Technology is disclosed for a spacecraft launch restraint and dispensing structure. Stacks of spacecrafts may be arranged around a central post. The dispensing structure has primary tie-down mechanisms that axially clamp the stacks of spacecrafts when in a stowed position. Each primary tie-down mechanism may have a rod located between two adjacent stacks, such that the rod tensions two stacks. In a deployment position, the primary tie-down rods extend away from the stack such that an ejection path is cleared. The dispensing structure also includes secondary tie-down mechanisms that radially connect the spacecrafts to the central post. After the primary tie-down rods are moved to the deployment position, the secondary tie-down mechanisms still hold the spacecrafts. The spacecrafts may be deployed by issuing control signals to the secondary tie-down mechanisms when the primary tie-down rods are in the deployment position.

The invention relates to a separation device for a spacecraft or launcher. The separation device includes an inner housing divided into at least two portions locked to each other by a locking device in a locking position. The locking device is arranged to move between a locking position and a releasing position. The separation device includes an initiator including means for providing high pressure fluid to an expansion chamber when the separation device is switched from a locked state to a released state. The high pressure fluid in an expansion chamber moves the locking device from the locking position to the releasing position when the separation device is switched from the locked state to the released state. The separation device comprises a dampening arrangement arranged to attenuate a peak load when the separation device is switched from the locked state to the released state.

A secondary payload bridge for a payload adapter is disclosed and includes a body portion, plurality of payload ports, and a secondary payload port. The plurality of attachment points are connected to the body portion of the secondary payload bridge. The plurality of attachment points are configured to removably attach the secondary payload bridge to the payload adapter to allow for clockable positioning of the secondary payload bridge around a circumference of the payload adapter. The secondary payload port is connected to the body portion. The secondary payload port is configured to releasably attach to a corresponding secondary payload.

A joint that is separable by detonating a detonating cord within an expanding tube. The joint is held together with a set of bolts. Each bolt is retained on one side of the joint with a lever. The expanding tube is retained under an arm of each lever. When the detonating cord is activated, the tube expands and exerts a force against an arm of each lever, thereby breaking the set of bolts, and allowing the joint to separate. In one example, the separable joint is used to retain a payload fairing on a launch vehicle so that the fairing can be jettisoned during flight.

A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

A satellite rescue system (SRS) (1) for rescue and recertification of dormant satellites, said SRS having a thruster end (13) with a primary propulsion nozzle (11) and maneuvering thrusters (12) and a satellite connection end (8) with a body (15) between both ends. The satellite connection end of the SRS has an interface ring (14) with clinch clamps (4) that securely attach to a ring (3) on the rescued satellite. An umbilical connector (7) on the satellite connecting end of the SRS provides power and data to the rescued satellite.

A release mechanism for separating two components including: (i) a first plate-shaped member (1) with a first midplane (21) that is connectable to a first component and having two opposite first surfaces (3; 3′) arranged parallel to the first midplane and a first coupling portion (5); (ii) a second plate-shaped member (2) with a second midplane (22) that is connectable to a second component and having two opposite second surfaces (4; 4′) arranged parallel to the second midplane and a second coupling portion (6); (iii) an explosive (9) arranged in the first coupling portion and/or the second coupling portion or between them; and (iv) a plurality of protrusions (10) provided on and firmly connected to at least one of the first surfaces and/or the second surfaces. The first member and the second member are coupled to each other in a mutual midplane comprising the first midplane and the second midplane.

The present technology is directed to thrusting rails for launch vehicles, and associated systems and methods. Certain embodiments of the thrusting rails can include a first rail housing portion having a cavity and a second rail housing portion having a projection positioned at least partially within the cavity. The rails can include a bellows positioned within the cavity and an elongated tube positioned within the bellows. The elongated tube can include a vent opening in a lateral wall of the elongated tube. A shield can be positioned between the vent opening at the bellows and a sleeve can be positioned within the elongated tube. The sleeve can be constructed from a fibrous material and positioned to retain an ordnance within the elongated tube.

A carrier of a spacecraft can include multiple latch assemblies that are linked together and held in place by one notched bolt or main shaft, which is out of the main load path. The latch assemblies secure the payload (e.g., CubeSat device) within a carrier by interfacing with pin assemblies on the payload. To deploy the payload, the shape memory alloy actuator is fired which causes a series of springs and preload forces to rotate latches of the latch assemblies out of the path of the pin assemblies. Once the latches are out of the way, the payload is deployed by a spring-loaded pusher assembly and guided through deployment using rollers. Each latch assembly is preloaded in tension using a corresponding preload lug of a receiver assembly.