Abstract: An antenna is disclosed. The antenna can include an aerodynamic surface and an antenna component comprising a structure configured to extend from the aerodynamic surface. The structure and at least a portion of the aerodynamic surface can form an antenna, such as a half double-ridge horn antenna or a half Vivaldi antenna. In one aspect, the structure can be configured to support a pod, thus integrating the antenna with a mechanical mounting structure for the pod.

Abstract: A cable cutter (10) for an aircraft (27) comprises an electrically-conducting body (12) configured to be mounted on an aircraft (27) and to cut a cable and an electrically-conducting auxiliary member (38) attached to, and electrically isolated from, the body (12). The body (12) and auxiliary member (38) are configured to together form an antenna. A method of manufacturing an antenna for an aircraft comprises the steps of providing a cable cutter (10) for an aircraft, the cable cutter comprising an electrically-conducting body (12) configured to be mounted on an aircraft (27) and to cut a cable; providing an electrically conducting auxiliary member (38) and attaching it to the body (12) so as to be electrically isolated from the body (12); and providing an antenna connector (42) and connecting the terminals thereof to the body (12) and auxiliary member (38) respectively.

Abstract: A communication system is provided. The system comprises a ground station, one or more airborne measurement devices, and an airborne device tethered to the ground station using one or more wires. The airborne device is operable to communicate with the one or more airborne measurement devices.

Abstract: Methods and apparatus are disclosed for passively steering an antenna disposed on a balloon in a balloon network. An example balloon involves: (a) an antenna and (b) a pressure-sensitive mechanism in mechanical communication with the antenna such that a change in the balloon's altitude causes at least an element of the antenna to rotate upward or downward, a separation distance between two or more radiating elements to increase or decrease, or a separation distance between the two or more radiating elements and a reflector to increase or decrease.

Abstract: A combination antenna fixture is configured to accommodate adjustment of independent azimuths for each frequency band of operation of antennas of a mobile telephone network. The antennas may be mounted within a single radome or housing used to protect the antennas from environmental conditions. Each of the antennas may be coupled to a different movable mounting device within a radome, which may enable directing the azimuth for each antenna independently. By directing the azimuth independently for each antenna, the signal coverage area for each antenna may be customized to optimize coverage over a geographic area.

Abstract: An antenna system can include a first panel of radiators that extend from a vertex in a first substantially linear direction. The antenna system can also include a second panel of radiators extending from the vertex in a second substantially linear direction. The first panel of radiators and the second panel of radiators form an angle between about 1 degree and about 45 degrees to enhance gain.

Abstract: An unmanned vehicle system, having at least one autonomous ground vehicle (A-GV) and at least one remote controlled aerial vehicle (RC-AV). The A-GV autonomously navigates across the ground, and on-board perception sensors, whose field of view that contains at least a portion of the ground ahead of the direction of travel of the ground vehicle as well as the RC-GV. The RC-AV flies in response to commands received from the control system of the A-GV. The RC-AV has on-board in-sky perception sensors having a field of view that contains at least a portion of the ground path to be followed by the ground vehicle. The control system of the A-GV locate the aerial vehicle, receives perception data from the on-ground perception sensors and the in-sky perception sensors, and uses combined perception data to determine a ground path for itself and for the RC-AV.

Abstract: A method of manufacturing is provided comprising forming a mounting plate adaptable to a plurality of models of aircraft, forming an adapter plate configured for use with the mounting plate, forming a radome configured to attach to the mounting plate, configuring a shape of the adapter plate to encompass at least one footprint of at least one antenna, and providing a plurality of hole patterns through the adapter plate corresponding to known hole patterns of the at least one antenna.

Abstract: An inventive antenna comprises two antenna elements forming a planar slotline antenna. The antenna furthermore comprises absorber elements surrounding the antenna elements on two layers. The absorber elements are shaped to partially cover the antenna elements and partially not cover the antenna elements. Moreover, they are shaped to dampen at least a dipole-mode of the antenna elements and not to dampen a slotline-mode of the antenna elements.

