The system (S) to separate at least two mechanical elements (E1, E2), comprises a holding device comprising a connecting screw integral with a mechanical element (E1) and held by a nut segmented in portions (4n) arranged between the connecting screw and an outer envelope integral with the other mechanical element (E2), the system (S) comprising a force generator generating a thrust force (F) in a longitudinal direction (X-X) and comprising an energy accumulator comprising a sealed chamber with a colloid of a porous matrix and liquid, the chamber deforming in the longitudinal direction (X-X) to adapt to the change from a compressed to a decompressed state in order to generate the force (F), and an activatable actuating element to, either apply a predetermined pressure to the chamber to keep the colloid in the compressed state, or not apply the predetermined pressure to allow the change in state of the colloid.

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.

Provided herein are various enhancements to spacecraft or other vehicles, including spacecraft docking mechanisms and vehicle mating systems. In one example, a vehicle mating mechanism includes a latch assembly of a vehicle having soft capture elements and hard capture elements. The soft capture elements accept a bar element of a mating vehicle and retain the bar element to within an envelope that provides a soft capture with the mating vehicle. The hard capture elements move within the envelope to engage the bar element and draw the bar element toward the vehicle to provide a hard capture with the mating vehicle. The vehicle mating mechanism can also include a cup-cone interface element of the vehicle that mates with a cup-cone interface element of the mating vehicle during the hard capture to establish an alignment between the vehicle and the mating vehicle.

Methods, systems, and apparatus for designing, constructing and using instrument landers for in situ exploration of small solar system bodies, such as asteroids and comets. In one aspect, a lander includes a CubeSat-style platform; instrument packaging, wherein the CubeSat-style platform and the instrument packaging are configured and arranged for an uncontrolled descent, hopping landing on a surface of a body in a solar system, where a descending trajectory for the lander is designed based on gravitational force and solar radiation, with no lander-based propulsion; and a mobility mechanism configured and arranged to self-orient the lander on the surface of the body in the solar system.

Disclosed is artificial satellite including: a mounting structure supporting equipment-bearing walls; a launcher-adapter rigidly connected to the mounting structure; a first radiator; and at least one first system for transporting heat by a fluid, including at least one duct having a first heat-exchange section and a second heat-exchange section, the second heat-exchange section being capable of being in thermal contact with the first radiator. The first heat-exchange section is in thermal contact with at least one portion of the launcher-adapter. Also disclosed is a method for filling a tank of propellant gas of the artificial satellite.

A rail-captive sled for deploying payloads into outer space from a space launch vehicle. The sled is driven by a piston, powered by residual tank pressure from a tank native to the space launch vehicle. The rails are arranged parallel and adapted to a cross-sectional shape of a payload, such as small satellites or cubesats. The sled is a box frame sled with an adaptation to receive the piston. The rails may be attached to the residual pressure tank, with the piston in the residual pressure tank and aligned to the rails, or the pressure may be drawn from tank plumbing to a cylinder specific to the piston. The rails have a releasable closure to avoid unplanned egress of the payload, and the closure locks in the open position once released. The piston may be constrained by a direct constraint or by the closure via the payload.

A module separation mechanism, in particular for rockets, includes a cylindrical first body, a cylindrical second body, and a ring connecting the two bodies, The ring comprises at least one tension lock together with a cover. The first body comprises at least one radially mounted actuator that is adapted to eject the tension lock together with the cover from the ring in a manner to disengage the ring. The first body further comprises at least one ejecting member adapted to eject the second body from the first body. The outer surface of the ring together with the cover is faced with the outer surface of the first body and the second body.

A separation device includes: an outer case; a pillar-shaped separation member including an engaging portion; a support member including a swinging portion and an engageable portion, the swinging portion being swingably supported by the outer case, the engageable portion supporting the separation member; an inner case including a fitting hole restricting swinging of the support member; and an operation-enabling element, which supports the inner case and which is fusion-cut when an electric current is applied thereto. When the operation-enabling element is fusion-cut, the inner case is displaced, such that: the engageable portion of the support member detaches from the fitting hole; the swinging portion swings; and the engageable portion moves away from the engaging portion to release the separation member.

A separation system for separable elements of spacecraft and launchers includes an upper ring, a lower ring and a band with an inner channel which houses slidable clamps, which are applied against the upper ring and the lower ring that form the connection interface between the two separable elements. A device joins/separates the ends of the band, both the upper ring and the lower ring including an outer protruding element with a wedged section to be lodged in the clamps. The upper ring also has an inner protruding element with a wedged section that matches a channel shaped section in the lower ring, the lower ring also has an outer portion including the outer protruding element with a wedged section and the channel shaped section, the outer portion protruding from a main part of the lower ring and being spaced from it creating a groove.

A method of releasing artificial satellites into Earth's orbit includes providing an orbital transport spacecraft able to move at orbital height and comprising a cargo area, hooking a plurality of satellites in said cargo area, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height, releasing said orbital transport spacecraft at orbital height, when said space launcher reaches orbital height, by imparting a separation thrust to said orbital transport spacecraft, releasing satellites in sequence from the cargo area. The release of each satellite from the cargo area occurs in a respective predetermined direction and upon the orbital transport spacecraft has reached a respective predetermined position.