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: A phased array antenna having a low profile (approximately ? wavelength) wide bandwidth (approximately 50%). The invention teaches making such an antenna using open channel resonators and monopole wave launchers. The wave launchers may conveniently be made on circuit card assemblies with strip lines that mimic coaxial cable monopole wave launchers. The channel resonators may be made in sections that are soldered to the circuit card assemblies. The circuit card assemblies have plated through holes that trace the edges of the resonator sections to provide electrical continuity.

Abstract: An apparatus and method for mounting a reflector antenna system on an outer surface of an aircraft which minimizes a swept arc of a main reflector. This allows the effective frontal area of the main reflector to be reduced such that a radome with a smaller frontal area can be employed to cover the antenna system. The preferred embodiments make use of a platform which rotates the main reflector about an azimuthal axis which is disposed forwardly of an axial center of the main reflector. In one embodiment, the azimuthal axis is located in a plane extending between the outermost lateral edges of the main reflector. In another embodiment the azimuthal axis is located forwardly of the outermost lateral edges of the main reflector.

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 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 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 antenna system comprises a Gatelink antenna (1), a Satcom Ku antenna (2), a Satcom Inmarsat antenna (3) positioned on a support that is mobile (5) in rotation and/or in translation and a device for the protection (6) of the antennas. Application to an airliner.

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: Conductive structures, including aircraft antennae and associated methods of formation, are disclosed. An antenna in accordance with one embodiment of the invention can include a flexible circuit material having a substrate and at least one conductive layer adjacent to the substrate. The flexible circuit material can be rolled to form a cylindrical or partially cylindrical antenna, such as a dipole antenna. The conductive material can further include circuit elements, such as leads, conductive lines, vias, and/or other elements electrically coupled to the antenna. The flexible circuit material can also support a transmitter and/or receiver that is coupled to the antenna via the circuitry. Accordingly, the antenna can be formed integrally with the circuitry and can be configured and positioned for enhanced signal reception and/or transmission.

Abstract: A system for calibrating airborne direction finding antenna arrays eliminates the problem of trying to maintain a constant depression angle when flying an airplane directly over a calibration antenna to collect deep depression angle data. The deep depression angle data necessary for calibration is provided by data from a scale model of the aircraft having a direction-finding array which simulates the actual direction-finding array on the aircraft. In order to collect deep depression angle data, the model is pivoted through 360° while maintaining a controlled depression angle. Thus, it is unnecessary for calibration to actually fly a plane to attempt to obtain deep depression angle measurements. In the subject system, only a single depression set of data is required from the aircraft. Thus, with the exception of baseline shallow depression angle data from this plane, the calibration data comes strictly from the scale model, which is much more easily obtained.

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: The present invention provides an antenna assembly (10) comprising a plurality of planar tiles (20). Each of the tiles carries a planar array of sets (22) of antenna elements (47-50) arranged to be operated as a phased array antenna. The tiles are arranged in an orientation which is conformal to a contour of an underlying structure. In use, only those tiles which are capable of communication in the steered direction are enabled, while those which are not capable of communicating in the steered direction are not used.

Abstract: A millimeter wave beacon includes a millimeter wave transmitter that produces at least one signal and plurality of antennas, coupled to the millimeter wave transmitter, that each emit millimeter wave radiation in response to the at least one signal. In one embodiment, the antennas are constructed and oriented to produce an overlapping signal field in which millimeter wave radiation emitted from multiple of the antennas can be detected. The millimeter wave radiation can be pulsed to encode various information of interest. Determination of the direction of approach to the beacon is facilitated by multiple antennas transmitting signals having different pulse encodings and/or different frequencies.

Abstract: A switching circuit for use at the antenna of a multiband mobile cellular handset comprises an antenna port 10, a TX low band port 14, a TX high band port 12 and at least one RX port 16. A single pole, triple throw solid state voltage-controlled switch made up of four PIN diodes D1 to D4 selectively connects any one of the TX low band port, TX high band port and RX port to the antenna port. No diplexer is used to separate the low and high band parts o the circuit.

