Disclosed is a space vehicle, such as a satellite, the vehicle including: at least one equipment-carrying module for carrying equipment of the vehicle; at least three posts extending at least partially in the same longitudinal direction and on the periphery of the equipment-carrying module, each post being provided with at least one releasable locking device; and a reinforcing structure which rigidly connects each post transversely to at least two other posts.

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.

Systems and methods for launching space vehicles into outer space are disclosed. Method include powering a thrust augmentation stage of a launch vehicle during an initial portion of a launch trajectory to provide thrust to the launch vehicle; following the initial portion of the launch trajectory, separating a first stage of the launch vehicle from the thrust augmentation stage; powering the first stage of the launch vehicle during the initial portion and during a second portion of the launch trajectory following the initial portion of the launch trajectory to provide thrust to the launch vehicle; and controlling a controlled descent of the thrust augmentation stage to Earth following separation of the thrust augmentation stage from the first stage.

Systems and methods for launching space vehicles into outer space are disclosed. Method include powering a thrust augmentation stage of a launch vehicle during an initial portion of a launch trajectory to provide thrust to the launch vehicle; following the initial portion of the launch trajectory, separating a first stage of the launch vehicle from the thrust augmentation stage; powering the first stage of the launch vehicle during the initial portion and during a second portion of the launch trajectory following the initial portion of the launch trajectory to provide thrust to the launch vehicle; and controlling a controlled descent of the thrust augmentation stage to Earth following separation of the thrust augmentation stage from the first stage.

A frangible manifold is used in connection with flight termination operations and stage separation. The manifold has a first portion and a second portion separated by a frangible portion. An aperture extends through the first, second and third sections. A first ordnance termination line is positioned in at least the first section of the first portion of the manifold. A second ordnance termination line is positioned in at least the second section of the second portion of the manifold. In the event of a flight termination, detonation of one ordnance line causes detonation of the second ordnance line. In the event of stage separation, the manifold splits at the frangible portion and the two ordnance lines are safely separated.

An explosive bolt system includes an explosive bolt and an initiator device. The explosive bolt includes a shank having a first longitudinal end, an opposed second longitudinal end, and a longitudinal axis. The explosive bolt is configured for securing two elements together between the first longitudinal end and the second longitudinal end. The shank includes an internal chamber accommodating a first layer of a high density first secondary explosive material, and further accommodating a second layer of a low density second secondary explosive material in arming communication with the first layer. The initiator device is positioned with respect to the explosive bolt such that the initiator device is in arming communication with the explosive bolt.

A launch apparatus comprising a second stage and a first stage wherein said second stage comprises a second stage space frame; wherein said first stage comprises a first stage space frame; wherein said second stage space frame is approximately pyramid shaped; and wherein said first stage space frame is shaped like a truncated pyramid; and wherein the overall shape of the combined second stage space frame and first stage space frame is pyramidal.

A shaped charge comprising a containment shell, an explosive charge placed in the containment shell and having a V-shaped surface, a fuse placed behind the explosive charge, and a layer of projection material placed in front of the V-shaped surface of the explosive charge. A layer of pyrogenic material is used for heating the projection coating. This pyrogenic material can also be mixed with the explosive charge.

Device for separating a second part from a first part, including a first interface intended to be fixed to the first part and a second interface intended to be fixed to the second part, a docking stud passing through the first and second interfaces and being held at the first interface by a separation nut and at the second interface by a first nut/locknut assembly, the docking stud being covered by a cap secured to the second interface and intended to receive it once the separation nut has broken and the first and second interfaces have been separated, and a retraction spring is provided to extract the docking stud from the first interface, propel it towards a damping material fixed at the bottom of the cap and hold it there by its residual holding force alone.

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