Abstract: A wide-bandwidth antenna (e.g., a rib-dipole antenna) includes a first pole formed by a first conductive member and/or a second pole formed by a second conductive member. The antenna also includes an antenna feed between the first conductive member and the second conductive member. The antenna also includes at least one electrically conductive element including a surface. A portion of the surface is electrically connected to, and extends from, the first conductive member or the second conductive member. The at least one electrically conductive element is capable of conducting a current that generates a magnetic field. The magnetic field lowers a total reactance of the antenna, thereby resulting in enhanced performance of the antenna and more efficient use of volume.

Abstract: An integrated driveshaft cover antenna includes a driveshaft cover including a conductive layer and having a generally curved cross-section. The driveshaft cover is hingeably secured and electrically coupled to a helicopter tail boom section to cover a driveshaft access opening. The integrated drive shaft cover includes a dielectric layer including a first surface shaped to conform to a curved outer surface of the driveshaft cover and a second surface opposite the first surface. The first surface of the dielectric layer is positioned over the curved outer surface of the driveshaft cover. The first surface is secured to the curved outer surface of the driveshaft cover. The integrated drive shaft cover includes a slotted patch high frequency (HF) antenna layer having an inner slot and extends a majority of a length of the dielectric layer. The slotted patch HF antenna layer is secured to the second surface of the dielectric layer.

Abstract: The invention relates to a method for digital and directional data transmission between aircraft and ground stations. In this arrangement data is exchanged digitally and directly, in other words directly by means of directional antennae, between the aircraft and the ground stations. Furthermore, transmission lobes are adapted during flight, and the directional antennae on the aircraft only illuminate regions on the ground that are located at a minimum distance across the flight path of the aircraft.

Abstract: A conformal lens-reflector antenna system in which a radio frequency (RF) reflector is disposed in a depression in a raised portion of a dielectrical RF lens. The RF reflector can be shaped to reflect RF signals between an RF feed path to the lens and a body of the lens that extends generally laterally away from the raised portion. RF signals having a frequency within a resonant frequency range of the lens can be directed along the RF feed path to the reflector, which can reflect the RF signals into the body of the lens from which the RF signals can radiate. Similarly, RF signals in the resonant frequency range of the lens in space near the lens can resonate in the lens, and the reflector can reflect those signals down the RF feed path.

Abstract: In one embodiment, a main radio unit for an avionic communication system is provided. The main radio unit includes a software defined radio (SDR) configured to simultaneously provide at least one safety certified channel for a cockpit of an aircraft and at least one other channel for cabin services of the aircraft, wherein the SDR is configurable such that the SDR can generate signals corresponding to different communication protocols. The main radio unit also includes an interface for the at least one safety certified channel, wherein the interface is configured to convert signals between a protocol for hardware in the cockpit and a satellite communication protocol used by the SDR for the at least one safety certified channel; and wherein the SDR is configured to communicate with an RF unit for transmission and reception of signals over an antenna.

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: An isotropic antenna system internally mounted in the outermost portion of an aircraft wing and in the elevated winglet or similar vertical member of an aircraft wing. The antenna includes a shaped dielectric substrate including a horizontally oriented section located in the horizontally oriented member of the aircraft wing, a vertically oriented section located in the vertically oriented member of the aircraft wing, a first antenna element on the top surface of the dielectric substrate in the vertically oriented member of the aircraft wing, a second antenna element on the top surface and the bottom surface of the dielectric substrate, an antenna feed point coupled to the first antenna element and to the second antenna element, and a Radio Frequency (RF) energy guide coupled to the second antenna element. When the antenna is implemented and installed it does not substantially alter the appearance or aerodynamic characteristics of the aircraft.

Abstract: Apparatus, systems and methods to transmit power and data are provided. A particular apparatus includes a transmission component. The transmission component includes at least one first frequency selective surface (FSS) layer, at least one second FSS layer, and a dielectric layer separating the at least one first FSS layer and the at least one second FSS layer. In a particular embodiment, the apparatus also includes a first coupler coupled to the dielectric layer to send a signal along the transmission component.