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: The invention is a sensor pod for mounting on the top surface of the fuselage of an aircraft. The pod it supported by right and left front supports and right and left rear supports that attach to the fuselage on either side of the longitudinal axis of the aircraft. A fifth structural support, aligned with the longitudinal axis of the aircraft, has a first end attached to the fuselage of the aircraft a second end attached to the sensor pod the aircraft.

Abstract: A system and method for providing wireless communication services to passengers of an aircraft through the use of a standard mobile telephone. A system of antennas on an air base station radiates above a horizontal plane in order to provide coverage for an aircraft flying through a service airspace. The air system may be conveniently overlaid on an existing terrestrial wireless system in order to share based station facilities. A stretched dome shaped antenna pattern provides 360 degrees of coverage in the horizontal plane. A cardioid direction antenna pattern in the horizontal plane provides coverage in a specific portion of the air space such as an air corridor. Various combinations of antennas, and transceivers are interconnected in order to provide the proper coverage, capacity and interference control requirements for a particular air cell.

Abstract: A phased array antenna system for an aircraft which allows a beam from the antenna to be scanned down to or below the horizon when the aircraft is traveling at high latitudes. The system comprises a conformal phased array antenna aperture mounted on either a top, port or a starboard side of a fuselage of the aircraft, and at least one feedhorn mounted either in a blade secured to the fuselage or in a leading edge of a horizontal stabilizer of the aircraft. The feedhorn illuminates the conformal antenna aperture and the aperture projects a beam therefrom which can be more easily directed at targets at or below the horizon. The invention allows smaller antenna apertures to be used to scan a beam toward the horizon.

Abstract: An antenna array includes two pairs of linear polarized antennas mounted to a perimeter portion of an airframe with one pair having a polarization normal to the airframe and the other pair having a polarization tangential to the airframe. The antenna array eliminates the cross-polarization problem of an electromagnetic wave incident upon the array when using linear polarized perimeter mounted antennas.

Abstract: An antenna system consisting of parabolic rectangular reflectors disposed contiguously in a linear array. The use of parabolic rectangular reflectors permits the reflectors to form a larger common rectangular aperture without gaps in illumination. The contiguous array of parabolic rectangular reflectors permits a lower profile which is ideal for use on an aircraft. Each parabolic rectangular reflector has its own feed system and each of the feeds are excited in phase. The combined radiation patterns of the parabolic reflectors produces a beam with a narrow width. This narrow beamwidth permits the system to communicate with one source while filtering out signals coming from other sources. In one embodiment, the antenna system may be mechanically steered in order to communicate with a transmitter and/or receiver whose relative position is continuously varying with respect to the antenna system.

Abstract: A millimeter wave beacon includes a millimeter wave transmitter that produces at least one signal and plurality of antennas, coupled to the millimeter wave transmitter, that each emit millimeter wave radiation in response to the at least one signal. In one embodiment, the antennas are constructed and oriented to produce an overlapping signal field in which millimeter wave radiation emitted from multiple of the antennas can be detected. The millimeter wave radiation can be pulsed to encode various information of interest. Determination of the direction of approach to the beacon is facilitated by multiple antennas transmitting signals having different pulse encodings and/or different frequencies.

Abstract: A multi-reflector antenna array capable of simultaneously transmitting and receiving communication signals at Ku-band frequencies is mounted on an exterior surface of an aircraft. The antenna array provides four cassegrain reflector antennas mechanically connected together in a group capable of being simultaneously mechanically scanned. A common support structure fixes the antennas with respect to each other. A drive mechanism and directional azimuth and elevation motors control the position of the array. The aerodynamic drag of the array is minimized using four antennas rather than a single large diameter antenna. Each antenna is positioned on a common horizontal centerline. Two centrally located antennas are positioned between two smaller diameter antennas. The antennas and positioning equipment are both mounted for rotation within a radome. A corporate power combiner/divider is provided to adjust both an amplitude and a phase of each antenna signal.

