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: 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 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: A method of producing polymer/nanotube composites where the density and position of the nanotubes within the composite can be controlled. Carbon nanotubes are grown from organometallic micropatterns. These periodic nanotube arrays are then incorporated into a polymer matrix by depositing a curable polymer film on the as-grown tubes. This controlled method of producing free-standing nanotube/polymer composite films may be used to form nanosensors which provide information regarding a physical condition of a material, such as an airplane chassis or wing, in contact with the nanosensor.

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: An aircraft wing that includes a conductive ground plane adjacent the wingtip, where the ground plane conforms to an aerodynamic surface of the wing. Because the ground plane conforms to the aerodynamic surface, it has minimal impact on the aerodynamics of the wing. The ground plane can be part of a wingtip device that is detachably secured to the tip of a main wing portion. The ground plane described herein can be used on any aircraft wing structure that employs an antenna including, but not limited to, a wing of a UAV.

Abstract: The present invention antenna preserves the general size and form factor of the prior art loop antennas while providing the benefits of multiple point feeds at less than one wavelength in separation of feed points. The invention antenna obtains omnidirectional radiation and improved efficiency over the prior art by way of dual slotted, open ended cylindrical or rectangular box structures fed with high impedance feed lines.

Abstract: An antenna arrangement, method, and cellular communications system for transmitting and receiving signals between a base station tower, ground-based mobile subscribers, and an aircraft. The antenna arrangement includes a vertically oriented array of antenna elements, and a feedline arrangement that feeds the antenna elements with progressively phase-retarded signals, thereby generating an elevated antenna beam directed upward toward the aircraft and away from the ground-based mobile subscribers. In one embodiment, the antenna arrangement also generates a horizontal antenna beam for communicating with the ground-based subscribers. The horizontal beam and the elevated beam are sufficiently separated in elevation to prevent mutual interference when using the same frequency spectrum.

Abstract: An antenna structure integrated in a hull or fuselage. The hull or fuselage can be the outer surface of an aircraft, artillery shell, missile or ship. The antenna structure includes an array antenna. The array antenna includes a number of antenna elements. Each antenna element includes a radiator and an RF feed. The antenna elements are arranged in a lattice within an antenna area including a central antenna area and a transition region outside the central antenna area wherein a number of the antenna radiators as well as resistive sheets are arranged in substantially the same plane as a surrounding outer surface of the hull or fuselage.

Abstract: A line of sight antenna supported in an upturned terminal winglet or similar vertical member of an aircraft is disclosed. An aperture is formed in the conductive winglet or vertical member, and the antenna is supported within the aperture by a support mechanism such that the antenna is exposed to the line of sight transmissions. A non-conductive covering may also be used for the aperture. Using the cover, the antenna within the winglet can be configured so that it does not alter the appearance or aerodynamic characteristics of the aircraft. Alternatively, the antenna can be coupled to the outside of the winglet or vertical member if cosmetics are not a concern. The frequency range of the antenna can be tuned to cover desired frequency ranges. The antenna position at the winglet maintains a large physical separation from fuselage-mounted antennas thereby reducing interference.

Abstract: A method of assembling an external telemetry unit for a projectile comprising the steps of providing a shell whose inside is formed to match the contour of the projectile body, encircling the front of the shell with a flexible battery and flexible electronic circuitry, and covering the flexible battery and flexible electronic circuitry with a plurality of contoured antennas. Also disclosed is a method of using an external telemetry unit comprising the steps of removing the fuze from a projectile having a projectile body and a fuze, sliding the unit over the front of the projectile body; reinstalling the fuze, firing the projectile, and observing the projectile data transmitted by the unit.

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

Abstract: An antenna for a micro air vehicle (MAV) takes the form of a wrap-around antenna (e.g., wrapped around a portion of the MAV) that selectively emits radio signals in different directions depending on a frequency selected by a radio altimeter in the MAV. The radar altimeter may be a pulsed or a frequency modulated continuous wave (FMCW) radar altimeter. The wrap-around antenna includes groups of radiating elements in which at least each group includes an average height that is different from an average height of an adjacent group. Further, the average height of the group determines which group will emit the signals most efficiently so that a desired sector of space may be covered by the signals emitted from the antenna. In one example, the center frequency of the radar altimeter may be controlled in a deterministic manner to cause the radiating elements to successively cover desired sectors of space.

