The antenna includes a first antenna unit and a second antenna unit. The first antenna unit and the second antenna unit are disposed on the same surface of a substrate. The first antenna unit includes a first primary radiation unit and a first secondary radiation unit, and the second antenna unit includes a second primary radiation unit and a second secondary radiation unit. A gap exists between the first primary radiation unit and the second primary radiation unit. The first secondary radiation unit is connected to one end of the first primary radiation unit that is away from the second primary radiation unit, the second secondary radiation unit is connected to one end of the second primary radiation unit that is away from the first primary radiation unit, and the first secondary radiation unit and the second secondary radiation unit are located on the same side of the substrate.

A system and method for a multi-panel multi-function active electronically scanned array (AESA) radar operation receives radar commands from individual aircraft systems and segments a plurality of AESA panels fixed (at variable azimuth/elevation about the aircraft) into a plurality of subarrays to carry out each individual function commanded by the individual aircraft system. Dependent on aircraft status and phase of flight, the and individual AESA are designated for use and the subarrays are sized based on desired radar function at the specific phase of flight and specific threat associated with the phase. The system dynamically shifts the designated AESA, subarray size, beam characteristics, power settings, and function to enable multiple simultaneous function of the suite of AESA panels.

A surface card antenna apparatus comprises a single circuit board having a major side surface. The surface card antenna apparatus further comprises a horizontal polarization antenna portion mounted on the major side surface of the single circuit board. The surface card antenna apparatus also comprises a vertical polarization antenna portion mounted on the major side surface of the single circuit board.

Unit cells for phased array antennas are described. The unit cells include a plurality of dipole antennas that are used to form a phased array antenna. In particular, the unit cells that form the phased array antenna each include a plurality of dipole antennas formed on a surface of a substrate that are arranged to collectively form a triangle. A plurality of the unit cells may be linked together to form a triangular lattice array having almost any desired size and aperture, thereby allowing the RF engineer the freedom to achieve a wide variety of performance goals when designing a phased array antenna.

An aircraft antenna assembly has a structural section of an aircraft, an antenna element, a cover transparent to radio waves, and a structural element. The structural section has an assembly of interconnected elongate longitudinal and transverse reinforcing elements and an outer skin arranged on one side of the assembly and secured on the reinforcing elements. A surface of the outer skin facing away from the elements forms an outer surface of the structural section. An opening closed by the cover, is formed in the outer skin. In the region of the opening, at least one of the reinforcing elements has a gap, in which the structural element is arranged and which divides the respective reinforcing element into two sections on opposite sides of the gap. The antenna element is arranged in the region of the opening on the opposite side of the outer skin from the outer surface.

A communication system for a hypersonic vehicle uses a distributed antenna system, an impedance matching circuit that provides impedance matching between a transmitter and/or receiver and the selected one or more antennas of the distributed antennas system and a surrounding plasma sheath, near-field probes to determine impedance of the plasma sheath adjacent to each of the probes and thus predict behavior of the respective antennas near the probes, and a control system that selectively connects a transmitter and/or receiver to one or more of the antennas based upon the antennas that are seeing the most favorable transmission or reception characteristics and controlling the impedance matching is to provide impedance matching for the selected antennas.

An antenna system having reduced back radiation is disclosed. The antenna system includes an antenna and ground plane. The antenna includes electro-textiles and is configured to operate in at least the frequency range between 1.1-1.6 GHz. The ground plane includes electro-textiles and is configured to operate as a frequency selective surface with electronic band gap characteristics to suppress edge and curved surface diffraction effects. In this system, the antenna and ground plane are configured to be located on a curved surface and to radiate with a directional radiation pattern having attenuated back lobes.

An antenna and radome assembly has an adapter plate engaging a first fitting configuration mounted to an aircraft fuselage. The adapter plate mechanically supports an antenna assembly wherein the antenna assembly is originally configured for a second fitting configuration. A radome is attached to the adapter plate enclosing the antenna assembly. The adapter plate has at least a nose portion providing reactive structure adapted to transform a longitudinal load on the radome into an induced downward vertical deflection.

Disclosed is a cross loop antenna system for an aerial vehicle. In one embodiment, the cross loop antenna system includes a cross bar antenna and a ground plane. The cross bar antenna includes two thin coplanar perpendicular bars that intersect in the middle and are parallel to the ground plane. Each bar couples to the ground plane at each end, comprising an antenna loop. Thus, the cross loop antenna system comprises two intersecting single-fed loops. The antenna can operate at a wavelength that is approximately twice the length of the bars. In such an embodiment, the antenna system may be resonant. The distance between the bars and the ground plane may be relatively small, thus minimalizing the vertical profile of the antenna. The antenna may be operated as a dual-band antenna and may produce an omnidirectional radiation pattern. An aerial vehicle may include two such antennas.

Various ring cells are disclosed herein that include a metallic ring patch and a ring slot to transmit or receive radio frequency (RF) signals. The disclosed ring cells use several dielectric layers that are separated by a low-dielectric foam layer upon which the ring patch is positioned. The ring slot is located below the foam layer. An electrically conductive fence formed curved electrically conductive walls or a circular pattern of electrical vias is positioned around the ring slot. Electrical feed lines are used to either supply electrical power to the ring cells or output RF signals that are received by the ring patch.