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).

Abstract: An antenna system comprises a Gatelink antenna (1), a Satcom Ku antenna (2), a Satcom Inmarsat antenna (3) positioned on a support that is mobile (5) in rotation and/or in translation and a device for the protection (6) of the antennas. Application to an airliner.

Abstract: A multi-reflector antenna array capable of simultaneously transmitting and receiving communication signals at Ku-band frequencies is mounted on an exterior surface of an aircraft. The antenna array provides four cassegrain reflector antennas mechanically connected together in a group capable of being simultaneously mechanically scanned. A common support structure fixes the antennas with respect to each other. A drive mechanism and directional azimuth and elevation motors control the position of the array. The aerodynamic drag of the array is minimized using four antennas rather than a single large diameter antenna. Each antenna is positioned on a common horizontal centerline. Two centrally located antennas are positioned between two smaller diameter antennas. The antennas and positioning equipment are both mounted for rotation within a radome. A corporate power combiner/divider is provided to adjust both an amplitude and a phase of each antenna signal.

Abstract: This patent application is for Tim Hunter for the sole purpose of attaining a patent for the antenna described in this document.

Abstract: An airborne repeater antenna array (70) in which beams transmitted from multiple antenna elements (80) of the array to form terrestrial communications. cells are shaped according to predetermined system parameters. At least one of airplane telemetry data (58) indicating an airplane flight pattern location, adjacent cellular system beam footprint data, and call distribution load within a terrestrial cell are received, and a complex gain is dynamically computed for each of the multiple antenna elements based on such data to thereby output a plurality of beams that form desired geographic communications coverage cells (100, 102, 104, 108).

Abstract: A folded microstrip antenna for a flight aggregate or aircraft can be arranged around edges of thin structural parts, such as wings, tail units or control flaps, such that its surface is identical with the structure and folding takes place at the edge of the structure. The antenna is constructed such that its characteristic impedance is much higher at the folding edge than at ends of the structural antenna away from the edge. As a result, an approximately omnidirectional characteristic can be achieved.

Abstract: A microstrip telemetry antenna adapted for use on a small diameter projectile. The antenna includes a filter integrally formed with the antenna. The antenna also has a first pair of tuning tabs and a second pair of tuning tabs which are approximately perpendicular to one another and which allow the antenna to tuned within the S-band of 2.2 to 2.3 GHz.

Abstract: A microstrip antenna system having a GPS antenna for receiving GPS data, a telemetry antenna for transmitting telemetry data, a Flight Termination System antenna which receives an RF signal having a set of decoder tones and a beacon tracking antenna for providing an RF signal to allow tracking of the device utilizing the microstrip antenna system. The microstrip antenna system is designed for use on a missile.

Abstract: A compact aircraft antenna for reception of GPS signals includes eight elements to provide eight antenna patterns usable for anti-jam signal processing. Four bent monopole elements are configured with vertical portions and horizontal inward-extending portions. The bent monopole elements are arranged for multimode excitation to provide a primary progressive phase omnidirectional right-hand circularly-polarized antenna pattern for basic signal GPS signal reception. Multimode excitation of the bent monopoles also provides omnidirectional left-hand circularly-polarized, uniform phase omnidirectional, and clover leaf auxiliary antenna patterns. Four individual slot element figure-eight type auxiliary antenna patterns are also provided. With availability of these primary and auxiliary patterns, adaptive type anti-jam processing can be employed to actively provide reduced-gain antenna pattern notches or nulls at incident angles of interference or jamming signals.

Abstract: A GPS conformal adapted for use on a small diameter projectile. The antenna includes a GPS antenna array of six driven elements The antenna also has an antenna cover which includes a parasitic element aligned the six driven elements. The electric field coupling between the parasitic element and the driven elements produces an omnidirectional radiation pattern.