Abstract: A wall element for emitting high-frequency radiation for an aircraft comprises an antenna device. The antenna device is adapted for emitting high frequency radiation. Furthermore, the antenna device is integrated in the wall element.

Abstract: A frame assembly for a composite panel includes a first frame having a first frame contact surface transverse to a first frame mount surface and a second frame having a second frame contact surface transverse to a second frame mount surface, the first frame mount surface receivable within the second frame mount surface to provide a conductive communication path therebetween.

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: Antenna system embodiments are shown which are especially suited for mounting on aircraft and for operation across widely-spaced frequency bands. Embodiments include blade members positioned in a ring arrangement and tuning circuits that are each coupled between a respective pair of the blade members and configured to successively remove blade members from operation as the operational frequency increases.

Abstract: An aircraft has a fuselage and a pair of wings joined to the fuselage at a dihedral angle. A wing extension, such as an angled winglet or a wing-tip pod, is joined to a distal end of each of the wings. A top-surface antenna lies in each of the top surfaces, and a bottom-surface antenna lies in each of the bottom surfaces. The antennas are preferably flat-panel antennas such as phased-array antennas.

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

Abstract: A lightweight broadband blade antenna assembly is incorporated into the surface of an airfoil, such as a structure component of an aircraft, or a separate airfoil (blade antenna) attached thereto. A first metallized area is formed on the airfoil adjacent a leading edge of the airfoil. A second metallized area is formed on trailing edge of the airfoil and is spaced from the first metallized area by a first gap which is configured to provide a capacitive coupling between the first and second metallized areas. A third metallized area is formed on the cap portion of the airfoil and is spaced from the first metallized area by a second gap and is electrically connected in series with the first and second metallized areas. RLC circuits are electrically connected across tuning gaps formed in the third metallized area to provide a broadband response.

Abstract: The present invention is an improved antenna system. In an embodiment of the invention, the antenna system of the present invention may be a dielectric resonator antenna which may include a dielectric cap that may surround a plurality of feed probes. The antenna system may be suitable for coupling to a projectile whereby the dielectric cap forms a front end, or nose, of the projectile. The plurality of feed probes may produce orthogonal vector components of a field to provide circular polarization. Additionally, feed probes may be optimally spaced within the dielectric cap to ensure the phase center of the antenna system may be co-located with a platform axis of rotation whereby no carrier phase rollup compensation may be required.

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: A choke ring apparatus for attenuation of electromagnetic waves in a mobile platform fuselage includes a ground plane mounted on a surface of the fuselage. The choke ring has an axial circular window and a series of concentric circular ring segments on the ground plane arranged coaxially about the axis of the window. The circular ring segments extend from the ground plane. The ring segments defining at least one groove therebetween. The ring segments have a flat ridge at the edge, and each groove has a depth defined by a pair of adjacent ring segments. The width of the flat ridge surfaces and a width of the groove between adjacent ring segments are approximately equal. The depth of the groove is determined based on a predetermined resonant frequency, such that the choke ring apparatus selectively attenuates electromagnetic waves in a region of the resonant frequency when propagating through the window.

Abstract: A shunt antenna mountable on an aircraft comprises a lower plate, an antenna element formed above the lower plate and integrated within a dorsal fin of the aircraft where the antenna element is substantially slant relative to the lower plate; one or more couplers formed on the lower plate and operatively connected to a lower forward end of the antenna element. The couplers transmit radio frequency signals to the antenna element, and the antenna element and the lower plate are separated by air to produce a capacitor effect.

Abstract: The invention relates to an aircraft undercarriage including at least one axle having at least one wheel mounted to rotate thereon, the undercarriage including a communication device for connecting a sensor mounted on a rim of the wheel to stationary processing means mounted on the aircraft, the communication device comprising a rotary antenna mounted on the wheel rim to rotate therewith and connected to the sensor, and a stationary antenna facing said rotary antenna so that the antennae are in electromagnetic relation, said stationary antenna being connected to the processing means, wherein the stationary antenna and the rotary antenna extend on the inner side of the wheel facing the undercarriage.

