Abstract: Composite structures having an integral intelligent skin are made of one or more plies of a structural base material and an intelligent or smart film by molding one or more plies and the film into an integral unitary body with the intelligent film outermost. The intelligent or smart film contains or bears a functionally active or interactive component such as antennae, electronic sensors, electric and/or electronic circuitry, and/or spectrally tailored coatings. A method of making the composite structure in a very economical manner is disclosed.

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: Methods and apparatus for components according to various aspects of the present invention operate in conjunction with reaction bonded silicon nitride (RBSN). In one embodiment, a missile radome comprises a wall defining the radome body, including a base and a tip. The wall may comprise a core and one or more skins adjacent the core, such as in a sandwich configuration. The core and the skins may have different densities. The radome wall may be configured to transmit wideband RF signals. The RBSN may be extruded to form the radome.

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

Abstract: A selectable beam antenna of generally linear, polygonal, planar or polyhedral form, able to operate at microwave and millimetre wave frequencies, and constructed from associated networks that incorporate radio frequency switches, time delays and amplitude weights positioned within a set of interleaved transmission, lines or waveguides to simultaneously perform both beam-forming and beam selection operations, which selectable beam antenna comprises: (i) a single RP antenna port connected to a 1-to-N corporate feed means, where N is greater than or equal to 2; (ii) a EF switch network means of N/q multi-pole-multi-throw radio frequency switch means (qPMT) connected to the corporate feed means; (iii) a RF distribution means of N×M singularly or multiply interleaved lines arranged so as to have approximately equal transmission length connected to the switch means, where M is the number of throws associated with each radio frequency switch means (qPMT); (iv) an antenna launch means of M×M interleaved antenna elem

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: An antenna system for an airborne radar system. The antenna system has a number of first antenna elements and a microwave power distribution system comprising a plurality of first T/R-units being coupled to the first antenna elements for distribution of microwave power to the plurality of first antenna elements. The microwave power distribution system has an assembly of waveguides coupled to a plurality of second antenna elements directed at an angle essentially perpendicular to the number of first antenna elements, wherein the first T/R units are coupled to the waveguides for distribution of microwave energy to the second antenna elements.

Abstract: A radar system, including: a compact, active phased array antenna for transmission and reception of a focused radiation beam, circuits for providing signals to produce or detect a radiation beam by the phased array antenna and to control or detect the direction of the radiation beam, and wherein the radar is adapted to be mounted on a missile and scan a selected area proceeding the direction of motion of the missile.

Abstract: The present invention relates to an airborne radar (3) notably for a drone (1). The airborne radar (3) has: A first structure (4) is, mechanically attached to an aircraft (1) carrying the radar (3). The first structure (4) has a degree of rotational freedom relative to the aircraft (1) on a first axis (23). A second structure (5) is, attached to the first structure (4). The second structure (5) has a degree of rotational freedom relative to the first structure (4) on a second axis (26) converging with the first axis (23). An antenna (28) receives and sends electromagnetic waves, attached to the second structure (5). An electronic module (40, 41) processes the electromagnetic waves sent or received by the antenna (28). The electronic module (40, 41) is attached to the second structure (5). This invention finds its main application in the field of tactical drones.

Abstract: An airborne electromagnetic survey system for conducting geological mapping is disclosed. A transmitter closed loop structure is used in the system and is designed for connection to a towing airborne vehicle. The transmitter loop structure comprises a plurality of interconnected loop segments, and transmitting means are fitted to at least one of the loop segments for generating and transmitting an earthbound primary electromagnetic field effective for geological surveying. Sensing means are fitted to the loop segments for receiving and sensing a vertical component of a secondary resulting electromagnetic field which arises from an interaction of the primary electromagnetic field with ground bodies that are traversed by the sensing means, while simultaneously nulling the primary electromagnetic field.

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

Abstract: A 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 aircraft having an airframe made of a composite material is provided with an isolated ground in order to reduce the threat of electrical fires. The aircraft includes a voltage source and at least one electronic device mounted on the airframe. Further, a power wire isolated from the airframe interconnects the voltage source and the electronic device. Also, a ground wire isolated from the airframe interconnects the voltage source and the electronic device. As a result, the onboard electric circuits are isolated from the airframe. In order to reduce electromagnetic interference in the circuit, the aircraft may be provided with a powerside capacitor, to interconnect the power wire and the airframe, and a groundside capacitor, to interconnect the ground wire and the airframe.

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: The invention concerns a unit having a glidepath aerial (1) and a support organ (2) designed to be mounted on the front landing gear of an aircraft, with said landing gear forming an electrically conductive ground plane. According to the invention: this aerial (1) is mounted on the support organ (2) and is electrically insulated from this support organ (2) by insulating elements, the support organ (2) 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 (1) and the ground plane is greater than ?/4, and the aerial (1) also has a transmission line (13, 15) designed to connect the aerial (1) to a receiver in the aircraft; this transmission line (13, 15) is surrounding by an electromagnetic shielding element (12) serving as a faradization screen for the transmission line (13, 15), and this element is designed to be electrically connected to the ground plane.

