The present invention discloses an ejection deployment and retrieval mechanism for a tethered satellite with repeatable unlocking and locking and a working method thereof, the present invention includes a separation ejection docking assembly and a sub-satellite; the separation ejection docking assembly includes an ejection sleeve, a locking mechanism, and a sub-satellite connector, the ejection sleeve adopts a two-stage internal-external sliding connection and provides initial kinetic energy to the sub-satellite by compressing a spring; the locking mechanism is mounted inside the ejection sleeve, one end of the sub-satellite connector is connected to the sub-satellite, and another end of the sub-satellite connector is slidably engaged with the locking mechanism to complete the locking/unlocking operations of the sub-satellite. The present invention can effectively reduce the complexity of the mechanism and improve the overall reliability of the mechanism without the additional control assembly to control the unlocking and locking of the mechanism.

A retaining and releasing device for spaceships retains and releases a body to/from a support structure. A releasing bolt keeps the releasable body and the support structure connected in a position for locking the retaining and releasing device. A locking device for locking the releasing bolt in the support structure has a case and a segmented ring. The case is movable axially relative to the releasing bolt and includes an end with a through-slot. A releasing system includes an actuator, a rod having the same orientation as the releasing bolt, with a locking pin, cooperating with the slot, and a compression spring. The actuator locks the rod in a position for locking the retaining and releasing device. The compression spring is in contact with the case of the locking device and disposed around the rod to rotate the rod. The device includes a system for removing the releasing bolt.

A space vehicle includes a body; a stacking pillar coupled to an exterior of the body and defining a longitudinal axis, wherein the stacking pillar is configured to be removably coupled to a stacking pillar of an adjacent space vehicle; and an engagement mechanism including: a pivot point within the stacking pillar defining a pivot axis perpendicular to the longitudinal axis; and a mounting post positioned within the stacking pillar and pivotably engaged with the pivot point so as to be pivotable about the pivot axis between a locked position and an unlocked position, wherein the mounting post is spring-biased to the unlocked position, and wherein the mounting post is configured to restrain the space vehicle from movement away from the adjacent space vehicle when the mounting post is positioned in the locked position and a mounting post of the adjacent space vehicle is positioned in a locked position.