A phase-controlled antenna array comprises at least four phase-controlled elements which are connected via a feed network. Each antenna element comprises a waveguide emitter with a signal output coupling or input coupling and a phase actuator which is rotatably attached in the waveguide emitter and contains a mounting and two polarizers, wherein each of the two polarizers can convert a circularly polarized signal into a linearly polarized signal. The antenna elements additionally comprise a connection element and a drive unit which is attached to a support and which is connected to the phase actuator via the connection element such that the drive unit can rotate the phrase actuator about an axis of the waveguide emitter. The antenna array additionally comprises a computing unit which is connected to the drive unit(s) of the phase-controlled antenna elements via control lines and which adjusts the rotation of each phase actuator.

A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

The present invention relates to a transmit-array radiofrequency antenna comprising: a support; a transmit-array arranged in a plane, called a transmission plane; at least one focal source fixed on the support and arranged at the focal length from the array; and a displacement mechanism for moving the transmit-array, the mechanism being connected to the support and being adapted to translationally move the transmit-array in at least one of the two directions in the transmission plane.

A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

The present description concerns a transmitarray cell (105) adapted to implementing a full-duplex communication, the cell comprising: a first antenna element (105a) located on a first surface of the cell; a second antenna element (105b) located on a second surface of the cell, opposite to the first surface; a transmit channel comprising, between the first and second antenna elements, a first phase-shift and amplifier circuit (203a); and a receive channel comprising, between the first and second antenna elements, a second phase-shift and amplifier circuit (203b).

A phased array antenna system including a front-end circuit having a plurality of antenna channels, each including a front antenna element and a rear antenna element, that provides a spatially combined beam. Each antenna channel includes a beam scan phase shifter and a true time delay phase shifter through which the receive signals or the transmit signals propagate. The system further includes a back-end circuit spaced from the front-end circuit and including an antenna receiving the receive signals from the rear elements or transmitting the transmit signals to the rear elements. The back-end circuit further includes an ortho-mode transducer that separates the transmit signal or the receive signal into orthogonally polarized signals, and a pair of couplers and a pair of polarization phase shifters that combine to adjust the polarization of the transmit signal or the receive signal. The spatially combined beam is reconfigurable in beam shape and its location.

A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the space fed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

The present disclosure provides a glass antenna structure including: a glass sheet provided in a vehicle; a monopole antenna unit located on one surface of the glass sheet; a plurality of rectangular patch planes located on another surface of the glass sheet at a position corresponding to the monopole antenna unit; and a co-planar waveguide (CPW) feeding line in contact with one end of the monopole antenna unit.

The present invention relates to a transmitting device and a receiving device. The transmitting device includes a controller, at least a feeding antenna and a plurality of transceiving modules. The controller generates a plurality of set of module control signals; the feeding antenna radiately transmits at least an internal transmission signal. Each transceiving module includes a plurality of transceiving units, and each transceiving unit includes a radiation slice and a transceiving circuit. A lengthwise edge of the radiation slice has a first end and a second end, and the first end and the second end of the lengthwise edge are toward an inner lateral side and an outer lateral side, respectively. The transceiving module performs transmission operation or reflection operation according to the module control signals.