variants transmitting and receiving signals through a plurality of conformal, spiral antennae mounted in a radome or missile body; and guiding the missile from information obtained from signals receive through the antennae.

Abstract: Antenna system embodiments are illustrated that include a planar, top-loaded dipole antenna and a planar elliptical dipole antenna arranged substantially coplanar and within the top-loaded dipole antenna. These antenna structures facilitate their combination with tuning coil chains, baluns and impedance matching circuits to operate over multiple frequency bands. System embodiments exhibit high gain and selectivity and may be digitally tuned over wide frequency bands (e.g., 30-600 MHz). The embodiments may be digitally tuned to support operational modes such as frequency hopping to thereby realize a secure communication system. Because these embodiments are configured to operate in the absence of a ground plane, they are especially suited for mounting on various portions of an aircraft's structure. For example, they may be configured as winglets and situated far out on wingtips to thus free the remainder of an aircraft's structure for other operational systems.

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.

Abstract: A method and apparatus comprising a planar member and a number of support members. The planar member may be configured to be attached to an airframe of an aircraft. The number of support members may be configured to connect the number of antennas to the planar member.

Abstract: A slotted waveguide antenna stiffened structure for an aircraft having an aircraft skin. The slotted waveguide antenna stiffening structure including a structural stiffening element reinforcing the aircraft skin; the structural element connected to a radio frequency feed source, the source providing energy with electromagnetic bandwidth to a slotted waveguide antenna having a plurality of slots. The antenna conformal to the aircraft skin and the structural stiffening element, the structural stiffening elements functioning as waveguides for the electromagnetic bandwidth. The slots may include a slot sealant enclosing the plurality of slots.

Abstract: The present invention is a multi-element anti-jamming (A/J) antenna array. The antenna array includes a first multi-band GPS edge-slot antenna and a second multi-band GPS edge-slot antenna. The first edge-slot antenna and the second edge-slot antenna are configured for implementation within at least one of an artillery shell and a munition. The first edge-slot antenna and the second edge-slot antenna are each further configured for supporting L-band frequencies.

Abstract: Radomes include an outer wall having a first average thickness and an inner wall having a second average thickness that is different from the first average thickness. At least a major portion of the inner wall is separated from at least a major portion of the outer wall by a space therebetween. The outer wall may comprise a layer of ceramic matrix composite (CMC) material. Aircraft and spacecraft include such radomes. Methods of forming radomes include forming an outer wall having a first average thickness, forming an inner wall having a different second average thickness, and coupling together the inner wall and the outer wall in such a manner as to provide a space between at least a major portion of the outer wall and at least a major portion of the inner wall.

Abstract: Methods and apparatus for a multilayer millimeter-wave window according to various aspects of the present invention operate in conjunction with a multilayer window that is substantially transparent to a passing millimeter-wave. The window may include multiple perforations in a thermally conductive element to be disposed in the path of the passing wave. A dielectric is positioned between each thermally conductive element and acts as a seal between wave source and an ambient environment. The window may also be configured to conform to a contoured surface or structure.

Abstract: A multi-element anti-jamming (A/J) antenna array is disclosed. The multi-element anti-jamming (A/J) array may include a circularly-polarized edge slot antenna and a dielectric resonator antenna. The circularly-polarized edge slot antenna and the dielectric resonator antenna are configured for implementation within an artillery shell, munition, or the like. The circularly-polarized edge slot antenna may be a gun-hard, embedded GPS antenna having an on-axis phase center. Further, the circularly-polarized edge slot antenna may have a forward-looking radiation pattern.

Abstract: The invention relates to a flush-mounted aircraft, UAV or missile antenna system, which is an integral part of the fuselage (3) of an aircraft, UAV or missile. The antenna system comprises a surface (3) made of a conductive material and a resonant recess (4) formed in said conducting surface, wherein said recess is conformed to provide a resonant behaviour in a selected operating frequency, the antenna system further comprising a radiating element (2) located within said recess and a feeding element (5) within said recess coupled to said radiating element.

Abstract: An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.

Abstract: An antenna system for an airborne radar system with a dorsal unit having two opposing long sides extending in a height direction (Z) and a longitudinal direction (X), and two opposing short sides extending in a lateral direction (Y) and the height direction (Z), and an upper side opposing a bottom side each extending in the longitudinal direction (X) and the lateral direction (Y). The antenna system comprises antenna devices being interspaced and mounted in connection to one of the short sides or both the short sides and extending in the height direction (Z). Each of the antenna devices comprises a waveguide board.

