A space vehicle system, a method of manufacturing a multiple space vehicle system, and a method of disposing space vehicles into Earth orbit are disclosed. The space vehicle system may include a first space vehicle including a first core structure with a first wall thickness. The space vehicle system may include a second space vehicle including a second core structure with a second wall thickness, the second wall thickness different from the first wall thickness, and the second core structure releasably attached to the first space vehicle in a stacked configuration.

A payload mounting system including a launch vehicle attach structure with radial ports, payloads, and a moment transmitting structure. The payloads attach to the radial ports. The moment transmitting structure attaches to the payloads surrounding said launch vehicle attach structure to minimize the moment transmitted to the radial ports thus maximizing the launch mass capability of the launch vehicle attach structure. The payload mounting system presents a novel evolved expendable launch vehicle (EELV) secondary payload adapter (ESPA) port small payload mounting system that permits maximum mass utilization of each ESPA ports without regard to center of gravity constraints. In one or more embodiments, the payload mounting system enables to connect, in the unused central volume of an ESPA ring, the adjacent faces of at least two payloads on opposing sides of an ESPA ring with a cross-reaching moment transmitting structure that reduces moments transmitted to the ESPA ring.

A pipeline separation device for liquid-propellant rocket comprising a first flange pipeline, a second flange pipeline, a clamping unit, a push-and-pull unit and an actuation unit. The first flange pipeline and the second flange pipeline dock along a first direction, a docking end surface docking with each other is limited by the clamping unit, and end surfaces opposite to each other after docking of the first flange pipeline and the second flange pipeline are respectively used for connecting with different medium pipelines; the actuation unit is used for pushing the push-and-pull unit so that the clamping unit relieves limit on the docking end surface. Being provided with a clamping unit and an actuation unit, the pipeline separation device for liquid-propellant rocket is capable of quickly pushing the clamping unit out when the actuation unit works, thereby relieving the limit on the first flange pipeline and the second flange pipeline.

To enable a local connection with separation on command, a connection device (20) comprises a first base plate (24), a first connection wall (22) forming a protuberance from the first base plate (24) and having an internal surface (22A) delimiting an internal volume (V) located on the side of the first base plate, on a first side, and a first connection surface (22B), a second base plate (28), a second connection wall (26) fixed to the second base plate on a second side and with a second connection surface (26A) covering the first connection wall (22) so as to form a space (S) between the first and second connection surfaces, a bonding layer (30) arranged in the space and extending along at least two distinct directions, and a heat generating material (32) arranged in an internal volume so as to enable heating of the bonding layer.

A pipeline separation device for liquid-propellant rocket comprising a first flange pipeline, a second flange pipeline, a clamping unit, a push-and-pull unit and an actuation unit. The first flange pipeline and the second flange pipeline dock along a first direction, a docking end surface docking with each other is limited by the clamping unit, and end surfaces opposite to each other after docking of the first flange pipeline and the second flange pipeline are respectively used for connecting with different medium pipelines; the actuation unit is used for pushing the push-and-pull unit so that the clamping unit relieves limit on the docking end surface. Being provided with a clamping unit and an actuation unit, the pipeline separation device for liquid-propellant rocket is capable of quickly pushing the clamping unit out when the actuation unit works, thereby relieving the limit on the first flange pipeline and the second flange pipeline.

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.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.

A system for securing spacecraft to a rocket and deploying the spacecraft into orbit includes a stack having a plurality of spacecraft arranged in layers, with each spacecraft being releasably mated with at least one spacecraft in an adjacent layer, and at least one hold down and deploy assembly configured to, in a first configuration, secure the layers of the stack together and secure the entire stack to the rocket, and, in a second configuration, release the entire stack from the rocket into orbit such that the layers passively separate.

The disclosure provides a connection and separation device driven by memory alloy wires, including an active end and a passive end. The active end includes a housing, an outer sleeve, fixed sheets, compression springs, a rotating sleeve, a base, memory alloy wires, guide wheels, a lock pin, a limiting sleeve I and a limiting sleeve II. The passive end includes a screw rod, a loading nut, a separation element and an adaptor. The upper end of the screw rod is provided with a threaded section matched with the loading nut, and the lower end of the screw rod is provided with multi-layer oblique protrusions. The multi-layer oblique protrusions extend into the upper part of an accommodating space formed by the limiting sleeve I and the limiting sleeve II. The memory alloy wires are shortened when being electrified, the base and the lock pin move up, the lock pin releases the limit on the lower ends of the limiting sleeve I and the limiting sleeve II, the two limiting sleeves rotate at the same time, the lower parts of the limiting sleeve I and the limiting sleeve II are folded, and the upper parts of the limiting sleeve I and the limiting sleeve II are opened and separated from the screw rod, so as to realize the separation of the active end and the passive end. The disclosure realizes quick separation and has the advantages of no impact, energy saving and environmental protection, small size, high reliability and reusability.

A separation device for a spacecraft or launcher, separation device being movable from a locked state, in which the separation device is arranged to lock onto a component of a spacecraft or launcher, to a released state, in which component is released, separation device including: an inner housing divided into at least two portions for locking onto component of spacecraft or launcher, and a locking arrangement arranged to move between a locking configuration and a releasing configuration, wherein the locking configuration is such that said at least two portions of inner housing are prevented from separating, wherein said locking arrangement includes: a first part arranged to at least partially enclose said at least two portions of inner housing when locking arrangement is in the locking configuration.