Provided is an antenna for receiving radio waves including frequencies in the L6 band unique to QZSS to realize accurate positioning by QZSS. A substrate-type antenna 1 comprises an arcuate antenna element 20 including a long arcuate antenna element 22 and a short arcuate antenna element 24, each of which includes an integral antenna element compatible with three frequency bands and a single antenna element compatible with one frequency band and arranged with a space from the integral antenna element. Each of the integral antenna element and the single antenna element extends from an outer peripheral part of the arcuate antenna element toward an inner peripheral part thereof. The substrate-type antenna 1 further comprises a plurality of connection units 34 connected to the long arcuate antenna element 22 and the short arcuate antenna element 24, respectively, and a coupler 30 to which the plurality of connection units 34 is coupled.

A composite antenna device (10) configured for omnidirectional operation, comprising a first antenna system (100) configured for use in a first frequency band of a first frequency range (FR2), comprising multiple first antenna elements (110, 110A) arranged in a cylindrical configuration; a second antenna system (200) configured for use in a second frequency band of a second frequency range (FR1) at a frequency which is lower than the first frequency band; and a housing (11) enclosing the first and second antenna systems, wherein the first and the second antenna systems are configured for omnidirectional operation about an axis (12) of the composite antenna device.

A composite antenna device (10) configured for omnidirectional operation, comprising a first antenna system (100) configured for use in a first frequency band of a first frequency range (FR2), comprising multiple first antenna elements (110, 110A) arranged in a cylindrical configuration; a second antenna system (200) configured for use in a second frequency band of a second frequency range (FR1) at a frequency which is lower than the first frequency band; and a housing (11) enclosing the first and second antenna systems, wherein the first and the second antenna systems are configured for omnidirectional operation about an axis (12) of the composite antenna device.

Disclosed in the present application are a signal continuous coverage method, device and apparatus for a target area, and an antenna system. The signal continuous coverage method for a target area, which is used for an aircraft bearing a communication base station, comprises: acquiring the flight height, the farthest distance of a flight trajectory, the roll angle and a preset center position of a target area of the aircraft; acquiring a vertical half-power angle of an airborne antenna of the communication base station and a farthest signal coverage point position relative to the preset center position; on the basis of the flight height, the farthest distance of the flight trajectory, the roll angle, the preset center position, the vertical half-power angle and the farthest signal coverage point position, determining a target downward inclination angle of the airborne antenna; and adjusting a current downward inclination angle of the airborne antenna to the target downward inclination angle so as to enable a signal continuous coverage area to comprise the target area.

An antenna system for space applications provides a membrane antenna with one or more flexible membranes. An antenna enclosure stores the membrane antenna during stowage. One or more first deployable support structures extend along a first axis from the antenna enclosure during deployment, at least a first point of the membrane antenna being operably anchored to a point on the first deployable support structures. Deployment mechanisms are operably anchored at a junction with the first deployable support structures. The deployment mechanisms extend one or more second deployable support structures along a second axis from the first deployable support structures during deployment. At least a second point of the membrane antenna is operably anchored to a point on the second deployable support structures. Extension of the first deployable support structures and second deployable support structures unfurls the membrane antenna along both axes to overlap the junction.

The disclosed invention provides a distributed directional aperture (DDA) system that is installed in a vertical lift aircraft that comprises a fuselage and a rotor system including rotary wings rotatably coupled to the fuselage. The DDA system provides capability to receive and/or transmit signals in one or more frequency bands, and provides communications, signals intelligence (SIGNINT), positional sensing, jamming, and offensive cyber on the vertical lift aircraft. The DDA system of the vertical lift aircraft includes a sensor and emitter array subsystem that includes a plurality of sensors and emitters distributed in the rotary wings, a beamformer subsystem that processes the sensor signals and emitter signals, and a telemetry subsystem that conveys signals between the sensor and emitter array subsystem and the beamformer subsystem.

The disclosed invention provides a distributed directional aperture (DDA) system that is installed in a vertical lift aircraft that comprises a fuselage and a rotor system including rotary wings rotatably coupled to the fuselage. The DDA system provides capability to receive and/or transmit signals in one or more frequency bands, and provides communications, signals intelligence (SIGNINT), positional sensing, jamming, and offensive cyber on the vertical lift aircraft. The DDA system of the vertical lift aircraft includes a sensor and emitter array subsystem that includes a plurality of sensors and emitters distributed in the rotary wings, a beamformer subsystem that processes the sensor signals and emitter signals, and a telemetry subsystem that conveys signals between the sensor and emitter array subsystem and the beamformer subsystem.

A power tether for aerial devices such as balloons or drones operates with as few as a single conductor, providing a ground return by capacitive coupling between the aerial device and a ground plane at a base station. High-frequency, high-voltage power allows significant power transfer through the low capacitance between the aerial station and the ground minimizing the necessary current flow.

Technologies directed to a radio frequency (RF) structure that provides an electrically insulating gap between a ground plane of a circuit board and a chassis at direct current (DC) and an electrical connection between the ground plane and the chassis at RF frequencies. One RF structure includes a first conductor electrically coupled to the ground plane and a second conductor electrically coupled to the chassis. A physical arrangement of a portion of the first conductor and a portion of the second conductor causes the RF structure to provide an electrically insulating gap between the ground plane and the chassis at DC and an electrical connection between the ground plane and the chassis at RF frequencies.

Antennas used aboard aircraft to communicate with satellites or ground stations may have complex antenna patterns, which may vary as the aircraft moves throughout a given coverage area. Techniques are disclosed for dynamically adjusting the instantaneous power fed to an antenna system to ensure that the antenna transmits at the regulatory or coordinated effective isotropic radiated power (EIRP) spectral limit. The antenna may transmit, in accordance with aircraft location and attitude, steerable beam patterns at different scan and skew angle combinations, causing variations in antenna gain and fluctuations in the transmitted EIRP. Using on-board navigational data, an antenna gain and ESD limit may be calculated for a particular scan and skew angle, which may be used to adjust power fed to the antenna such that the antenna transmits substantially at maximum allowable EIRP as the steerable beam pattern is adjusted.