Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

In some embodiments, an antenna may include a plurality of reflectarray tiles and a frame including a plurality of frame elements coupled electrically and mechanically. The frame may be configured to conform to a shape of a surface. Each frame element may be configured to receive one of the plurality of reflectarray tiles. In some aspects, the plurality of reflectarray tiles may be illuminated directly or indirectly by a feed.

An aircraft antenna assembly has a support element having a first and a second surface on opposite sides, an antenna element arranged on or in the support element, and a sealing device. The first surface and the sealing device are configured such that the antenna assembly is arranged on an outer skin section of an aircraft such that the first surface faces the outer skin section, the sealing device is situated between the support element and the outer skin section, and a cavity is defined by the sealing device, the outer skin section and the first surface. The support element or the sealing device y has a flow channel having a first and a second opening at opposite ends, the flow channel connecting the cavity and the environment and opening into the cavity at the first opening and opening into the environment at the second opening.

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.

One embodiment is an apparatus comprising an aircraft and an aerial network communications system associated with the aircraft. The network communications system may comprise an antenna physically connected to an outside surface of the aircraft; and a transceiver electrically connected to the antenna. The aerial network communications system receives signals from and transmits signals to an unmanned aerial vehicle (UAV) via a communications network comprising a control station and a plurality of airborne network nodes.

A compact shallow cavity-backed discone antenna array for conformal omnidirectional antenna applications is disclosed. The antenna array comprises a plurality of discone antennas arranged in a ring array within a circular contoured conical cavity. The cavity is covered with an electrically transparent radome. The individual discone antenna elements are fed with coaxial transmission lines. Good performance is demonstrated by simulation and by experiment in terms of reflection coefficient and omnidirectional gain radiation patterns from about 960 MHz to 1220 MHz. In one embodiment, the shallow cavity-backed discone antenna array may be used as a flush-mounted antenna that conforms to the outer mold line of an aircraft.

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.

Wireless communication systems for an aircraft are disclosed. In an embodiment, the wireless communication system includes a router, an antenna, a control unit, and an antenna steering unit. The router is connected to the antenna. The router is configured to transmit and receive wireless data communication to and from a stationary communication server outside the aircraft through at least one ground base station via the antenna. The antenna is a directional antenna. The control unit is configured to determine an attitude change of the aircraft by determining a change in at least one of a roll angle, a pitch angle, and a yaw angle of the aircraft. The antenna steering unit is connected to the control unit. The antenna steering unit is configured to steer an antenna beam of the directional antenna based on the attitude change of the aircraft.

Aspects of the disclosure provide an antenna system for a high-altitude platform (HAP). The antenna system may include a central panel including a first set of antenna elements. The antenna system may also include a plurality of auxiliary panels arranged around the central panel and at an angular offset from the central panel. Each auxiliary panel of the set of auxiliary panels may include a second plurality of antenna elements. The first plurality of antenna elements may be configured to provide network coverage within a first area having a first radius and each of the second sets of antenna elements are configured to provide network coverage within a second area beyond the first radius.

An antenna assembly and method of forming the same includes a dielectric support base including an antenna element layer having one or more antenna elements, and a cavity layer coupled to the dielectric support base. The cavity layer includes a main body having one or more cavities. The one or more antenna elements are disposed within the one or more cavities.