An antenna apparatus is formed on a plane defined by perpendicular first and second axes. The antenna apparatus includes a primary radiating part, and two secondary radiating parts each including a section that extends along the first axis. The primary radiating part includes a first radiator having reflection symmetry about the second axis, a second radiator symmetrical to the first radiator with respect to the first axis, and two feed-in points The first radiator includes two lateral segments and a connector segment interconnecting the two lateral segments The lateral segments taper toward the first axis. A distance between the feed-in points is smaller than a length of a long edge of the connector segment.

Described are several embodiments of parabolic reflective antenna systems where a flexible primary reflector is supported by radial ribs of shape memory material deployed by application of heat. Several feeds made with shape memory materials working with the reflector are presented. Feed preforms include corrugated, telescopic and flattened ribbon types which extend or unfurl into final shapes upon application of heat. Several antenna and feed embodiments also contain supports for secondary reflectors and patch antennas.

Systems and methods for making and/or using a hybrid laminate composite tube structure. The methods comprise: wrapping a plurality of lamina layers around a male cylindrical tool (e.g., mandrel); treating the lamina layers with heat/pressure to form the hybrid laminate composite tube structure; and assembling a structure by adhesively bonding the hybrid laminate composite tube structure to a metallic fitting. The lamina layers comprise: at least one first lamina layer formed of a first material having a first CTE; and at least one second lamina layer formed of a second material different from the first material and having a second CTE different than the first CTE. The hybrid laminate composite tube structure has at least one property that is different in the axial direction than the hoop direction. An axial CTE of the hybrid laminate composite tube structure is tailored to provide a net zero CTE for the assembled structure.

Antenna system includes a base structure and a multiplicity of vertebrae arranged in a stack to define a spine. The spine has an elongated length which extends from a base end to a tip end. A compression applicator is configured to apply an elastic compression force on the stack in a direction along the elongated length from the tip end to the base end. Vertebra interfaces associated with each of the adjacent pairs of the vertebrae are configured to facilitate a variable deviation in an angular alignment of a vertebra axis of each vertebra relative to an adjacent one of the vertebra contained in the stack.

Systems and methods for deploying an extendable reflector structure. The methods comprise: transitioning the extendable reflector structure from a stored configuration to a deployed configuration; and causing expansion of a pantograph coupling structure while the extendable reflector structure is being transitioned from the stored configuration to the deployed configuration. The pantograph coupling structure indirectly couples the extendable reflector structure to a boom such that a beam produced by the extendable reflector structure during operation is offset from a focal axis of the extendable reflector structure by a certain amount.

An antenna structure includes a radiator element configured for operation at a first microwave frequency range and at a second microwave frequency range that is higher than the first microwave frequency range, and a reflector including the radiator element attached thereto. The reflector includes an enclosure that houses the radiator element and a radiating aperture. The antenna structure further includes a radome assembly adjacent the radiating aperture. The radome assembly includes a flexible radome having a thickness that is less than a wavelength corresponding to the first or second microwave frequency ranges, and a tensioning member that extends along a perimeter of the flexible radome and maintains tension in a surface of the flexible radome.

Deployable reflector antenna includes a fabrication hub in which at least one additive fabrication unit disposed. The additive fabrication unit is configured to form at least one rigid structural element of a reflector antenna system. In a stowed condition, an RF reflector material comprised of a flexible webbing is disposed in a stowed configuration proximate to the fabrication hub. A fabrication control system controls the additive fabrication unit so as to form the at least one rigid structural element. The RF reflector material is arranged to transition during the additive fabrication process from the stowed configuration in which the flexible webbing material is furled compactly at the fabrication hub, to a deployed configuration in which the flexible webbing material is unfurled.

Perimeter truss reflector includes a perimeter truss assembly (PTA) comprised of a plurality of battens, each having an length which traverses a PTA thickness as defined along a direction aligned with a reflector central axis. A collapsible mesh reflector surface is secured to the PTA such that when the PTA is in a collapsed configuration, the reflector surface is collapsed for compact stowage and when the PTA is in the expanded configuration, the reflector surface is expanded to a shape that is configured to concentrate RF energy in a predetermined pattern. Each of the one or more longerons extend around at least a portion of a periphery of the PTA. These longerons each comprise a storable extendible member (SEM) which can be flattened and rolled around a spool, but exhibits beam-like structural characteristics when unspooled.

A strut-and-node truss design that is applicable to all space frame structure designs can be made with using robotic (semi-autonomous and/or fully autonomous) or telerobotic assembly/joining. Nodes can include a 2-dimensional weld path in an effort to reduce the complexity of having to weld in 3-dimensions. Furthermore, each strut to node connection can be concentrated in a small area where each weld can be performed robotically from a fixed position that only requires the robotic weld head to swivel in a small operating window to reach each joint.

Antenna apparatus and spacecraft to be deployed in a more compactly stored state are disclosed. In an example of the disclosed technology, a spacecraft includes: a main-reflection unit configured to reflect and emit a radio wave outside, a sub-reflection unit configured to face the main-reflection unit, a radiator arranged to face the sub-reflection unit and configured to radiate the radio wave in a direction of the sub-reflection unit, a main body configured to be able to accommodate at least one part of the sub-reflection unit therein, and a delivery device connected to the sub-reflection unit and configured to deliver the sub-reflection unit, at least one part of which is accommodated in the main body, to a position where the sub-reflection unit is able to reflect the radio wave radiated from the radiator to the main-reflection unit and cause the main-reflection unit to radiate the radio wave outside.