Provided is an antenna integrated structure in which an antenna is inserted into ground vehicle, marine ship and aircraft structure, and more particularly, a sandwich panel type antenna integrated latticecore having a structure for improving communication performance of an antenna module.

Embodiment of the present disclosure relates to a shared aperture antenna for continuous transmission of signal to ground station at two different spot frequencies. The antenna provides a broad side radiation pattern for frequency range of S band and squinted radiation pattern for frequency range of Ka band. The dual band microstrip antenna is configured on a single layer substrate, having a rectangular slot at small offset from the center on low frequency radiating patch. The positioning of radiating patch and length of high impedance microstrip feed are adjusted to fit into the slot and to get desired squint at high frequency. Two separate coaxial feeds are provided to excite the antenna independently. Third feed fulfil the termination needed by travelling wave array which increases the impedance bandwidth of antenna. A radome is provided to protect the radiating element from environment.

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.

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.

A low-profile conformal antenna (LPCA) is disclosed. The LPCA includes a plurality of dielectric layers forming a dielectric structure. The plurality of dielectric layers includes a top dielectric layer that includes a top surface. The LPCA further includes an inner conductor, a patch antenna element (PAE), and an antenna slot. The inner conductor is formed within the dielectric structure, the PAE is formed on the top surface of the top dielectric layer, and the antenna slot is within the PAE. The LPCA is configured to support a transverse electromagnetic (TEM) signal within the dielectric structure.

A movable device includes a fuselage and a navigation antenna arranged at an edge portion of the fuselage. The navigation antenna is tilted relative to the fuselage. One side of the navigation antenna proximal to a center portion of the fuselage is at a higher level than another side of the navigation antenna distal from the center portion of the fuselage.

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

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 lightning diverter system configured to equip a radome of an aircraft comprises a segmented strip configured to transmit lightning by ionization of the air to a point of junction with the aircraft structure. The segmented strip is configured to be installed on an inner wall of the radome. The lightning diverter system comprises at least one metal block configured to be installed in a through-hole of the radome, so as to be flush with an outer wall of the radome opposite to the inner wall and which is configured to be subject to an airflow when the aircraft is moving. The arrangement of the segmented strip and of the metal block or blocks is such that, when the lightning strikes the metal block on the outer wall of the radome, the lightning is transmitted to the segmented strip on the inner wall of the radome.

An aircraft antenna (101) including a radome (102) wherein the radome (102) has a main body (105) shaped to enclose one or more antennae (107) when the antenna (101) is attached to a fuselage skin portion (103), wherein the main body (105) includes a front surface portion (203), a rear surface portion (401), adjacent side surface portions (205,207), and an upper surface portion (209) that form a smooth outer aerodynamic surface (211) of the antenna (101), and wherein the upper surface (209) is substantially planar in shape along a length of 60% to 80% of a length (L) of the of the radome (102).