Abstract: A lightweight broadband blade antenna assembly is incorporated into the surface of an airfoil, such as a structure component of an aircraft, or a separate airfoil (blade antenna) attached thereto. A first metallized area is formed on the airfoil adjacent a leading edge of the airfoil. A second metallized area is formed on trailing edge of the airfoil and is spaced from the first metallized area by a first gap which is configured to provide a capacitive coupling between the first and second metallized areas. A third metallized area is formed on the cap portion of the airfoil and is spaced from the first metallized area by a second gap and is electrically connected in series with the first and second metallized areas. RLC circuits are electrically connected across tuning gaps formed in the third metallized area to provide a broadband response.

Abstract: In the case of the electromagnetic waves of a band with a short wavelength, in an antenna opening, the technical subject which conflicts between loss of electromagnetic waves and the mechanical strength of a member exists. This invention was made in view of such a problem, and aims at offering a radome with little cover of electromagnetic waves, absorption of electromagnetic waves, and dispersion of electromagnetic waves by the member of a radome. It aims at offering a strong and lightweight radome cheaply.

Abstract: A vehicle equipped with an on-vehicle telecommunication system having an electromagnetic field shielding case installed in the vehicle and for housing a user portable communication device, which has a first communication module permitting, via a first antenna, short-range radio-frequency transmission and reception, and a second antenna permitting long-range radio-frequency transmission and reception to and from a remote radio-base station.

Abstract: A conformal antenna comprising: an electrically neutral airframe; metalized fabric covering said airframe; and transmission lines attached to said metalized fabric to connect to a transceiver.

Abstract: A shunt antenna mountable on an aircraft comprises a lower plate, an antenna element formed above the lower plate and integrated within a dorsal fin of the aircraft where the antenna element is substantially slant relative to the lower plate; one or more couplers formed on the lower plate and operatively connected to a lower forward end of the antenna element. The couplers transmit radio frequency signals to the antenna element, and the antenna element and the lower plate are separated by air to produce a capacitor effect.

Abstract: A microstrip antenna configured to wrap around a projectile's body without interfering with the aerodynamic design of the projectile. The microstrip antenna has three identical conformal antenna elements equally spaced around the circumference of the projectile's body. The antenna has an operating frequency of 241.2 MHz or 231.0 MHz, a maximum diameter of ten inches and a maximum length of nine inches.

Abstract: A choke ring apparatus for attenuation of electromagnetic waves in a mobile platform fuselage includes a ground plane mounted on a surface of the fuselage. The choke ring has an axial circular window and a series of concentric circular ring segments on the ground plane arranged coaxially about the axis of the window. The circular ring segments extend from the ground plane. The ring segments defining at least one groove therebetween. The ring segments have a flat ridge at the edge, and each groove has a depth defined by a pair of adjacent ring segments. The width of the flat ridge surfaces and a width of the groove between adjacent ring segments are approximately equal. The depth of the groove is determined based on a predetermined resonant frequency, such that the choke ring apparatus selectively attenuates electromagnetic waves in a region of the resonant frequency when propagating through the window.

Abstract: This invention relates to an apparatus for emission and/or reception of electromagnetic waves for aerodynes, characterised in that it comprises a blade antenna on the top of the fuselage of the aerodyne, a principal reflect-array arranged horizontally at the bottom of the blade antenna, a principal illumination horn arranged at the summit of the blade antenna, the horn illuminating the principal reflect-array, two secondary reflect-arrays arranged vertically on each side of the faces of the blade antenna, two secondary illumination horns arranged at the bottom of the blade antenna in the plane of the principal reflect-array, each horn illuminating one of the secondary reflect-arrays, each reflect-array reflecting waves emitted by the illumination horn illuminating it.

Abstract: Disclosed are antenna embodiments and air vehicles so equipped that include a first antenna component, and a second antenna component, separated by a free space gap, where the antenna embodiments are adapted to capacitively couple the first antenna component and the second antenna component across one or more portions of the free space gap and where the first antenna component member has a degree or axis of rotation, relative to the second antenna component.

