The invention relates to a foldable/deployable structure (1) comprising: —a mast (4) which can be deployed along a longitudinal deployment axis, the mast being designed to be placed either in a folded state requiring little axial installation space, or in a deployed state having a predetermined shape, —a base (10) upon which the deployable mast (4) is rested, the structure (1, 2) further comprising a bracing device, the bracing device: —having at least three points for attachment to the base (10) and at least three points for attachment to the mast (4), the bracing device connecting the base to the mast; —being designed to limit the transverse movements of the mast relative to the base (10) at least when the mast (4) is in a deployed state, and; —comprising at least one connecting member (22, 42, 60) chosen from the group formed by fabrics, non-woven fabrics and ties, the ties being chosen from the group formed by monofilaments, cables, bundles and strips; the structure (1, 2) being characterised in that it comprises a device (30) for tensioning each connecting member of the bracing device when the mast (4) is in the deployed state, the tensioning device (30) enabling a proximal end of the mast (4) to be maintained in the deployed state, at a distance from the base (10) greater than the distance separating the proximal end of the mast (4) from the base (10) when the mast is in the folded state.

The example non-limiting technology herein provides a Synthetic Aperture Radar (SAR) solution on board a micro-satellite that provides global revisit within 1 month; a cost below US$ 10 million; and satellite mass lower than 100 kg. One solution uses an inflatable Cassegrain type antenna with a phased beam steering array in the 1.2 GHz band.

Inflatable support structures and related systems are disclosed. An example antenna system includes a mast configured to support an antenna member. The mast includes a strength member including an inner space that extends along an axis. The strength member is changeable between a first state in which the strength member is rollable along the axis and a second state in which the strength member is rigid along the axis. The mast also includes a sleeve arranged along an outer portion of the strength member. The mast also includes a bladder disposed in the inner space of the strength member and configured to receive a fluid. The first state and the second state of the strength member are based on a fluid pressure in the bladder.

Systems and methods described herein include collapsible and deployable antenna structures. The antenna structures may include any combination of shape memory composites, inflatable envelopes, and/or degradable materials.

An inflatable tracking antenna assembly may include an inflatable antenna. The inflatable antenna may be configurable in a packed configuration and a deployed configuration. In the deployed configuration the inflatable antenna may be generally spherical in shape. The assembly may include an antenna support structure. The support structure may include a plurality of support arms that couple with lateral sides of the inflatable antenna. The support structure may include a base that is coupled with each of the plurality of support arms. The base may include an azimuth actuator that adjusts an azimuth position of the inflatable antenna and an elevation actuator that adjusts an elevation angle of the inflatable antenna. The support structure may include a plurality of support legs that extend outward from the base.

Inflatable support structures and related systems are disclosed. An example antenna system includes a mast configured to support an antenna member. The mast includes a strength member including an inner space that extends along an axis. The strength member is changeable between a first state in which the strength member is rollable along the axis and a second state in which the strength member is rigid along the axis. The mast also includes a sleeve arranged along an outer portion of the strength member. The mast also includes a bladder disposed in the inner space of the strength member and configured to receive a fluid. The first state and the second state of the strength member are based on a fluid pressure in the bladder.

An outer space deployable antenna may include a ground plane and a flexible antenna coupled to the ground plane and moveable between a flat stored configuration and a conical deployed configuration. The flexible antenna may include a dielectric layer and a plurality of antenna arms. The flexible antenna may have a circular shape with a circular sector notch in the flat stored configuration that closes in the conical deployed configuration.

A space deployable antenna apparatus includes an inflatable antenna configurable between a deflated storage position and an inflated deployed position. The inflatable antenna includes collapsible tubular elements coupled together in fluid communication. The collapsible tubular elements in the deployed position include a longitudinally extending boom tubular element, at least one driven tubular conductive element transverse to the boom tubular element, at least one reflector tubular conductive element transverse to the boom tubular element, and at least one director tubular conductive element transverse to the boom tubular element. A foam dispenser is configured to inject a solidifiable foam into the inflatable antenna to configure to the inflated deployed position.

A technique for a dielectric lens and an antenna assembly. The dielectric lens that includes a for a reference surface and a pattern of varying thicknesses made from a first dielectric. The pattern of varying thicknesses is situated on the reference surface. The thickness differences between adjacent formations of the pattern of varying thicknesses is less than an incident wavelength of electromagnetic energy. The antenna includes mounting fixture, the dielectric lens connected to the mounting fixture, and a transceiver operatively coupled to the mounting fixture. The transceiver is configured to transmit an electromagnetic signal directed to the dielectric lens.

The example non-limiting technology herein provides a Synthetic Aperture Radar (SAR) solution on board a micro-satellite that provides global revisit within 1 month; a cost below US$ 10 million; and satellite mass lower than 100 kg. One solution uses an inflatable Cassegrain type antenna with a phased beam steering array in the 1.2 GHz band.