A new system and apparatus for detachably joining a first component to a second component is disclosed, along with a method for detachably joining two components. Embodiments of the present invention include a tensioning apparatus and system for clamping joints. The tensioning apparatus may include a wedge block and a fastening device. The clamping joint may be a tongue and groove joint that is tightened using the tensioning apparatus.

An apparatus includes a satellite in the form of a plate having a thickness being smaller than a width of the satellite. The apparatus also includes a plurality of contact points distributed on a face of the satellite, allowing for one or more additional satellites to be stacked upon the satellite.

An isolation module between a vibration generating device, such as a satellite launcher, and a structure to be isolated, such as the structure carrying a satellite, comprising: at least two fastening parts, and a connecting means. The first fastening part, called the frame, comprises at least two parallel radial branches, and the second fastening part, called the support, comprises at least one radial branch extending between the two branches of the frame. The connecting means is made from an elastomer material and includes at least one pair of identical elastomer pads, being mounted in series between the frame and the support.

A connecting-separating device is for separating satellites from launchers or satellite dispensers. Circumferentially aligned clamps can be coupled on their inner face on rings of separable elements constituting the union interface between the two separable elements. A release mechanism connects two of the clamps through one of the ends of the clamps. The two clamps are connected by the release mechanism include a protrusion protruding from their outer faces at the end opposite the end connecting with the release mechanism. The rest of the clamps include a protrusion protruding from their outer faces at each of their ends adjacent the adjacent clamps, so that each pair of clamps adjacent and not connected to one another by the release mechanism are connected to one another by connectors connecting the protrusions.

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.

Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Disclosed is a method of manufacturing a final piece including several materials, the final piece being produced at least according to the steps of: inserting an elastomer (5) in at least one insertion cavity (6) of an initial piece (2) so that the elastomer (5) is in contact and fixed with the initial piece (2); then cutting the initial piece (2) in at least two distinct parts (3, 4), so that the at least two distinct parts (3, 4) are fixed together but not in contact with each other, the at least two distinct parts (3, 4) being connected together by the elastomer (5). This may be applied to manufacturing a final piece including several parts, of various natures, connected together.

A structural system and a method for joining a launch vehicle and with satellites are disclosed. The method includes generating centerlines of objects requiring a connection for a structure, generating hemispheres about the centerlines, shelling of the hemispheres; performing a finite element analysis (FEA) for verifying the strength of the structure; and increasing or decreasing the thickness of the hemispheres for providing both optimal strength and minimum mass for the structure. The novel design and construction of interconnected hemispheres provide nearly the maximum physical strength for a given amount of material that could otherwise not be accomplished by utilization of a single spherical structure. In addition, the structure permits the construction of modular elements that are readily constructed using generally low-cost, simple, reliable and verifiable methods.

A payload adapter configured to removably attach to one or more payload bridges. The payload adapter includes a forward open end defined by a forward ring, an aft open end defined by an aft ring, a plurality of truss supports connecting the forward ring and the aft ring to one another, and a plurality of mounting fixtures disposed around a circumference the payload adapter. The mounting fixtures are each configured to releasably attach to a secondary payload bridge.

A system (100) and method (300) for launching multiple satellites from a launch vehicle is provided. The system includes a mechanical structure (102) which has one or more mounting means (104A-F), a control unit (106) for controlling the one or more mounting means for positioning and separating the multiple satellites in the mechanical structure, an image capturing system for monitoring the positioning of each satellite in the mechanical structure. The mounting means are adapted to position the satellites in axial, inclined and radial separations at a distance to ensure that each satellite will not come in contact with each other in short duration as well as long duration of orbit evolution.