Abstract: A wireless high-rate communication device for a vehicle, adapted for data exchange between at least one computer system of the vehicle and at least one computer system of a structure separate from the vehicle. The device includes at least one antenna connected to at least one emitter/receiver in turn connected to the at least one computer system of the vehicle, the device adapted for exchanging data according to a point-to-point ultra-wideband communication mode, with a device of the structure including at least one antenna connected to at least one emitter/receiver in turn connected to at least one computer system of the structure when the at least one antenna of the vehicle is in a vicinity of the at least one antenna of the structure.

Abstract: An on-board communication and navigation system for an aircraft is provided for allowing an aircraft to transmit and receive information via satellite link. Specifically, the system includes a radome assembly and a fuselage coupler. The radome assembly, for example, may include an antenna, an antenna control unit and an inertial reference unit. During installation, the fuselage coupler is securely and permanently mounted on the aircraft, typically on the fuselage at the top of the aircraft. Once the fuselage coupler is securely mounted, the radome assembly can be removably attached to the fuselage coupler, allowing the radome assembly to be quickly and easily removed and reattached to the aircraft, as needed.

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 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 determining the distance of an aircraft from an offset runway during a landing by offset approach, the offset runway being situated at a distance D from a main runway equipped with at least one elevation beacon, comprises at least the following steps: determining the height h at which the aircraft is situated, height determined with respect to a point T1 of the offset runway, height measured by a radioaltimeter with which the aircraft is equipped, determining the angle of elevation ? of the MLS mode by using the information of the elevation beacon provided by an elevation beacon with which said main runway is equipped, determining the value of the distance ? of the aircraft from the azimuth beacon (10) by using the following formula ? = ( h Tan ? ( ? ) - D ? ? 2 Cos ? ( ? ) ) 2 + h 2 , and, using said distance ? to obtain a point of location of the aircraft in an offset runway reference frame.

Abstract: A technique for suppressing backwaves employs a photonic approach. In one aspect, the technique includes an apparatus, including: a radiating element; and a microwave-photonic device for suppressing backwaves from the radiating element. In a second aspect, the technique includes a method for removing unwanted radiation from a radiating device, comprising: receiving unwanted radiation from the radiating device; communicating the received radiation to an electro-optically active material; communicating laser light to the electro-optically active material; communicating electromagnetic products of interactions between the radiation and the laser light to a photodiode; and communicating photodiode outputs to a termination.

Abstract: A reflector 38 includes a mirrored surface 48 and a frequency selective surface 46. The frequency selective surface 46 is arranged to reflect radiation of a first frequency band 52 and allow radiation of a second frequency band 50 to pass. The mirrored surface 48 is arranged to reflect radiation of the second frequency band 50. In this manner, the focal power for radiation of the first frequency band 52 is independent to the focal power for radiation of the second frequency band 50. Accordingly, the design of optical components associated with the second frequency band 50 can be undertaken independently of those associated with the first frequency band 52 so as to achieve the optimised focusing for each frequency band.

Abstract: A method, system, and device relating to a broad-band fragmented aperture tile and antenna system are disclosed. In one exemplary embodiment, an aperture tile comprises a plurality of unit cells. The plurality of unit cells individually comprise a driven radiating element layer, a module layer having a printed circuit board, wherein the module layer comprises one or more of a time delay module, a radio frequency distribution module, a radio frequency module, or a digital signal processor. Furthermore the aperture tile is coupled to a cold plate configured for heat transfer.

Abstract: Antenna unit cells suitable for use in antenna arrays are disclosed, as are antenna array and mounting platform such as an aircraft comprising antenna unit cells. In one embodiment, an antenna unit cell comprises a dielectric substrate having a length extending along a first axis and a width extending along a second axis, a first plurality of radiating elements disposed on a first side of the dielectric substrate, and a second plurality of radiating elements disposed on a second side of the dielectric substrate, opposite the first side, wherein the second plurality of radiating elements extend to an edge of the unit cell, and the first plurality of radiating elements overlap portions of the second plurality of radiating elements. Other embodiments may be described.

Abstract: This disclosure provides a radome to be installed on an emission face side of an antenna, which includes an outer wall having a side cross-section formed in a substantially semi-circular shape to include the antenna therein, and an inner wall arranged between the outer wall and the antenna, and formed in a shape to substantially conform to the outer wall. A gap between the outer wall and the inner wall is wider near both ends on the circumference of the substantially semi-circular shape than at a substantially midpoint on the circumference of the substantially semi-circular shape.

