A deployable antenna structure is provided that, in one embodiment, implements an offset feed, cylindrical parabolic antenna. The antenna structure employs a semi-rigid panel that can transition from a stowed state characterized by the retention of substantial strain energy to a deployed state characterized by less strain energy than in the stowed state but more than if the panel were in a strain-free state and a portion of the panel having a shape that closely conforms to a cylindrical parabolic shape.

There are described methods and devices for intra-spacecraft communication in space, the electro-optical device having at least one of transmitting capabilities for converting a first electrical signal into a first optical signal and outputting the first optical signal within a spacecraft, and receiving capabilities for receiving a second optical signal within the spacecraft and converting the second optical signal into a second electrical signal, the electro-optical device having at least one integrated circuit dedicated to at least one of the transmitting capabilities and the receiving capabilities, the at least one integrated circuit configured for operating in an analog mode where configuration voltages for the integrated circuit are provided by analog voltage settings unaffected by radiation.

Apparatuses, methods, and systems for a printed circuit board that includes multiple antennas, and operates to support satellite communications, are disclosed. One apparatus includes a first flat panel element. The first flat panel element includes a multilayer PCB (printed circuit board). The multilayer PCB includes a first exterior layer comprising N antenna elements, and a second exterior layer comprising N RF (radio frequency) chains operative to process the RF signals, each of the N RF chains electrically connected to a one of the N antenna elements, and N metal patches arranged in a square, wherein an air gap is located between the N metal patches and the N antenna elements, wherein dimensions, orientation, and spacing between the N metal patches and the N antenna elements are selected based on a carrier frequency, bandwidth, and directionality of the propagated RF signals.

Increasing demand for communications systems for facilitating communications such as communications satellites leads to continuously increasing frequency bands of the signal for communication and the quantity of beams carrying the signals may make it more and more difficult to have a significant number of mechanical and electrical components concentrated in a location in proximity to the array while maintaining antenna efficiency. Provided is a direct radiating array (“DRA”) antenna for transmitting or receiving an electromagnetic radio frequency (“RF”) signal of at least one predetermined signal frequency band and a method of assembly that overcomes at least some of the disadvantages of existing direct radiating array systems and methods. The DRA antenna comprising a plurality of radiating elements, a plurality of RF signal chain paths and a beamforming network board having a plurality of electrical ports for electrically connecting to the plurality of RF signal chain paths.

A waveguide polarizer for converting between a linearly polarized electromagnetic field in a first waveguide and a circularly polarized electromagnetic field in a second waveguide is provided. The waveguide polarizer includes a structure interconnecting the first and second waveguide which includes a waveguide excitation arrangement with a bifilar helical shape. A circularly polarized antenna arranged to be connected to the first waveguide of the waveguide polarizer and a satellite arrangement are also provided.

Antennas with tunable elements and methods for using the same are disclosed. In some embodiments, an antenna comprises: a plurality of radio-frequency (RF) radiating antenna elements, wherein each antenna element of the plurality of RF radiating antenna elements comprises a tunable element, circuitry connected to the tuning element to set a voltage on the tunable element. In some embodiments, the circuitry comprises a voltage storage structure, a first transistor having a first gate connected to the voltage storage structure, a first source connected to the tunable element, and a first drain for coupling to a constant voltage source, and a data voltage input terminal operable to apply a voltage to the voltage storage structure and to the first gate to determine current through the first transistor.

Embodiments provide in-flight configuration of satellite pathways to flexibly service terra-link and cross-link traffic in a constellation of non-processed satellites, for example, to facilitate flexible forward-channel and return-channel capacity in a satellite communications system. For example, each satellite in the constellation can include one or more dynamically configurable pathway, and switching and/or beamforming can be used to configure each pathway to be a forward-channel pathway or a return-channel pathway in each of a number of timeslots according to a pathway configuration schedule. At least some of the pathways can be further selectively configured, in each timeslot, to carry “terra-link” traffic to and/or from terrestrial terminals and “cross-link” traffic to and/or from one or more other satellites of the constellation.

A dual-use spring attached to a small satellite that performs two common functions for small satellites including operating as a communications antenna for the small satellite, which eliminates the need for a separate antenna deployment step, and ejecting the small satellite from a modified deployment container mounted on a launch vehicle. The deployment container is modified by removing a conventional deployment spring and pusher plate, which increases available container space.

A deployable assembly for antennae includes a structure having a reflective surface and n pairs of segments, each pair of segments corresponding to one side of a deployed polygonal shape. N hinge joints are between the two segments of a side. N hinged angular links are between every two adjacent sides. The structure is changeable from a stowed substantially cylindrical shape into a deployed substantially planar polygonal shape with n sides. A deployable boom is between two segments. The boom lays stowed between the two segments before deployment and ends in a feeder electromagnetically feeding the antenna and includes a clamping element for keeping the structure closed when stowed. The feeder acts as structural support element when stowed and electromagnetic feeder for the antenna when deployed. A cable network shapes the reflective surface, with corresponding cables held by tensor elements protruding from the back of the segments.

A transmitarray cell (105) comprises a first antenna element (105a) adapted to switching between two phase states, a second antenna element (105b) adapted to switching between two other phase states and between two circular polarization directions and a coupler (201) coupling the first antenna element to the second antenna element.