A signal shielding and transmitting case with a length-adjustable antenna comprises a remote control part, a signal shielding case, and a PCB and an antenna driving part arranged in the signal shielding case, wherein a control line penetrates through the antenna driving part and is fixedly connected to a signal transmitting antenna, and the remote control part can control the length of the signal transmitting antenna stretching out of the signal shielding case based on the gear lever principle to allow users to adjust the intensity of signals transmitted by the signal transmitting antenna freely.

Systems, devices, and methods for precision boom deployment are provided in accordance with various embodiments. The tools and techniques provided may have space and/or terrestrial applications. Some embodiments include a boom deployment system that may include a furlable boom. Some embodiments include: boom reinforcement devices, end fitting devices, contoured support devices, edge support devices, spiral harness devices, latch devices, combined boom spool and tension drive devices, and/or rotary encoder devices. Some embodiments may utilize a composite slit-tube boom. Some embodiments utilize a furlable boom that may be fabricated with curvature along its length.

An antenna having a reflector mounted on a rigid boom uses a line feed or phased array feed to operate in the Ka band with frequencies up to 36 gigahertz while maintaining the ability to operate at frequencies down to L-Band of 1-2 GHz.

Methods, systems, and devices for furlable antenna blade components are provided in accordance with various embodiments. For example, some embodiments include a device that may include one or more furlable antenna blade components; each of the one or more furlable antenna blade components may include one or more conductive elements. In some embodiments, each of the one or more furlable antenna blade components include one or more laminate layers. Some embodiments include a method that may include: furling one or more furlable antenna blade components around a central axis; and/or securing the one or more furlable antennae blade components when in a furled state.

A base, a spool, and an antenna structure coupled to the spool has ends that are affixed to the base. The antenna structure is wound about the spool in a stowed state, and unwound to form a loop antenna in the deployed state. The antenna structure may be a bistable composite tape with a cross-sectional curvature and having one or more antenna conductors embedded therein. A storage containment device holds the antenna structure in the stowed state. When in the stored state, the antenna structure generates a strain force against the spool biased to unwind and deploy the antenna structure to form a loop antenna when released. Another embodiment adds a second spool rotating in a direction opposite the first to achieve either state. A further embodiment uses two loop antennas by winding two antenna structures around two pairs of spools, respectively.

A mast assembly (10), a method of deploying a mast (20), a slit locking clamp (50) for a mast and to a support assembly (14) for an extendible member (20) are provided. The mast assembly (10) comprises an extendible mast (20) configurable between a coiled form and an extended form. When extended the mast is resiliently biased in the form of an elongate tube having a slit along its length defined by longitudinal edges of the mast. When coiled the mast is opened out at the slit to a flattened cross section and wound about an axis extending transversely to the longitudinal extent of the mast. A slit locking clamp (50) clamps across the slit in the mast at a position along the length of the mast so as to stabilise one edge relative to the other.

An example system for extraterrestrial deployment of a flexible membrane surface includes a flexible membrane having a periphery and an interior. The flexible membrane is rolled about a roll axis into a cylindrical geometric shape in an undeployed state. A payload base has extendable radial booms, wherein the distal end of each extendable radial boom is attached to the periphery of the flexible membrane and the interior of the flexible membrane is free of attachment to the extendable radial booms. The payload base and the extendable radial booms are positioned to one side of the flexible membrane along the roll axis. The extendable radial booms are configured to extend orthogonally to the roll axis from the payload base to unroll the flexible membrane about the roll axis to form the flexible membrane surface in a deployed state, wherein the roll axis is substantially orthogonal to the flexible membrane surface.

Systems, devices, and methods for precision boom deployment are provided in accordance with various embodiments. The tools and techniques provided may have space and/or terrestrial applications. Some embodiments include a boom deployment system that may include a furlable boom. Some embodiments include: boom reinforcement devices, end fitting devices, contoured support devices, edge support devices, spiral harness devices, latch devices, combined boom spool and tension drive devices, and/or rotary encoder devices. Some embodiments may utilize a composite slit-tube boom. Some embodiments utilize a furlable boom that may be fabricated with curvature along its length.

An antenna having a reflector mounted on a rigid boom uses a line feed or phased array feed to operate in the Ka band with frequencies up to 36 gigahertz while maintaining the ability to operate at frequencies down to L-Band of 1-2 GHz.

A spacecraft includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls, disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors. At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array. The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector is disposed, undeployed, forward of the respective feed array, proximate to and outboard of one of the plurality of sidewalls. In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.