Abstract: A tunable antenna comprises a conductor, a shunt inductance tuning element, a switch that controls the shunt inductance tuning element and the conductor, and a local ground connected to the shunt inductance tuning element. The switch is capable of activating the shunt inductance tuning element to change a frequency and bandwidth of the tunable antenna.

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

Abstract: A frequency selective surface-based (FSS-based) device (200) for processing electromagnetic waves providing at least a third-order response. The FSS-based device includes a first FSS (202), a second FSS (210), and a high quality factor (Q) FSS (206) interposed between the first and second FSSs. A first dielectric layer (204) and a second dielectric layer (208) separate the respective FSS layers. The first and second FSSs have first and second primary resonant frequencies, respectively. The high Q FSS has a lower primary resonant frequency relative to the first and second primary resonant frequencies. The overall electrical thickness of the PSS device can be <?/10. The high Q FSS has a loaded quality factor of at least thirty at the lower primary resonant frequency.

Abstract: An apparatus comprises a distributed array of antenna elements for receiving a radio frequency signal on a satellite communications link, wherein the radio frequency signal includes a known preamble; a plurality of mixers for translating the radio frequency signal to a plurality of baseband signals having in-phase and quadrature components; a processor for applying weights to the baseband signals, wherein the weights are found adaptively in response to the preamble in combination with decision-directed feedback when the preamble is not present; and a receiver for processing the weighted baseband signals. A pre-processor can be used to create sub-arrays of the antenna elements using maximal-ratio weighting. A method performed by the apparatus is also provided.

Abstract: A space-fed array is selectively operable in a reflective mode or in a feed-through mode. The array includes, in an exemplary embodiment, a primary array; and a feed array. The primary array includes a first side set of radiating elements, a first set of phase shifters, a set of switches, a second set of phase shifters and a second side set of radiating elements. Each of the switches is connected between corresponding ones of the first set and the second set of phase shifters and ground, selectively settable at an open position or at a closed position. The open position corresponds to the feed through mode, and the closed position corresponds to the reflective mode.

Abstract: The present invention relates to a device for locking a movable component of an aircraft. The device includes an electronic tag adapted for receiving a polling signal and returning an identification signal. The present invention also involves an on-board system allowing for detection of such locking devices.

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: 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 invention provides a novel, low-cost, spin-stabilized lander architecture capable (with appropriate system scaling tailored to the attributes of the target) of performing a soft-landing on a solar-system body such as Earth's Moon, Mars, Venus, the moons of Mars, Jupiter, Saturn, Uranus and Neptune, selected near-Earth and main-belt asteroids, comets and Kuiper belt objects and even large human-made objects, and also moving about on the surface of the target solar-system body after the initial landing in movement akin to hopping.

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

Abstract: A conformal end-fire antenna with a high impedance ground surface structure and an array of radiating elements formed thereon. The ground surface structure includes an array of metal protrusions on a electrically conductive sheet, the metal protrusions arranged in a two-dimensional lattice. The ground surface structure acts as a magnetic surface at an RF frequency band of interest, functioning as an electrical short at DC, and as a mirror which reflects an RF field in the frequency band with virtually no phase reversal.

Abstract: A conformal end-fire antenna with a high impedance ground surface structure and an array of radiating elements formed thereon. The ground surface structure includes an array of metal protrusions on a electrically conductive sheet, the metal protrusions arranged in a two-dimensional lattice. The ground surface structure acts as a magnetic surface at an RF frequency band of interest, functioning as an electrical short at DC, and as a mirror which reflects an RF field in the frequency band with virtually no phase reversal.

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

Abstract: A polygonal cylindrically shaped phased array antenna forming a radar has an active aperture that focuses in any of one or more angular azimuth directions without inertia. It further includes adjacent multiple similar polygonal staves joined along their vertical edges to form a right regular polygonal cylinder. Each stave is further decomposed into flat panels, wherein each panel has a plurality of antenna elements positioned in a regular rectangular or triangular lattice. Each panel contains a beam forming network that electronically forms and steers an electromagnetic beam for purposes of transmission and subsequent reception. The panels optionally may operate as autonomous radars which when coherently combined form multiple larger antenna apertures, each capable of operating autonomously. A switching network allows transmit power and all requisite radar and control signals to be sent to and received from a selected set of panels anywhere on the polygonal cylinder.

Abstract: Methods and apparatus for components according to various aspects of the present invention operate in conjunction with reaction bonded silicon nitride (RBSN). In one embodiment, a missile radome comprises a wall defining the radome body, including a base and a tip. The wall may comprise a core and one or more skins adjacent the core, such as in a sandwich configuration. The core and the skins may have different densities. The radome wall may be configured to transmit wideband RF signals. The RBSN may be extruded to form the radome.