Abstract: A microwave reflector antenna for use on an aircraft. The microwave reflector antenna has a stationary plate that is attached to and stationary relative to the aircraft. A rotary plate rotates relative to the stationary plate about an azimuth axis. A rotary joint is attached to the rotary plate and has an axis of rotation that is aligned with the azimuth axis. A reflector is attached to the rotary plate adjacent the rotary joint so that the azimuth axis does not intersect the reflector. Individual ball bearings are positioned between the rotary plate and the stationary plate to allow the rotary plate to rotate about the azimuth axis. The stationary plate has gear teeth positioned along a peripheral side wall of the stationary plate. An azimuth motor is attached to the rotary plate and engaged with the gear teeth to selectively rotate the rotary plate about the azimuth axis.

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: A phased array antenna system for an aircraft which allows a beam from the antenna to be scanned down to or below the horizon when the aircraft is traveling at high latitudes. The system comprises a conformal phased array antenna aperture mounted on either a top, port or a starboard side of a fuselage of the aircraft, and at least one feedhorn mounted either in a blade secured to the fuselage or in a leading edge of a horizontal stabilizer of the aircraft. The feedhorn illuminates the conformal antenna aperture and the aperture projects a beam therefrom which can be more easily directed at targets at or below the horizon. The invention allows smaller antenna apertures to be used to scan a beam toward the horizon.

Abstract: A microwave antenna for an aircraft including a reflector element with a front surface and a rear surface. A horn is mounted to the front surface of the reflector element and an orthomode transducer is mounted to the rear surface of the reflector element. The orthomode transducer is coupled to the horn. Solid state power amplifiers that amplify a microwave signal to be transmitted and low noise amplifiers that amplify a received microwave signal are coupled to the orthomode transducer. The solid state amplifiers and the low noise amplifiers are also located on the rear surface of the reflector element.

Abstract: A reflector 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 on which the radome is mounted. In one preferred embodiment the radome includes a base portion which is covered with a cover of radar absorbing material (RAM). In another embodiment the radome includes a curved base portion which is adapted to match the curvature of the surface of the mobile platform on which the reflector is mounted.

Abstract: A stratospheric platform communication system (10) having antenna boresight angles (EL, AZ) that can be adjusted by an adjustable payload antenna (40) according to the requirements of a specific application. The present invention provides an efficient use of available resources by allowing platform systems (10) and GEO satellite systems to share the radio frequency spectrum without interference, and improves the coverage area provided by a stratospheric platform system by allocating stratospheric platforms (12) to specific coverage areas in combination thereby increasing coverage capacity in high traffic areas.

Abstract: A microwave reflector antenna comprises a rotary plate that rotates about an azimuth axis. At least one elevation cradle is attached to the rotary plate to provide an elevation axis and rotates about the azimuth axis with the rotation of the rotary plate. The at least one elevation cradle has a curved guide with a plurality of ball bearings to facilitate the rotation of the reflector about the elevation axis. A reflector travels along the at least one cradle as the reflector rotates about the elevation axis. The reflector rotates about the azimuth axis with the rotation of the at least one cradle. The rotation of the reflector about the azimuth axis and about the elevation axis define a swept volume of the reflector. The at least one cradle is positioned on the rotary plate so that the at least one cradle is within the swept volume of the reflector.

Abstract: A microwave reflector antenna for use on an aircraft. The microwave reflector antenna has a stationary plate that is attached to and stationary relative to the aircraft. A rotary plate rotates relative to the stationary plate about an azimuth axis. A rotary joint is attached to the rotary plate and has an axis of rotation that is aligned with the azimuth axis. A reflector is attached to the rotary plate adjacent the rotary joint so that the azimuth axis does not intersect the reflector. Individual ball bearings are positioned between the rotary plate and the stationary plate to allow the rotary plate to rotate about the azimuth axis. The stationary plate has gear teeth positioned along a peripheral side wall of the stationary plate. An azimuth motor is attached to the rotary plate and engaged with the gear teeth to selectively rotate the rotary plate about the azimuth axis.

