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.

According to some aspects, an antenna is provided comprising a substrate, a first conductive region disposed on a first side of the substrate, a second conductive region disposed on a second side of the substrate, and a coaxial transmission line, an inner conductor of the coaxial transmission line electrically coupled to the first conductive region and an outer conductor of the coaxial transmission line electrically coupled to the second conductive region, wherein the second conductive region includes at least one structural feature that functions as a choke when the first and second conductive regions are operated together as an antenna. According to some aspects, an aerial vehicle comprising a conformal antenna is provided.

An antenna array includes a plurality of flared notch radiators recessed within a missile nose cone and positioned in a circumferential arrangement around and extending radially from the payload's metal skin to contact an annular metal cover that provides a ground plane such that each flared notch radiator is inclined towards the boresight axis. The payload's metal skin provides an image plane for each flared notch radiator to launch RF energy with a radial polarization normal to the image plane forward through the annular RF radome. Each flared notch radiator may be positioned within a 5 sided waveguide to further improve directionality and isolation.

An apparatus and related method are disclosed for compensation of an antenna and/or an antenna array located at a surface that experiences environmental conditions. The apparatus can include: an embedded compensation and/or calibration structure configured to be interrogated by an electromagnetic wave, to dynamically compensate for surface erosion, thermal expansion, and/or dielectric constant changes of a surface scattering antenna; and a processor configured to: receive measurements of the compensation and/or calibration structure to determine beam pointing for dynamically varying surface conditions and perform sensing and/or seeking observation.

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.

Disclosed are embodiments of antenna assemblies for integration with aircraft lighting systems. The antenna assemblies in some embodiments include a ground plane, a patch antenna positioned on the ground plane, and a radome covering the patch antenna. The patch antenna and radome are configured as an annular ring for positioning around a light fixture received through a center opening through each of the ground plane, patch antenna, and radome such that the antenna assembly can mount and connect to the aircraft utilizing the light fixture aperture without the need for a separate antenna aperture.

Method for compensate cavity effect in aircraft embedded antenna impedance and Embedded antenna array for aircraft The present invention relates to a method for compensate cavity effect in aircraft embedded antenna impedance by using radiofrequency (RF) absorber materials applied to entirely embedded antennas (non-protruding installation) particularly used in aircraft. The invention also refers to embedded antenna arrays for aircraft using radiofrequency (RF) absorber materials to enhance and/or optimize its impedance matching.

A phased array antenna for a mobile platform combines transmit and receive antennas within a common, low profile enclosure. Transmit and receive functions, a power supply, up and down frequency converters, and an antenna controller are integrated into closely packaged layers within the enclosure.

A system for air-to-air communications which provides for multi-band simultaneous high and low frequency communications utilizing a variable geometry type antenna. The system operates simultaneously in a broadcast mode on low frequencies and in a directed mode on high frequencies.

According to some embodiments, an unmanned vehicle includes a power supply configured to supply an electrical power signal to a motor for propelling the unmanned vehicle, a wireless communication device configured to transmit or receive a radio frequency (RF) signal, and a motor feed antenna coupled to the power supply and the wireless communication device, the motor feed antenna configured to conduct the electrical power signal from the power supply to the motor, and to transmit or receive RF signals as an antenna for the wireless communication device.