Abstract: An antenna assembly is for a fuselage of an aircraft and includes a satellite antenna, a radome covering the satellite antenna, and attachment fittings for coupling to the fuselage of the aircraft. The attachment fittings include fore, aft and side attachment fittings. The fore attachment fittings react to vertical, lateral and longitudinal loads. The aft attachment fittings react to vertical and lateral loads and permit longitudinal displacement. Left side and right side attachment fittings react to vertical loads and permit lateral and longitudinal displacement. A fairing mounts the radome to the attachment fittings.

Abstract: A computing device may include a conductive member, a slot antenna having a slot defined by the conductive member and an antenna pattern portion disposed proximate to the slot, and/or a slot switch configured to switch a portion of the slot. The slot switch may have a first terminal and a second terminal such that the portion of the slot is disposed between the first terminal and the second terminal. The slot switch may be switchable between a first configuration in which the first and second terminals are electrically connected and a second configuration in which the first and second terminals are not electrically connected. The computing device may also include a switching controller configured to switch the slot switch between the first and second configurations.

Abstract: An antenna includes a radiator and a reflector and has a radiation pattern that is based at least in part on a separation distance between the radiator and the reflector. The antenna includes a linkage configured to adjust the separation distance based at least in part on the altitude of the antenna. The resulting radiation pattern can be dynamically adjusted based on altitude of the antenna such that, while the antenna is aloft and the antenna is ground-facing, variations in geographic boundaries and intensity of the radiation received at ground level are at least partially compensated for by the dynamic adjustments to the radiation pattern.

Abstract: An antenna, including a radiating element configured to have a fundamental resonance frequency being regarded as a first harmonic resonance frequency fo, and feed points positioned on the configured radiating element at selected multiple locations that correspond to where a multiple of the first harmonic resonance frequency have current maxima, wherein feeds at the feed points cooperate at an operating frequency of the antenna to constructively combine their respective antenna radiation patterns.

Abstract: Conformal antennas and methods for radiating radio frequency energy using conformal antennas are provided. In particular, one or more tapered feeds can be provided as part of or interconnected to a conductive top plate. The one or more tapered feeds have a depth that decreases from a feed point to a tip. The tip of the one or more tapered feeds is adjacent a cavity formed over a lens region. An aperture over the lens region can be covered or filled by an impedance surface. This impedance surface may comprise a frequency selective surface. Alternatively, a frequency selective surface can be provided over the lens region of an antenna incorporating one or more stripline feeds.

Abstract: An apparatus is provided. In the apparatus, there is an antenna package and an integrated circuit (IC). A circuit trace assembly is secured to the IC. A coupler (with an antenna assembly and a high impedance surface (HIS)) is secured to the circuit trace assembly. An antenna assembly has a window region, a conductive region that substantially surrounds the window region, a circular patch antenna that is in communication with the IC, and an elliptical patch antenna that is located within the window region, that is extends over at least a portion of the circular patch antenna, and that is in communication with the circular patch antenna. The HIS substantially surrounds the antenna assembly.

Abstract: This antenna unit comprises an antenna having a radiating front surface, a back surface and a lateral outline having at least one electric field reinforcing region. It is characterized in that it further comprises a device protecting the antenna from lightning, having an internal surface at least partially capping the lateral outline of said antenna by being in electrical contact with said lateral outline, said internal surface covering the or each electric field reinforcing region, said protecting device having a curved external surface opposite said internal surface.

Abstract: A system and method for reducing energetic proton flux trapped in the inner radiation belt by injecting Ultra Low Frequency (ULF) electromagnetic waves is disclosed. The ULF electromagnetic waves is generated by space or ground based transmitters and the frequency range is selected such that the injected waves are in gyrofrequency resonance with trapped 10 to 100 Mev protons. Pitch angle scattering of the trapped protons in gyro-resonance with the injected waves increases their precipitation rate by forcing their orbits into pitch angles inside the atmospheric loss-cone where they are lost by intaracting with the dense neutral atmosphere at altitudes below 100 km. The reduction of energetic proton flux trapped in the inner radiation belt allows use of commercial electronics with submicron feature size on Low Earth Orbit satellites and microsatellites without the operational constraints imposed by the presence of energetic proton fluxes trapped at the inner radiation belts.

Abstract: A proximity warning system for a helicopter (22) comprising at least two radar units (1-3), preferably three radar units (1-3) arranged to transmit microwaves and receive reflections of said microwaves from obstacles (10). The at least two radar units (1-3) are fixed next to a main rotor head(s) (20) of the helicopter (22) for horizontally scanning an entire environment of 360° around the helicopter (22), all of said at least two radar units (1-3) operating essentially at the same frequency.

