Device, systems, and methods for boom deployment and/or boom stowage are provided in accordance with various embodiments. Some embodiments may facilitate root control of a boom utilizing a variety of tools and techniques. Some embodiments may facilitate boom tip control. Some embodiments may include a boom and a boom spool. Some embodiments include one or more devices that may include: one or more compliant components, one or more boom spreaders, one or more stabilizing tabs, one or more spool locks, one or more boom tip guides, one or more root clamps, and/or a single consolidation roller. Some embodiments include methods that may utilize one or more of the noted devices.

A hold-down release apparatus includes a housing, a reciprocating retention member, a release member, bias member(s), and a fuse wire. The retention member moves between retention and release positions and is biased toward the release position. With the retention member in the release position, the release member can move out of the housing; with the retention member in the retention position, the retention member obstructs the release member from moving out of the housing. The fuse wire obstructs movement of the retention member to the release position and holds the retention member in the retention position against the bias force. With an actuation current flowing through the fuse wire, the bias force breaks the fuse wire, allowing the retention member to move to the release position in response to the bias force, and the release member to move out of the housing.

A deployment and aiming device of an instrument comprises: a first support, a second support to receive the instrument, N mandrels, N being an integer number greater than or equal to 1, positioned around the first support, each of the N mandrels rotationally mobile relative to the first support about a mandrel axis ZN intersecting the mandrel, N linear elements, each of the N linear elements cooperating with one of the N mandrels, each of the N linear elements having first and second ends, wherein the first end of the N linear elements is fixed in the mandrel with which it cooperates at a fixing point, wherein the second end of the N linear elements is linked to the second support, such that a rotation of the mandrel about its axis ZN generates a displacement of the fixing point.

A configurable spacecraft attachment and deployment system and a method of constructing a configurable spacecraft attachment and deployment system are provided herein. In one embodiment, the configurable spacecraft attachment and deployment system includes: (1) a connecting structure configured to secure at least one spacecraft to a launch interface, (2) an actuating assembly configured to constrain the spacecraft to the connecting structure before deployment thereof and release the spacecraft from the connecting structure when deployed, and (3) a deploying mechanism coupled to the connecting structure and configured to eject the spacecraft from the attaching structure, wherein the connecting structure, the actuating assembly, and the deploying mechanism are modular components and the connecting structure and deploying mechanism are selected to form the system based on parameters of the spacecraft.

A deployment device intended to be positioned on a bearing structure, includes a first instrument and a second instrument, a deployment mechanism comprising: a main arm connected to a face of the bearing structure at a first attachment point, on the one hand, and to the first instrument on the other hand, the second instrument being connected to the main arm, a main motor configured to actuate the main arm in relation to the face, a secondary motor configured to actuate the second instrument in relation to the main arm, and in that the two instruments are suitable for passing from a stored configuration, one over the other, on the face of the bearing structure, to a deployed configuration wherein the two instruments are at a distance from one another and from the bearing structure, and/or vice versa.

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.

Various embodiments provide for Corrugated Rollable Tubular Boom (COROTUB) designs. Various embodiments provide a new thin-shell tubular mast design, specifically COROTUB designs, that have unique corrugation features enabled in part by shells only affixed to each other at two respective cross-sectional end web regions.

A nanosatellite with an illumination element, and an arrangement of nanosatellites in low earth orbit (LEO) arranged to controllably apply their illumination to be visible on the ground. The nanosatellites may be coordinated to provide illumination events visible on the ground at particular locations and particular times. Each nanosatellite has an illumination element that provides a sustained external illumination event being of at least momentary duration and to be visible from the ground. The event forms at least part of a display for viewing from the ground.

Various embodiments provide for bistable collapsible tubular mast (Bi-CTM) booms. Various embodiments provide CTM booms that may be bistable in nature, thereby achieving intrinsic benefits bistability may bring. Bistability may be achieved in various embodiments through specific combinations of the thin-shell cross-section geometry and the composite laminate selected for each thin-shell segment Additionally, in various embodiments, the thin-shell geometry of each boom half may be different. Various embodiments may include combinations of circular, ellipsoidal, or parabolic segments that form each shell.

An objective of the present invention is to provide a deployable structure which enables an element even with high rigidity to be folded. A deployable structure (1A) includes a pair of belt-shaped elements (3A, 3A) and a connecting element (4A), wherein the connecting element (4A) connects the pair of belt-shaped elements (3A, 3A) so as to be freely deformable between a folded state and a deployed state, with corners (307) of the pair of belt-shaped elements (3A, 3A) being in contact with each other on their front faces (301) on one side in a thickness direction of the pair of belt-shaped elements (3A, 3A), wherein the pair of belt-shaped elements (3A, 3A) extends in parallel to a predetermined plane xy in the folded state and perpendicular to the predetermined plane xy in the deployed state. Ends of the front faces (301) of the belt-shaped elements (3A, 3A) are connected to the connecting element (4B) via first bent portions (5) which are bendable along the ends. Lateral faces (303, 304) of the pair of belt-shaped elements (3A, 3A) have second cutouts (308) which avoid an interference of the pair of belt-shaped elements (3A, 3A) in the deployed state.