Various enhanced rocket fairings and associated mechanisms are discussed herein for split fairings with two fairing halves. In some implementations, electrically-actuated base clamps are included to deploy the rocket fairing by applying a spring force between a corresponding fairing half and a payload adapter, which directs movement of the fairing halves upwards and away from the payload adapter until release of the fairing halves. In other implementations, electrically-actuated fairing mechanisms are included to hold together a first fairing half and a second fairing half, and separate the first fairing half from the second fairing half using a spring force. In further implementations, one fairing half includes a tab feature configured to overlap a second fairing half. The tab feature can deform inward under a pressure differential between an exterior and a payload envelope to reduce a gap between the two fairing halves.

A payload joint (10) for detachably attaching to each other two adjacent construction elements (2) in a spacecraft and/or launch vehicle, the payload joint (10) comprises two opposing clamps (11a, 11b) and two opposing flanges of the construction elements collaborating with angled surfaces of the clamps (11a, 11b). The payload joint comprises a bolt that connects the clamps (11a, 11b) and drives them towards each other when tightening the payload joint (10). The payload joint (10) further comprises a bolt cutter (101) arranged for cutting the bolt upon activation.

The disclosure concerns a joint (1) for releasably connecting a first space craft element (2) to a second space craft element (3) comprising a first flange (4) on the first space craft element (2) and a second flange (5) on the second space craft element (3). The joint (1) comprises first shoe portions (6) and second shoe portions (13) formed as sectors of a solid of revolution, keeping the flanges (4, 5) together in a longitudinal direction, The shoe portions are positioned next to each other in a circumferential direction the reference to a longitudinal direction of the space crafts. The first shoe portions being arranged to, at a prevailing Coulomb friction, not allow self-locking and the second show portions are arranged to allow self-locking.

A separation system for separable elements of spacecraft and launchers includes an upper ring, a lower ring and a band with an inner channel which houses slidable clamps, which are applied against the upper ring and the lower ring that form the connection interface between the two separable elements. A device joins/separates the ends of the band, both the upper ring and the lower ring including an outer protruding element with a wedged section to be lodged in the clamps. The upper ring also has an inner protruding element with a wedged section that matches a channel shaped section in the lower ring, the lower ring also has an outer portion including the outer protruding element with a wedged section and the channel shaped section, the outer portion protruding from a main part of the lower ring and being spaced from it creating a groove.

A multiple hold-down and release device for spacecraft includes a central structure including a central section with a cylindrical inner hole, an inner axial shaft insertable into the inner hole. A release bolt aligns with the inner axial shaft. A main bushing is partially arranged inside the inner hole and axially guided by guiding bushings on the main bushing and the inner hole. The main bushing includes a protrusion and internal retainer spring. Arms protruding from the central section are axially preloaded by a pusher opposite the central section. Connecting levers each connect to the end of the corresponding arm by the pusher. Hold-down assemblies on the periphery of the device each include a hold-down support and a fastener with conical contact surfaces, a torsion spring around a torsion spring shaft, and articulated with the corresponding hold-down support by the corresponding torsion spring shaft.

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.

A connection system is provided for releasably connecting a first component and a second component in a first direction parallel to a reference longitudinal axis, including one or more locking devices and an actuator. Each locking device has a geometrically locked configuration and an unlocked configuration. In the geometrically locked configuration the locking device is capable of reversibly geometrically locking together the first component and the second component in a mutually clamped relationship along the first direction, each locking device comprising at least two linkage elements pivotably mounted to one another about a common clamp axis. The actuator device is configured for transitioning each locking device from the geometrically locked configuration to the unlocked configuration by selectively applying to each respective locking device an unlocking force directly to the respective linkage elements at the respective common clamp axis, in a second direction parallel to a reference transverse axis.

A payload dispenser for a launch vehicle includes a plurality of panels. At least one panel includes a payload mounted onto the panel. The panels are attachable to each other to thereby form a self-supporting dispenser.

Disclosed is a satellite including a cylindrical main body, the main body having an inner wall defining an inner space and an outer wall, and extending along a main axis between a lower end surface and an upper end surface, at least one of the lower end surface and the upper end surface including an interface mechanism intended for engaging with a complementary interface mechanism of another satellite or of a launcher, the satellite also including at least one external device attached to the outer wall of the main body, the outer device extending to project transversely from the outer wall relative to the main axis.

A release system may include a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space or into a ballistic (non-orbital) trajectory for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly and a biasing element assembly. The actuator release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The biasing element assembly may be configured to provide a configurable force in a first direction normal to a surface of the launch vehicle adaptor plate to separate the space vehicle separation plate from the launch vehicle adaptor plate when the actuator-release mechanism assembly is triggered to release the space vehicle separation plate from the launch vehicle adaptor plate.