Abstract: An aircraft comprising a fuselage and a radome fixed to the fuselage. The radome defines a housing and the fuselage comprises a sealed bulkhead closing the housing. A weather radar antenna comprises a main panel. A plurality of peripheral panels are arranged around the main panel, inclined from a planar surface of the main panel and located on the same side of the planar surface. The housing contains the antenna which is mounted on the fuselage through a mechanical support fixed to the fuselage and to the weather radar antenna on the same side of the planar surface as the peripheral panels. A bird strike shield is located between the antenna and the sealed bulkhead. The shield comprises a dome with a top and a base, the base being fixed to the aircraft fuselage. An opening is formed at the top of the dome through which the mechanical support passes.

Abstract: Systems and methods are disclosed to intelligently employ antenna resources in a manner that may reduce interference between communications signals even in instances where multiple separate frequency band communications need to be supported in a vehicle of limited size. A manifold antenna system is proposed that provides a scheme and a physical construct whereby multiple individual radio receiver/transmitter units may share a limited number of transmitting and receiving antennas. The disclosed manifold antenna system is particularly adaptable to aircraft, spacecraft, vessel or vehicle applications where there is limited room for mounting a number of individual antennas as may be needed to support each radio receiver/transmitter unit in an effort to minimize an amount of interference as is conventionally caused by having transmitting antennas located in too close a proximity to receiving antennas.

Abstract: An antenna system for mobile communication includes a transportation device and an antenna module installed on the transportation device. The antenna module has a first polarized antenna unit and a second polarized antenna unit. The polarized direction of first polarized antenna unit is perpendicular to the polarized direction of second polarized antenna unit, such that when the transportation device moves along a first direction, the first and the second polarized antenna units are coupling to each other, and each has an 8-shaped radiation pattern. The longitudinal direction of the radiation pattern of the first polarized antenna unit and the longitudinal direction of the radiation pattern of the second polarized antenna unit are parallel to a second direction, and the second direction is not parallel to the first direction. Thus, the instant disclosure provides the antenna system capable of restraining the multipath fading of mobile communication.

Abstract: Described herein is a method and system for gimbaled mounting of satellite dishes. The gimbaled mount for satellite systems overcomes some of the most common negative events affecting satellite communications. The system is a cost effective solution that amortizes the cost of the additional equipment to well over the customary three to five years for satellite use and extends its working life expectancy to 20 years or more. Utilization of stainless steel rather than normal steel or lighter duty aluminum further extends the mounting systems longevity. The inclusion of an environmental feedback system for both snow and ice damage, wind damage, and earthquake damage increases the projected useful life of the mounting system.

Abstract: A radome having localized areas of reduced radio signal attenuation includes a body having a first portion and a second portion. The first portion has a reduced radio signal attenuation property in a transmit band and a second portion has a reduced radio signal attenuation property in a reception band.

Abstract: A radome having localized areas of reduced radio signal attenuation includes a body having a first portion and a second portion. The first portion is mechanically stronger than the second portion and the second portion has a reduced radio signal attenuation property compared to the first portion.

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: This invention relates to improved ultra-wideband synthetic aperture radar and inverse synthetic aperture radar, capable of simultaneously and independently imaging a plurality of spectral and polarimetric channels covering multiple radio frequency octaves. Advances in technologies relating to signal processing, graphical user interfaces, color representations of multi-spectral radar images, low aerodynamic drag polarimetric SAR antenna systems, and synthetic aperture radar aircraft platforms are some of the advancements disclosed herein.

Abstract: An apparatus (10) for forming a three dimensional object (30) by layer-wise addition of a build material has a build-support (100) for supporting the object (30) during forming and a removable metallic base-layer (110) that is in the form of a mesh, film, sheet or foil. The base-layer (110) is removably securable to the build support (100).

Abstract: In an example embodiment, an airborne radio frequency (RF) antenna device can comprise: a radiating portion; a waveguide portion connected to the radiating portion; a desiccant airflow channel; and an internal air volume located within the RF antenna device and associated with the desiccant airflow channel. The desiccant airflow channel can be integral with the RF antenna device. The internal air volume can be vented to the environment outside of the RF antenna device through the desiccant airflow channel.

