Separation device assemblies include a first plate defining respective contact surfaces and engagement surfaces and a second plate defining a respective contact surfaces and engagement surfaces. A fracture groove is located on separation walls of the first and second plates. A first end member, a second end member, and the separation wall of the first plate define a first plate expansion device channel and the second plate defines a similar second plate expansion device channel. When assembled, the first plate and the second plate form an expansion device cavity and the first and second plates form a frangible joint. The respective engagement surfaces are configured to engage with receiving channels of attachable mounting devices.

A Marman band clamp has multiple parts, such as two halves, that together make up a ring. The halves are joined by diametrically opposed mechanical connections, one of which is a mechanical release separably mechanically coupled ends of the parts (halves). The mechanical release may include an explosive bolt that is used to release the ends of the halves. The mechanical release may capture portions of the release at the ends of the ring halves after severing of the explosive bolt. A nut may be retained by an end of one of the halves by use of a retainer fastener, such as a pin, to prevent the nut from separating from the ring half end when the bolt is severed. This helps retain the pressurized gases between the severed part of the bolt longer, better using the energy from the pressurized gases to reliably separate the ends of the halves.

Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for passively engaging with and securing the target vehicle.

This disclosure relates generally to a release device utilizing at least two load bearing elements joined by a thermally degradable structural adhesive with an integral heating element to cause thermal degradation of the mechanical properties of the adhesive resulting in separation of the elements under load. The apparatus of the invention is particularly useful for spacecraft and other vehicular separation mechanisms.

A satellite dispenser and method of using same are disclosed. In various embodiments, a satellite dispenser as disclosed herein includes a dispenser body defining an interior cavity to accommodate a payload; and a plurality of externally adjustable restraints positioned within the interior cavity and configured to be extended further into the interior cavity by actuation of a manual interface external to the interior cavity.

A satellite dispenser is disclosed. In various embodiments, a satellite dispenser as disclosed herein includes a dispenser body defining an interior cavity configured to receive a payload; and a composite guide rail comprising a groove configured to receive at least a portion of a payload, the composite guide rail having an orientation that substantially aligns a longitudinal axis of the groove with an ejection axis of the dispenser.

The disclosure relates to an improved satellite deployer system and method utilizing a novel geometric configuration employing a draft geometry between a satellite and a deployer that prevents jamming of a satellite during deployment while simultaneously reducing satellite deployment tipoff rates. The satellite deployer system includes a receptacle having the general shape of an extruded cylinder or polygon with draft. The satellite deployer system includes a satellite shaped to conform with the inside of the receptacle. The satellite deployer system includes a releasable mechanism to hold the satellite in the receptacle. The satellite deployer system includes an ejector mechanism that pushes or pulls the satellite out of the receptacle. The satellite is deployed from the launch vehicle by the ejector mechanism after the releasable mechanism is released.

Technology is disclosed herein for orbit raising of multiple spacecraft launched with a single launch vehicle. Two or more spacecraft are configured in a stacked launch configuration in which a lower spacecraft is mechanically coupled with a payload adapter of a launch vehicle with one or more upper spacecraft above the lower spacecraft. Propellant that is stored in the lower spacecraft during launch is transferred to an upper spacecraft in the stack after launch. The propellent may be used by the upper spacecraft for an orbit raising maneuver that raises the orbit of at least the upper spacecraft from a first orbit to a second orbit. Storing the propellant in the lower spacecraft lowers the center of mass of the stack during launch. Lowering the center of mass reduces the structural bending moment of the stack during launch, which allows a greater total launch mass.

A flow deflector for an aerial vehicle system has a flow deflector body, a clip arranged in an interior of the flow deflector body, and a spring within the clip. The flow deflector body includes a first portion at a forward end shaped to engage a surface of an aerial vehicle body and a second portion at an aft end shaped to engage a surface of a booster engine. The flow deflector body can include a plurality of body segments arranged to form the flow deflector body. The clip may be configured to fit around and engage a portion of an aft flange of the aerial vehicle body. The spring can be preloaded and arranged to press on the aft flange when the clip engages the portion of the aft flange.

A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.