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

Abstract: An external telemetry unit for a projectile. The external telemetry unit comprises a shell adapted to be inserted between the front of the projectile body and the fuze, a flexible battery and flexible electronic circuitry encircling the front of the shell, and a plurality of contoured antennas covering the flexible battery and flexible electronic circuitry. The inside of the shell is formed to match the contour of the projectile.

Abstract: An aircraft phased array antenna system has transmit and receive antenna structures externally mounted on the aircraft fuselage. Each antenna comprises a plurality of phased array elements and antenna power and support equipment. Aerodynamically shaping antenna structure to enclose an antenna element grid provides additional antenna structure volume, which is efficiently utilized by locating antenna support equipment within the antenna structure. To control signal attenuation a receive antenna internal converter converts receive frequency signals to L-band frequency signals for aircraft use, and a similar transmit antenna converter converts L-band frequency signals to transmit frequency signals, thus unconstraining antenna to internal aircraft equipment spacing. To reduce power loss and cabling weight, antenna operating power is first generated in the 28 to 270 volts DC range within the aircraft, and locally converted in each antenna to the 3 to 6 volt DC power to operate each antenna's phased array elements.

Abstract: An object deflection system includes at least one sensor for detecting an impending impact of a first object with a second object. The sensor communicates with a deflector deployment device to substantially instantaneously activate the deflector deployment device upon detecting the impending impact. When activated, the deflector deployment device substantially instantaneously deploys a deflector so that the first object impacts the deflector. The first object is therefore deflected by the deflector and prevented from impacting second object.

Abstract: A projectile (12) carries a combination antenna (21), whose tuning corresponds to both the fundamental frequency of the radar (17) of a proximity fuse and the third harmonic of the carrier frequency of a satellite navigation receiver (20), in its replaceable tip (11) under its ballistic radome hood (14), so that both systems may be operated via this one combination antenna (21). For the decoupling, the radar range finder (18) is only put into operation when the navigation receiver (20) has been switched off because the projectile (12) has arrived over the target area on its corrected flight path.

Abstract: An aircraft antenna includes an aerodynamic housing structured for attachment to an outer surface of an aircraft, and the housing contains an electromagnetic radiator and tuned over a first band of frequencies potentially to produce secondary radiations in at least a second band of frequencies, and a suppression filter effective at the frequencies of the secondary radiations.

Abstract: The invention relates to antenna elements for the UHF and VHF range for antennas of an airborne vehicle with empennage parts. These antenna elements are integrated into the empennage parts (L) which are made of a dielectric material and are configured in such a way that they radiate directionally broadband in flight direction. The empennage parts are made, for example, of ceramic, and the antenna elements are embedded therein or are applied to their surface. The antenna elements (A) are preferably expanding Vivaldi-type slot radiators that are halved along their axis of symmetry and use the airborne vehicle (F) as an electrical mirror. Arranging the antenna elements in the area of the rudder maximizes both the aperture and the distance between the phase centers of the individual elements, but no additional volume is required for the antennas.

Abstract: A low radar cross-section monocone antenna is provided with an ultra-wide bandwidth in the microwave region of the electromagnetic spectrum running from 1 gigahertz to 18 gigahertz by decreasing the low frequency cutoff through enlarging the overall dimensions of the cone while at the same time maintaining the base diameter of the apex of the cone to the initially-set dimension that establishes the high frequency cutoff of the antenna. The apex of this cone that serves as its feed point has a base diameter that results in the wide bandwidth, with the monocone antenna having a 5 dBi gain and omnidirectional coverage.

Abstract: A multi-band blade antenna for use on a vehicle is formed by patterning the metal on both sides of a printed circuit board. One side is patterned into low-frequency patch and ground elements, and the other side is patterned into high-frequency patch and ground elements. The length of the patterned patch element on the low-frequency side of the board approximates the length of the board, while the effective length of the high-frequency patch element is approximately twice as long. Tuning for the frequency bands of mobile telephones in different regions (for instance, the European Union, United States and Japan) is by means of differences in slot length in the patch member on the low-frequency side, and differences in separation between the patch and ground members on the high-frequency side. RLC components are affixed to the low-frequency side after patterning. The printed circuit board has a shape which, in a complementary housing, may add ornamentation to the exterior of a vehicle on which it is mounted.