Abstract: A method of and apparatus for mitigating adverse transmission and/or reception effects that an obstruction would otherwise have upon a RF signal to be transmitted or received, the RF signal being available at a feed point and wherein the obstruction is spaced from the feed point in a direction of desired transmission or reception. An artificial impedance surface is disposed adjacent the feed point and the obstruction, and the artificial impedance surface is designed (i) to have a spatially non-varying impedance function in a constant impedance region at least immediately adjacent the feed point and (ii) to have a non-constant impedance function in one or more regions spaced from the feed point and closer to the obstruction.

Abstract: An aircraft, or other conductive body, (10) comprises transmission means for transmitting information to at least one other aircraft, said transmission means comprising: means (13) for generating an electric field external to the aircraft such that said field can control electrical charge (12) on at least one other aircraft; and means (40) for varying the electric field in accordance with information to be transmitted to said at least one other aircraft so that said at least one other aircraft can determine such information by detection of the control of electrical charge. The conductive body (10) comprises receiver means for receiving information from the transmission means of a similar conductive body, said receiver means comprising: electrical charge storage means (13) for storing electrical charge responsive to control by said transmission means; and detection means (34) for detecting the control of such electrical charge so as to determine information transmitted by said transmission means.

Abstract: Systems and methods for improving bearing accuracy in a Traffic Collision Avoidance System (TCAS) environment. An interrogation signal is transmitted from an array of antenna elements. A response to the transmitted interrogation signal from a target is received at a first pair of elements of the array. The first pair of elements is separated by at most ½? of the response signal. A processor determines coarse bearing of the received response. A second pair of elements of the array of antenna elements receives a response to the interrogation signal. The second pair of elements is separated by approximately N? of the response signal. N is an integer not equal to zero. A first bearing value to the target is determined based on the determined coarse bearing and the received response at the second pair of elements. The array is mounted on an aircraft or on a ground installation.

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: In one embodiment an artificial magnetic conductor assembly to reflect an electromagnetic signal with a phase shift that measures between ?90 degrees and +90 degrees at a target frequency comprises a first ground plane, a plurality of metallic elements disposed at a first distance from the first ground plane, a plurality of capacitors coupling adjacent metallic elements of the plurality of metallic elements, and a dielectric substrate disposed between the first ground plane and the array of metallic elements and formed from a material having a relative permittivity that measures between 1 and 20.

Abstract: Disclosed is a winglet radome assembly, which can include at least one antenna assembly that can send and receive signals, such as radio waves. Some implementations of the winglet radome assembly can be secured to a wing of an aircraft, such as a fixed-wing aircraft. In addition, the winglet radome assembly can be configured to secure to a distal end of the wing and can be securely adapted to a variety of aircraft.

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: A gyrotropic metamaterial structure that include a plurality of chiral metamaterials forming one or more pairs of dipole structures. A plurality of lumped circuits are positioned between the one or more pairs of dipole structures. The lumped circuits have a plurality of subwavelengths antennas that are combined to change the polarization states of an incident polarized wave by producing Faraday-like rotation allowing for nomeciprocal propagation of the incident polarized wave.

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: A method and apparatus for reworking an antenna aperture. A plurality of antenna cells comprise walls and antenna elements on the walls. Replacement antenna cells are placed adjacent to the plurality of antenna cells. The replacement antenna cells comprise a replacement wall and a replacement antenna element on the replacement wall. A conductive splice is attached to the replacement antenna element and to a one of the antenna elements on a one of the walls.

Abstract: A meteorological radar installed on board an aircraft, including a mechanical support fixed to a bulkhead of a nose of the aircraft, wherein an antenna is mounted on the mechanical support to enable turning mobility around an axis of rotation. The antenna includes a pedestal, on which at least one blade, extending radially along the axis of rotation, is installed. A free side of the blade, along which a plurality of radiating elements is distributed, perceptibly has the shape of a portion of conic in a plane including the axis of rotation. Because the blade is mobile only in rotation along the axis of rotation, and the selection of the emission/reception direction is performed electronically, not mechanically, the space and length requirements of the meteorological radar are fixed, whether the meteorological radar is in operation or not, and are determined based on the eccentricity and parameter of the conic.

