An antenna assembly includes a first magnetic substrate having a first surface and a second surface opposite from the first surface. One or more antenna elements are disposed on the first surface of the first magnetic substrate. A microstrip feed line is disposed on the second surface of the first magnetic substrate. A second magnetic substrate is secured to the first magnetic substrate. The second magnetic substrate includes one or more cavities aligned with the one or more antenna elements and the microstrip feed line.

An antenna assembly includes one or more dielectrics having a first surface and a second surface opposite from the first surface. An antenna layer includes one or more antenna elements disposed on the first surface of the one or more dielectrics. A stripline feed network is disposed on or within the one or more dielectrics. One or more cavities are formed in the one or more dielectrics. The one or more cavities are disposed below the one more antenna elements.

A system of spiral antennas is incorporated into aircraft body panels. The spiral antennas may be slot or printed material antennas, cavity backed for unidirectional communication, or open for bi-directional communication. The spiral antennas are operated in concert as a steerable array. The spiral antennas are utilized for various signal functions including ultra-wideband communications and electronic support measures interferometry.

Disclosed are embodiments of exterior aircraft assemblies integrating compatible elements. In one example, an integrated aircraft assembly includes an aerodynamic housing attachable to an aircraft, an antenna system including at least one antenna element housed within the aerodynamic housing, and a lighting system including at least one light fixture housed within the aerodynamic housing. The at least one antenna element and the at least one light fixture may be co-located within then housing or mounted separately on the housing.

An aircraft has a fuselage, a wing assembly coupleable to the fuselage, and an empennage including a pair of tail booms configured to be removably coupled to the wing assembly. The wing assembly includes a pair of boom interfaces located on laterally opposite sides of the fuselage. Each tail boom has a boom forward end configured to be mechanically attached to one of the boom interfaces using an externally-accessible mechanical fastener.

A planar antenna includes a plurality of antenna elements and transmits and receives a radio wave to and from a target. An attitude controller is attached to the planar antenna and controls an attitude of the planar antenna mechanically. An antenna controller controls the attitude controller such that the planar antenna points in a predetermined direction with respect to the target. A scan controller controls beam scanning performed by the planar antenna and adjusts an excitation phase of each of the antenna elements in accordance with a signal level of a reception signal generated from a radio wave received from the target during performance of the beam scanning, thereby directing a beam from the planar antenna toward the target. The scan controller limits a range of the beam scanning to a range within which no grating lobe occurs.

Examples disclosed herein describe an antenna architecture (e.g., a planar electronically steered antenna architecture) that enables operation at low elevation angles, down to zero degrees from the satellite. The proposed ‘3SA’ architecture may improve power consumption and array footprints. The proposed ‘3SA’ architecture can support aero terminal implementation on aircraft, enabling the use of GEO, MEO and LEO satellites even in regions having low elevation angles. The architecture may include a horizontal antenna array and vertical antenna array as well as a controller for switching between the antenna arrays.

Techniques are provided for fabricating a low profile antenna that operates with increased efficiency. An antenna implementing the techniques according to an embodiment includes a first arm comprising a first spiral portion and a first rectilinear portion, and a second arm comprising a second spiral portion and a second rectilinear portion. The second spiral portion is concentric with the first spiral portion. The antenna further includes an insulator to separate the arms. The insulator and the arms are planar surfaces disposed within a rectangular region. The first rectilinear portion is adjacent to a first and second side of the perimeter of the rectangular region, and the second rectilinear portion is adjacent to a third and fourth side of the perimeter of the region. The antenna is fabricated as a printed circuit board which is mounted on the fuselage of an aircraft, which serves as a ground plane for the antenna.

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 datalink such as used on high-speed vehicles (missiles, guided-projectiles, manned or unmanned aircraft) includes an integrated conformal antenna array and out-of-band rejection filter for use with an RF radio. Integration of a single rejection filter between the EME power received by the antenna array and the coaxial RF connector effectively protects the connector as well as the radio. The connector can now be designed based solely on the transmit power requirements of the radio. The resultant connector is smaller and takes up less space inside the vehicle.