Abstract: A scanned radio frequency (RF) antenna having a small volume is described.

Abstract: The present invention is directed to an antenna system which may serve as a common antenna for multiple avionics systems implemented on-board an aircraft. The antenna system provides horizontal and vertical polarization functionality, while providing high isolation between a first input port of a coupler of the antenna system (the first input port being connected to a first avionics system) and a second input port of the coupler (the second input port being connected to a second avionics system).

Abstract: An integrated driveshaft cover antenna includes a driveshaft cover including a conductive layer and having a generally curved cross-section. The driveshaft cover is hingeably secured and electrically coupled to a helicopter tail boom section to cover a driveshaft access opening. The integrated drive shaft cover includes a dielectric layer including a first surface shaped to conform to a curved outer surface of the driveshaft cover and a second surface opposite the first surface. The first surface of the dielectric layer is positioned over the curved outer surface of the driveshaft cover. The first surface is secured to the curved outer surface of the driveshaft cover. The integrated drive shaft cover includes a slotted patch high frequency (HF) antenna layer having an inner slot and extends a majority of a length of the dielectric layer.

Abstract: Embodiments of a multi-purpose mounting device for mounting an electrical device to a structure coupled to an airborne object are provided. In one embodiment, the multi-purpose mounting device includes an adapter member and a slide member coupled to the adapter member. The slide member is radially spaced apart from the adapter member to form an open slot, which is configured to receive a portion of the external structural therein to secure the multi-purpose mounting device to the airborne object. A first mounting surface is provided on one of the adapter member and the slide member and configured to support the electrical device.

Abstract: Compound antennas are disclosed, as are aircraft comprising compound antennas and methods to use compound antennas. In one embodiment, a compound antenna comprises a ground plane, a helix antenna element comprising a first dielectric core having a first end and a second end and coupled to the ground plane at the first end, the helix antenna element exhibiting a normal mode polarization pattern, and a conical spiral antenna element disposed proximate the helix antenna element, the conical spiral antenna element exhibiting an axial mode polarization pattern, wherein both the normal-mode and the axial mode patterns are circular polarization patterns and have the same sense. Other embodiments may be described.

Abstract: A unit includes a glidepath aerial and a support organ designed to be mounted on the front landing gear of an aircraft, with the landing gear forming an electrically conductive ground plane. The aerial is mounted on the support organ and is electrically insulated from this support organ by insulating elements. The support organ has a longitudinal dimension at least equal to around one quarter of the wavelength ? at which the aerial functions, so that the distance separating this aerial and the ground plane is greater than ?/4, and the aerial also has a transmission line designed to connect the aerial to a receiver in the aircraft. The transmission line is surrounded by an electromagnetic shielding element serving as a faradization screen for the transmission line, and designed to be electrically connected to the ground plane.

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: 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: 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: 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 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 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: 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 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: Compound antennas are disclosed, as are aircraft comprising compound antennas and methods to use compound antennas. In one embodiment, a compound antenna comprises a ground plane, a helix antenna element comprising a first dielectric core having a first end and a second end and coupled to the ground plane at the first end, the helix antenna element exhibiting a normal mode polarization pattern, and a conical spiral antenna element disposed proximate the helix antenna element, the conical spiral antenna element exhibiting an axial mode polarization pattern, wherein both the normal-mode and the axial mode patterns are circular polarization patterns and have the same sense. Other embodiments may be described.

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: Apparatus, systems and methods to transmit power and data are provided. A particular apparatus to transmit power and data includes a transmission medium. The transmission medium includes at least one first frequency selective surface (FSS) layer, at least one second FSS layer, and a dielectric layer separating the at least one first FSS layer and the at least one second FSS layer. In a particular embodiment, the apparatus also includes a first coupler coupled to the transmission medium to send a signal along the transmission medium and a second coupler coupled to the transmission medium. The second coupler may receive signals via the transmission medium, receive power via the transmission medium to power devices coupled to the second coupler, process and send data via the transmission medium, or any combination thereof.

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: 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: 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: 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: 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: 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.