Abstract: A handheld device and a planar antenna thereof are provided. The planar antenna comprises a radiator having a feeding point, a first short point and a second short point. The feeding point is coupled to a circuit board of the handheld device so that the handheld device transmits and receives a RF (radio frequency) signal through the radiator. The first short point is coupled to a ground of the circuit board so as to be grounded. A control element is disposed on the handheld device or the planar antenna in order to control the second short point to be selectively electrically coupled to the ground so that the planar antenna can operate at two different central frequencies. Furthermore, the planar antenna can operate at multiple central frequencies by changing a position of the second short point contacted to the radiator.

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 two-element array antenna system includes a first antenna element and a second antenna element. A transmitting, receiving, and processing (TRP) system is coupled to the first and second antenna elements via, respectively, a single first transmission element and a single second transmission element. The first and second transmission elements have respective transmit-path and receive-path functionality. The TRP system is configured to determine an amplitude offset and phase offset associated with the transmit-path functionality of the first and second transmission elements, and, based on data obtained during the determination of amplitude offset and phase offset associated with the transmit-path functionality of the first and second transmission elements, determine an amplitude offset and phase offset associated with the receive-path functionality of the first and second transmission elements.

Abstract: A high gain multi-beam aircraft blade antenna of an air-to-ground antenna systems includes multiple columnar matrix antenna elements housed within a blade. The elements are arranged to create independently steerable directed beams. A first independently steerable beam is used to provide communication. A second independently steerable beam is used to simultaneously search other signals.

Abstract: Disclosed is a patch antenna that is formed on the surface of an airplane. The patch antenna has a thickness that is sufficiently small, so that the aerodynamic shape of the airplane is not significantly affected. An insulating layer is disposed on the body of the airplane and antenna elements are then placed on the insulating layer. Various frequencies can be either received or transmitted by using antenna elements of various sizes. The body of the airplane is used as a ground plane for the antenna array. When multiple antenna arrays are utilized, antenna elements at the same frequency can generate a lobe that can be directed in different directions using phase changes. Various techniques can be used for applying the insulating layers to the airplane and forming the antenna elements on the insulating layers.

Abstract: An antenna is disclosed. The antenna can include an aerodynamic surface and an antenna component comprising a structure configured to extend from the aerodynamic surface. The structure and at least a portion of the aerodynamic surface can form an antenna, such as a half double-ridge horn antenna or a half Vivaldi antenna. In one aspect, the structure can be configured to support a pod, thus integrating the antenna with a mechanical mounting structure for the pod.

Abstract: Sensor pod attachment assemblies are provided for attaching a sensor pod containing airborne sensor equipment to an aircraft fuselage. The sensor pod assemblies may include fore and aft pairs of attachment pylon assemblies each having a lower end attached to the aircraft fuselage and an upper end attached to the sensor pod. The fore pair of attachment pylon assemblies can include port and starboard pylon structures, and a cross-support base connected to upper ends of the port and starboard pylon structures. The aft pair of attachment pylon assemblies may include a lengthwise adjustable spar assembly.

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: 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 behavior 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: The invention relates to a radome (1) for an aircraft, and more specifically to a device for connecting said radome to the structure of said aircraft. The radome that is the subject of the invention comprises a plurality of locking units able to bring together the opposing surfaces of the aircraft's fuselage (10) and the radome (1), each unit comprising: locking means (20) able to exercise a traction force on the surface of the fuselage, substantially normal to the surface, via attachment means; centering means able to withstand the shear forces substantially tangential to the opposing surfaces of the fuselage and radome; the locking means (20) are placed such that they are located inside the cone of resulting forces on the centering means so as to minimize the bending stresses generated by the assembly in the radome (1).

Abstract: A log-periodic dipole array antenna according to one exemplary embodiment of the present disclosure includes a dielectric substrate, a radiating element having a plurality of lines extending from a center to an outer side and symmetrically arranged on the dielectric substrate based on the center, so as to resonate in a first frequency band and a second frequency band, the plurality of lines being connected at the center or the outer side of the radiating element in an alternating manner, the lines becoming longer going from up to down of the radiating element fed according to a predetermined long-periodic ratio, and a band stopper formed on one point for connecting the lines to each other