Abstract: The present invention is a folded monopole antenna assembly. The folded monopole antenna assembly includes a dielectric substrate, the dielectric substrate being configured for receiving at least one input. The folded monopole antenna assembly further includes a folded monopole antenna. The folded monopole antenna is configured for being connected with the dielectric substrate. Further, the folded monopole antenna includes at least one reactive circuit. The folded monopole antenna is further configured for receiving a signal via a received input included in the at least one received input. The antenna assembly is configured for implementation within an artillery shell and/or a munition.

Abstract: When an excitation signal is generated from an exciter due to an activation signal generated from a radar control device and is distributed to supply to each antenna sub-module, a combination reception signal is transmitted to a receiver from each antenna sub-module. The receiver takes in the combination reception signal obtained by each sub-module in response to an instruction from the radar control device, a frequency converter converts the combination reception signal into a prescribed frequency band, and a distributed aperture combination circuit performs a beam combination in accordance with a distributed aperture combination algorithm. In this way, a radar apparatus, which is equivalent to an active phased array radar of a large aperture and with high performance, is achieved.

Abstract: The present invention is a system which includes an interposer. The interposer may include a mounting plate for mounting the interposer to a fuselage of an aircraft. The interposer may interface with the fuselage to form a seal for maintaining pressure within the aircraft. The system may further include an antenna module. The antenna module may include a ground plane, an aircraft antenna, and a radome. The ground plane may be connected to the aircraft antenna and may be configured for allowing the antenna module to be mounted to the interposer. The radome may be connected to the ground plane to form an enclosure for housing the antenna. The antenna module may be removably connected to the interposer. The system may further include an interconnect for electrically connecting the antenna module to electronics located within the aircraft. The antenna module may be disconnected from the interposer without breaking the seal formed between the interposer and the fuselage.

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: Transparent, flat antenna (A) for transmitting and receiving electromagnetic waves, comprising at least one transparent, electrically insulating substrate (1) that has in its surface (1.1) an electrically insulating, circumferential edge region (1.1a), a transparent, electrically conductive coating (2) that covers large areas of the surface (1.1) of the substrate (1) up to the edge region (1.1a) and is formed by at least two flat segments (2.1n), where n=1 or a whole number n>1, that contain or are made of at least one electrically conductive material (2.2) and are insulated from each other by at least one linear, electrically insulating region (2.3), and at least one connection (3) for galvanic, capacitive, or inductive decoupling of the antenna signal from at least one flat segment (2.1n); Method for its manufacture and its use as a transparent built-in part.

Abstract: An antenna assembly for installation in a vehicle, such as an aircraft, and a method for using the same. The antenna assembly includes at least one window mounted antenna for an aircraft for enabling the aircraft to communicate wirelessly with a network, such as a Metropolitan Area Network (MAN). The window mounted antenna includes a panel that is transparent to visible light and has at least one antenna element, which can be etched onto the panel. The panel can attach to the interior window of the aircraft, or to an inner surface of the inner pressure window of the aircraft, or can replace the interior window, so as to position the antenna element in a side-looking direction with respect to the aircraft.

Abstract: A multi-feed horn includes a first feed horn, a second feed horn and a third feed horn which are connected to a first waveguide, a second waveguide and a third waveguide, respectively. The first feed horn is provided with a first proximal end opening and a first tip opening which are rectangular in shape, the second feed horn is provided with a second proximal end opening and a second tip opening which are rectangular in shape, and the third feed horn is provided with a third proximal end opening and a third tip opening which are rectangular in shape. Consequently, a multi-feed horn, a low noise block downconverter and an antenna apparatus which allow a further improvement in the reception characteristic and in the manufacturing accuracy can be provided.

Abstract: Optically reconfigurable radio frequency antennas for use in aircraft systems and methods of its use are disclosed. In one embodiment, the antenna includes a surface-conformal reflector that includes optically addressable carbon nanotubes. The nanotubes can be combined with light-sensitive materials so that exposure to light of the correct wavelength will switch the nanotubes back and forth between a metallic and non-metallic state. The antenna has a transmitter that radiates a radio frequency signal in the direction of the surface illuminator and an addressable optical conductor to illuminate the nanotubes with one or more optical signals. When the domains are illuminated they switch portions of the carbon nanotubes between its non-metallic states and metallic states to reflect the radiated radio frequency signal.

Abstract: An electrically small antenna (ESA) for resolution of subwavelength features is disclosed. The ESA is on the order of meters and has an efficient transmit/receive capability. The ESA is 1/10 of the length of the equivalent dipole length, and may be scaled down to 1/10,000. The ESA includes a metamaterial shell. Such an antenna may include phase sensitive current injection in the metamaterial resonant structures for loss-compensation.

Abstract: An aircraft structure having properties of an electromagnetic cavity is used to enhance wireless transmission for at least one of wireless data communication and wireless power transmission.