Abstract: An attenuation device for use under a radome disposed on a mobile platform such as an aircraft for reflecting a portion of the electromagnetic energy radiated by an antenna disposed under the radome such that the reflected portion of energy impinges the radome at an angle normal thereto, thereby reducing or eliminating further reflections of the reflected portion of energy within the radome toward the mobile platform. In one embodiment the radome includes a base covered with a radar absorbing material (RAM). In another embodiment the radome includes a curved base adapted to match the mobile platform surface curvature on which the attenuation apparatus is mounted. In a further embodiment, RAM is disposed on an exterior surface of the mobile platform under the radome. In still another embodiment, the base is formed of an attenuating transverse magnetic TM wave corrugated plate.

Abstract: An antenna system is disclosed including a GPS antenna which is driven by an articulator in an opposite direction to aircraft roll. Aircraft roll is sensed by an onboard navigation system and translation module sends a signal to a processor which provides a drive signal to the articulator. As the aircraft rolls in one direction, the antenna is driven oppositely to maintain the vertical orientation of the antenna.

Abstract: An aircraft phased array antenna system has transmit and receive antenna structures externally mounted on the aircraft fuselage. Each antenna comprises a plurality of phased array elements and antenna power and support equipment. Aerodynamically shaping antenna structure to enclose an antenna element grid provides additional antenna structure volume, which is efficiently utilized by locating antenna support equipment within the antenna structure. To control signal attenuation a receive antenna internal converter converts receive frequency signals to L-band frequency signals for aircraft use, and a similar transmit antenna converter converts L-band frequency signals to transmit frequency signals, thus unconstraining antenna to internal aircraft equipment spacing. To reduce power loss and cabling weight, antenna operating power is first generated in the 28 to 270 volts DC range within the aircraft, and locally converted in each antenna to the 3 to 6 volt DC power to operate each antenna's phased array elements.

Abstract: The invention relates to antenna elements for the UHF and VHF range for antennas of an airborne vehicle with empennage parts. These antenna elements are integrated into the empennage parts (L) which are made of a dielectric material and are configured in such a way that they radiate directionally broadband in flight direction. The empennage parts are made, for example, of ceramic, and the antenna elements are embedded therein or are applied to their surface.

Abstract: An antenna is described which includes first, second, and third conductive layers and a first and second laminate to separate the layers. The laminates are configured with plated through holes to provide contact between the first and third layers, the holes defining antenna cavities, the second conductive layers being the antenna. A plurality of slots in the first conductive layer align within the defined antenna cavities, further defining the antenna cavities for the second conductive layer.

Abstract: An aircraft in-flight entertainment system includes a satellite TV receiver, at least one video display connected to the receiver, and a multi-beam antenna on the aircraft for receiving signals from a plurality of satellite TV transponders. The multi-beam antenna may have right-hand circularly polarized (RHCP) and left-hand circularly polarized (LHCP) beams offset from one another by a beam offset angle. The beam offset angle may be less than an angle defined by the spacing of the DBS transponders. The system may also include an antenna steering positioner connected to the multi-beam antenna, and an antenna steering controller for steering the multi-beam antenna based upon received signals from at least one of the RHCP and LHCP beams. The antenna steering controller may comprise a processor for steering the multi-beam antenna based on a selected master one of the RHCP and LHCP beams and slaving the other beam therefrom.

Abstract: This invention relates to an aircraft using such an antenna comprises: a structural element (8) that is conducting in the operating frequency band of the antenna, with size equal to at least one quarter of the wave length along the polarization direction of the electromagnetic wave for the minimum frequency of this frequency band, and comprising a cutout forming a cavity (9); a removable exciting element (10) placed in this cavity that acts as an exciter of this cavity (9); and a metallization that is electrically conducting at the operating frequencies of the antenna providing metallization between the exciting element (10) and the structural element (8).