The present invention discloses an SMA wire-driven reusable release mechanism having a self-resetting function. The present invention adopts a structure of two-stage load reduction and one-stage release. First-stage load reduction: a compression rod and a hoop petal, as well as an inclined block and a shell or a sliding block, all cooperate with each other by means of inclined surfaces, which can transfer most of tension load of the compression rod to the shell, leaving only a small part of the load transmitted to a thrust bearing. Second-state load reduction: balls in the thrust bearing are coated with a molybdenum disulfide lubricating coating, which can effectively reduce friction so as to reduce a torque transmitted to a driving shaft. First-stage release: the driving shaft drives a thrust bearing to rotate by a certain angle, causing an upper ring of the thrust bearing to descend to release a certain axial clearance.

Systems, methods, and apparatus for dual port ring compatible satellites are disclosed. In one or more embodiments, a method for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle involves attaching a strongback of each of the spacecrafts to two respective payload ports of the payload attach ring on the launch vehicle. In one or more embodiments, the strongback of each of the spacecrafts is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate. The method further involves separating the strongback of each of the spacecrafts from the two respective payload ports of the payload attach ring on the launch vehicle by using at least one mechanical actuator on each of the beams.

A device for the hold-down and controlled release of space satellites installed on launchers and loads installed on space satellites, includes a blocking member made up of segments radially displaceable from a mutually approached retaining position to a mutually spaced-apart release position of a connecting screw. In order to control the radial displacement of the segments between the retaining position and the release position there are provided a rotatable element coaxial with the blocking member, an articulated mechanism which operatively connects the rotatable element with the segments of the blocking member, and linear motors for driving the controlled rotation of the rotatable element and, through the articulated mechanism, the simultaneous displacement of the segments of the blocking member.

Systems, methods, and apparatus for dual port ring compatible satellites are disclosed. In one or more embodiments, a method for removably attaching at least one spacecraft to a payload attach ring on a launch vehicle involves attaching a strongback of each of the spacecrafts to two respective payload ports of the payload attach ring on the launch vehicle. In one or more embodiments, the strongback of each of the spacecrafts is attached to each of the two respective payload ports via a respective beam mounted to a respective port adaptor plate. The method further involves separating the strongback of each of the spacecrafts from the two respective payload ports of the payload attach ring on the launch vehicle by using at least one mechanical actuator on each of the beams.

A release apparatus for releasing a satellite comprises a release plunger that can be preloaded by a release spring and that is held in a preloaded position by two two-armed pivot levers pivotable about a respective pivot axis, wherein each pivot lever can be held against a force of a spring in a holding position by a release element.

A reusable device for holding and releasing a bar. The device includes a tightening component, a hold and release component, and at least one loosening component. The hold and release component includes a plurality of segments, each segment includes a first bearing surface configured to bear on part of the bar, when the plurality of segments is in a holding configuration under the effect of a tightening pressure generated by the tightening component. The plurality of segments includes a second bearing surface configured to bear on one end of the at least one loosening component. The at least one loosening component is made from a first single-acting shape memory material. Each end of the at least one loosening component exerting a loosening pressure compensating for the tightening pressure, so as to place the hold and release component in a configuration in which the part of the arm is released.

A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.

The device for holding down a mobile structure, e.g., a payload, to a launch vehicle and for releasing the payload comprises a base structure fixed to the launch vehicle, a plate fixed to the payload, a releasable actuator, a release payload mechanism and a release rod are driven to movement in an axial direction relative to the base structure upon activation of the actuator. The base structure and the plate comprises mating surfaces including a concentric shear feature capable of transferring combined shear, axial, and moment loads between the base structure and the plate, with a single point of preloaded axial-only retention.

A spin ejection mechanism and a method of launching objects from extraterrestrial sites is disclosed. The mechanism includes a first bracket. At least one second bracket is spaced apart from the first bracket. At least one guide mechanism is operably coupled between the first bracket and one of the at least one second brackets. The at least one guide mechanism is configured to axially restrain the second bracket. At least one releasable lock mechanism is operably coupled to the at least one second bracket and configured to initiate restrained movement of one of the at least one guide mechanism. A spring-loaded lock mechanism is coupled to the first bracket and configured to initiate unrestrained movement of the at least one guide mechanism.

An actuator module for releasing an equipment component comprising a module base forming a guide sleeve, a release body for coupling to the equipment component and inserted into the guide sleeve, which release body is movable relative to the guide sleeve along a sleeve axis thereof from a standby position to a working position, a blocking body mounted on the guide sleeve, which, in its blocking position, blocks the release body against movement out of the standby position into the working position and, in its release position, allows movement of the release body from the standby position into the working position, and an actuator unit for moving the blocking body from the blocking position to the release position, the actuator unit comprising at least one actuator wire of shape memory material secured with wire ends to the module base and coupled to the blocking body for applying an activating force.