Abstract: An example satellite assembly includes a cover and an antenna attached to the cover. The satellite assembly further includes a base and a satellite module attached to the base such that the antenna is connected to the satellite module when the cover is secured to the base to form a sealed enclosure.

Abstract: A communication system including an antenna array with feed network coupled to communication electronics. In one example, a communication subsystem comprises a plurality of antennas each adapted to receive an information signal and a plurality of orthomode transducers coupled to corresponding ones of the plurality of antennas, each OMT is adapted to provide at a first component signal having a first polarization and a second component signal having a second polarization. The communication subsystem also comprises a feed network that receives the first component signal and the second component signal from each orthomode transducer and provides a first summed component signal at a first feed port and a second summed component signal at a second feed port, and a phase correction device coupled to the first and second feed ports and adapted to phase match the first summed component signal with the second summed component signal.

Abstract: The present disclosure relates to an airborne radar notably for a drone. In at least one embodiment, the airborne radar has a first structure and a second structure. The first structure is mechanically attached to an aircraft carrying the radar. The first structure has a degree of rotational freedom relative to the aircraft on a first axis. The second structure is attached to the first structure. The second structure has a degree of rotational freedom relative to the first structure on a second axis converging with the first axis. An antenna is attached to the second structure and configured to receive and send electromagnetic waves. An electronic module configured to process the electromagnetic waves sent or received by the antenna is attached to the second structure.

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: Antennas, integrated driveshaft covers, and methods are disclosed. A particular antenna includes a dielectric layer. The dielectric layer has a first curved surface and a second curved surface opposite the first curved surface. A conductive body has a curved outer surface, where the first curved surface of the dielectric layer is positioned against the curved outer surface. A high frequency (HF) antenna layer is positioned over positioned over the second curved surface of the dielectric layer, where the HF antenna layer is curved to conform to the second curved surface of the dielectric layer. A pair of contacts may be configured to receive an electrical connection for the HF antenna layer. When an HF signal is applied to the pair of contacts, the conductive body interacts with the HF antenna layer to radiate energy.

Abstract: An antenna may include an enclosure formed by a front wall and a back wall opposite to the front wall, and a front face and a back face opposite to the front face. Both the front face and the back face extend between the front wall and the back wall to form a cavity within the enclosure. The enclosure further includes a slot formed in the front face to form a cavity backed slot. A radio frequency (RF) connector is mounted in the front wall. A shaped feed line is mounted within the cavity and is electrically connected to the RF connector to transmit and receive RF energy. The shaped feed line extends across the slot to couple the RF energy between the slot and the shaped feed line. The shaped feed line has a predetermined structure to substantially reduce an electric field strength to improve power handing of the antenna.

Abstract: Antenna apparatus and methods of using the same that employ a broadband, planar, single feed ultra high frequency satellite communication (UHF SATCOM) antenna device which may be mounted on composite or other non-metallic and non-electrically conductive surfaces. The antenna apparatus may be implemented using a single antenna feed and impedance matching network with a low profile antenna shape that optimizes over-the-horizon gain, with no requirement for a ground plane. The antenna apparatus may also be implemented to cover the entire UHF SATCOM frequency band using a single antenna feed.

Abstract: A system (10) for providing connectivity to a mobile phone network having a plurality of towers providing wireless access to the network, includes a base (16) having one or more control motors (20, 22) connected to the base to rotate the base and one or more directional antennas (14) mounted on the base. A means is provided to determine the current location and orientation of the antennas (14) and a central control unit is provided in communication with each control motor (20, 22) and the means. A database accessible by the central control unit contains information relating to the location of each of the towers and the central control unit determines the most suitable tower for connection to the system (10). The control motor rotates the base (16) such that the directional antenna (14) is pointing in the direction of said tower.

Abstract: Radomes include an outer wall having a first average thickness and an inner wall having a second average thickness that is different from the first average thickness. At least a major portion of the inner wall is separated from at least a major portion of the outer wall by a space therebetween. The outer wall may comprise a layer of ceramic matrix composite (CMC) material. Aircraft and spacecraft include such radomes. Methods of forming radomes include forming an outer wall having a first average thickness, forming an inner wall having a different second average thickness, and coupling together the inner wall and the outer wall in such a manner as to provide a space between at least a major portion of the outer wall and at least a major portion of the inner wall.

Abstract: A radar system comprises a plurality of antenna sub-systems, each operable to transmit and receive radio frequency (RF) signals in a corresponding sector, wherein the plurality of antenna sub-systems are positioned such that the corresponding sectors cover a total range of about 180 degrees to about 360 degrees without rotation of the radar system. The radar system also comprises shared backend circuitry coupled to each of the plurality of antenna sub-systems and operable to process signals from each of the plurality of antenna sub-systems to detect the presence of an obstacle in one of the corresponding sectors.