In one aspect, the inventive concepts disclosed herein are directed to an antenna array system employing a current sheet array (CSA) wavelength scaled aperture. The CSA wavelength scaled aperture can include a first frequency region associated with a first operating frequency band and a second frequency region associated with a second operating frequency band. The first operating frequency band can include one or more current sheet sub-arrays having a respective plurality of first unit cells scaled to support the first operating frequency band. The second operating frequency band can include one or more current sheet sub-arrays having a respective plurality of second unit cells scaled to support the second operating frequency band. The CSA wavelength scaled aperture can include one or more capacitors each of which coupled to a respective first unit cell of the first frequency region and a respective second unit cell of the second frequency region.

A broadband conformal antenna (BCA) is disclosed. The BCA includes a narrow approximately rectangular outer conductive (NARO) housing, a plurality of dielectric layers within the NARO housing forming a laminated dielectric structure, and an inner conductor formed within the laminated dielectric structure. The NARO housing includes a top broad wall and the BCA further includes an antenna slot within the top broad wall. The BCA is configured to support a transverse electromagnetic signal within the NARO housing.

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.

A structural panel of an aircraft is constructed with a multiphase antenna embedded inside the structural panel between multiple sheets of fiberglass.

A system for emitting and/or receiving electromagnetic waves embedded in an aircraft, the aircraft including an emitting and/or receiving device for emitting and/or receiving electrical signals, a radome having an electrically insulating protective envelope (12), on which at least one lightning arrester strip (21) is arranged, the radome being attached to a metal frame of the aircraft (30), a first part of the at least one lightning arrester strip is electrically connected to the metal frame of the aircraft, a second part of the at least one lightning arrester strip is connected to the emitting and/or receiving device via a metal element (35) of a predetermined shape, the at least one lightning arrester strip forming an antenna and a part of the metal element (35) is placed at a predetermined distance (d) from a part of the metal frame of the aircraft (30) for forming a capacitive link between the metal element and the metal frame of the aircraft.

A broadband stacked multi-spiral antenna array comprising two or more spiral antennas with a dielectric layer having a generally uniform thickness positioned between each pair of stacked antennas, which are all center-fed and in-phase. The antenna array may be embedded in a non-conductive material, such as fiberglass embedded in a resin, a honeycomb core sandwich, or structural foam, that may be used to form a structural element of a mobile platform. The structural element may include a via providing a pathway for coaxial cables. If two structural elements are hatch covers on the port and the starboard sides of an aircraft, the use of a stacked multi-spiral antenna array in each structural element provides two roughly hemispherical coverage patterns which together provide an omni-directional coverage pattern. The stacked multi-spiral antenna array may also include a reflecting cavity placed at the bottom of one of the spiral antennas.

A method and apparatus for retrofitting an aircraft. Connection points for a reinforcement structure are located. The reinforcement structure is associated with the airframe during original manufacturing of the aircraft and accommodates forces from an antenna system attached to the reinforcement structure. The antenna system includes an antenna selected from a plurality of types of antennas. An antenna adapter plate in the antenna system is attached to the reinforcement structure connected to the airframe of the aircraft during the original manufacturing of the aircraft using the connection points. The antenna is attached to the antenna adapter plate, wherein the antenna adapter plate is configured to receive any one of the plurality of types of antennas. The reinforcement structure is configured to handle loads from any one of the plurality of types of antennas and the antenna adapter plate attached to the connection points.

An antenna includes an ion exchange material and at least one polymer member coupled to a communication circuit. The at least one polymer member is configured to, responsive to receiving a bias voltage, interact with the ion exchange material to change electrical conductivity of the at least one polymer member.

Adhesive bondlines in a cell-based structural array are thermally cured using tooling blocks inserted into the cells. The tooling blocks have embedded susceptors that are inductively heated by an alternating electromagnetic field generated by an electromagnet.

A frequency-selective composite structure includes a laminate panel, and a frequency-selective filter including a plurality of frequency-selective surface elements coupled to an exterior surface of the laminate panel and arranged in a frequency-selective surface pattern, wherein each one of the frequency-selective surface elements includes a nanomaterial composite.