Abstract: A microstrip antenna system having a GPS antenna for receiving GPS data and a telemetry antenna for transmitting telemetry data mounted on a dielectric substrate. The microstrip antenna system is designed for use on small diameter airborne projectiles which have a diameter of about 2.75 inches. A pair of band stop filters are integrated into the antenna system to isolate the transmitted telemetry signal from the received GPS signal.

Abstract: A reflector 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 on which the radome is mounted. In one preferred embodiment the radome includes a base portion which is covered with a cover of radar absorbing material (RAM). In another embodiment the radome includes a curved base portion which is adapted to match the curvature of the surface of the mobile platform on which the reflector is mounted.

Abstract: A radar antenna for a guided missile is calibrated in flight using a point source of microwave radiation and a lens to emulate a far field source. The microwave source and lens fit behind a metal cap at the leading end of the radome and so do not adversely affect the radar. A variety of techniques to power the point source are disclosed, and a variety of lens arrangements are disclosed. The invention allows a radar antenna to be calibrated in flight, and so insures against mis-calibration due to aging components as well as the heat and mechanical forces associated with storage and/or launch of the missile.

Abstract: An array antenna including: a frame having a two-dimensional array of a plurality of openings; an electromagnetically radiating tile disposed in each opening; and mounting means for holding at least one tile in a corresponding opening of the frame, each of the mounting means comprising at least two biasing members, each biasing member exerting a biasing force on the tile relative to the frame. Preferably, each biasing member is a leaf spring having first and second ends attached to the frame and a bowed section attached to the tile. Furthermore, it is preferred that each biasing member further have a way to vary the biasing force with temperature, such as fabricating the bow portion from a first and second material, each having a different coefficient of thermal expansion. Also provided is a spacecraft which utilizes the array antenna of the present invention.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: The present invention provides an antenna assembly (10) comprising a plurality of planar tiles (20). Each of the tiles carries a planar array of sets (22) of antenna elements (47-50) arranged to be operated as a phased array antenna. The tiles are arranged in an orientation which is conformal to a contour of an underlying structure. In use, only those tiles which are capable of communication in the steered direction are enabled, while those which are not capable of communicating in the steered direction are not used.

Abstract: An in-flight entertainment system provides live video/audio programming to passengers and operators over an aircraft video/audio distribution system. The programming signals are derived from satellite broadcast signals that may be in either circular polarized form or linear polarized form. The broadcast signals are collected by two probes and extracted as right and left circular polarized signals. The right and left circular polarized signals are converted into either circular or linear polarized IF signals, and the IF signals are processed by a receiver/decoder unit to produce the live video/audio programming signals.

Abstract: This invention relates to an antenna for transmission/reception of radio frequency waves that comprises:

Abstract: An elevation angle detection device uses signals from first and second of oppositely pointing antennas to determine an elevation angle of an emitting source. The signal from the second antenna is inverted and phase-compared with the direct signal from the first antenna. The first and second antennas are physically displaced along their axes by about ⅜ electrical wavelengths to establish a sensitive angular region of about ±7 degrees. In one embodiment of the invention, the phase of the signal from the first antenna is phase delayed slightly before being applied to the phase detector. This displaces the sensitive angular region upward. The phase of the signal from the second antenna is phase delayed slightly before being applied to a second phase detector. The signal from the first antenna is applied to the second phase detector without being phase delayed. This displaces the sensitive angular region downward.

Abstract: Antenna carrier comprising antenna elements to be connected to an air vehicle, said antenna carrier projecting from a mounting area forwards or rearwards seen in the travelling direction of the air vehicle. The antenna carrier comprises an elongate front part (3), which comprises a flexurally rigid shell (6); an elongate, pliable mounting part (2), which at its front end (11) connects to the front part (3); a front mounting point (13) via which a front part of the mounting part (2) is connected to the air vehicle; and a rear mounting point (14) via which a rear part of the mounting part (2) is connected to the air vehicle. The flexural rigidity of the shell (6) of the front part and the mounting part (2) is adjusted in such manner that the eigenfrequencies of the antenna carrier are well separated from the critical eigenfrequencies of the air vehicle.