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 present invention is directed to a fuze application capable of GPS (Global Positioning System) and proximity radar functionality by co-locating a proximity radar antenna with a GPS DRA (Dielectric Resonator Antenna) fuze. The GPS DRA fuze has a HE11? mode structure resulting in an E-field null at the center. The monopole proximity radar antenna is mounted in the E-field null center and is thus electrically isolated from the GPS DRA fuze. The high dielectric constant permits the GPS DRA fuze to operate in the L1 frequency and the electrically shortened proximity radar antenna to resonate in the C-Band within a small form factor. The GPS DRA fuze maintains a forward-looking CP (circular polarization) pattern while proximity antenna maintains a desirable monopole pattern. Nesting allows mounting of both GPS and proximity radar antennas on the fuze nose while reducing the total space occupied.

Abstract: This invention is related to a high efficiency antenna (1) having compact dimensions, particularly for installation on a vehicle, such as an aircraft or a high velocity train or a motor vehicle, comprising a main circular reflector (5), an illuminator (2) or feed, centrally mounted with respect to said main reflector (5), and a sub-reflector (3), mounted on said illuminator (2) by means of a positioning support member (4), said antenna (1) being installed upon a positioning member adapted to carry out azimuth and elevation polarisation movements.

Abstract: A system for receiving direct broadcast satellite signals in a mobile craft is disclosed. Generally, the system includes an orientation system for determining the first orientation of the mobile craft, a controller or processor for determining first position control data, and an electronically-pointable antenna adapted to receive first position control data from the controller, such that the antenna is pointable in accordance therewith, such that a first direct broadcast satellite signal is receivable from a first direct broadcast satellite, and a direct broadcast satellite receiver for processing a first radio frequency signal corresponding to the first direct broadcast satellite signal received by the electronically-pointable antenna.

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: 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 processor means mounted on the aircraft. According to the invention, the communication device comprises firstly an antenna secured to the sensor and thus rotating together with the wheel, and secondly a stationary antenna extending at the end of the axle and connected to the processor means, the two antennas being in radio communication through a cover of non-conductive material secured to the wheel and covering the end of the axle.

Abstract: The invention relates to an antenna (1) including: a first (2) and a second (3) linear sub-antenna equipped with sensors (21-2M, 31-3N) forming first and second line portions and generating a basic signal (Si?, Gj?), wherein the angle between the directional vectors of the first and second tangents to the midpoint of the first and second line portions is between 30° and 150°; a device for transmitting an electromagnetic signal at a frequency equal to at least 10 GHz; an antenna processing device (4, 5) forming a plurality of combined signals (VSi, VGj); a signal processing device (6, 7) generating combined signals (TSi, TGj); a device (8) for calculating the correlation coefficients ([Cij]) between the useful combined signals; a device (8) generating a detection signal ([Rij]) when a correlation coefficient exceeds a predetermined threshold.

Abstract: A rectenna structure comprising a flexible, dielectric sheet of material; a plurality of metallic lenslets disposed on the sheet of material; and a plurality of diodes disposed on the sheet of material, each diode in said plurality of diodes being arranged at a focus of a corresponding one of said plurality of metallic lenslets.

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 method for calibrating a sensor mounted on an aircraft includes the steps of: using an optical device to create reference points which define a reference line that is parallel to both horizontal and vertical planes of the sensor, and using the reference line to calibrate the sensor with respect to a reference coordinate system.

Abstract: An antenna array (501) for use in an aviation application setting comprises an external covering (503) and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering is also configured and arranged to be disposed, at least in part, in a fixed position proximal to an exterior surface (206) of an aircraft. The four radio frequency antennas are electrically discrete from one another and are each configured and arranged to receive radio frequency signals for a corresponding different radio frequency platform. These four radio frequency antennas are also configured and arranged as an integral mechanical structure.

Abstract: A reduced height log periodic antenna that may safely be positioned under the rotating blades of a helicopter sitting on the ground and still resonate in the frequency range at which the antenna was originally designed to resonate. The antenna comprises a pair of antenna booms, a first plurality of vertical antenna radiating elements connected to the booms, and a second plurality of vertical antenna radiating elements connected to the booms. In addition, the antenna includes a plurality of tuned horizontal antenna radiating elements, each tuned horizontal radiating element being connected to the top of one of the second plurality of vertical antenna radiating elements, and a plurality of tuned upwardly bent horizontal antenna radiating elements, each tuned upwardly bent horizontal antenna radiating element being connected to the bottom of one of the second plurality of vertical antenna radiating elements.

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: 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, pan of a watercraft or part of a spacecraft.

Abstract: A phased array radar antenna includes at least two antennas (11, 12, 13, 14) adapted for simultaneous operation at different non-mutually interfering frequencies. The phased array radar antenna may be fitted to an aircraft having a fuselage supporting first and second radar side antennas (11, 12) on opposite sides thereof, a nose portion supporting a first radar end antenna (13), and a tail portion supporting a second radar end antenna (14). Respective radomes cover the first and second radar end antennas so as to provide a smooth aerodynamic contour, and a radar control unit (15) is disposed within the fuselage and coupled to the first and second radar side antennas and to the first and second radar end antennas for operating the first or second radar side antenna simultaneously with the first or second radar end antenna at respective first and second different frequencies.

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: 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.