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 harmless low-consumption on-orbit continuous launch system includes a satellite platform, a launch apparatus and a plurality of CubeSats. The satellite platform carries the launch apparatus and dozens or hundreds of CubeSats, and is launched from a ground into an orbit for on-orbit operation. The launch apparatus is configured to store the plurality of CubeSats and provide power for on-orbit launching of each of the CubeSats. A solid working medium in the launch apparatus is activated by heating to undergo a phase change, and the activated solid working medium expands instantly and is converted into a high-pressure gaseous working medium. The high-pressure gaseous working medium does work to eject the CubeSats, such that the CubeSats obtain a speed increment. The CubeSats enter a transfer orbit towards different target spacecraft through the speed increment applied by the launch apparatus to perform a plurality of different on-orbit serving missions.

The present invention relates to a release system (1, 2, 3, 4, 5), that includes a segmented structural element (10) comprising: a first segment (10a) designed to be coupled to a first structure, a second segment (10b) designed to be coupled to a second structure, and a solder joint (11) joining respective ends of said first (10a) and second (10b) segments, thus holding down the first and second structures with respect to one another; wherein said solder joint (11) is electromagnetically heatable and includes a solder alloy having a predefined melting temperature. The release system (1, 2, 3, 4, 5) is characterized by further including magnetic field generating means (13, PW1, PW2, PW3, PW4, PW5) configured to, upon reception of a release command, generate a time-varying magnetic field through the solder joint (11) such that to cause heating thereof up to the predefined melting temperature of the solder alloy, thereby causing melting of said solder alloy; whereby separation of the first (10a) and second (10b) segments is caused, thus enabling release of the first and second structures from one another.

Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.

A space vehicle element configured to be at least partially destroyed during re-entry of a space vehicle into the atmosphere comprises a heat generating part comprising a metallo-thermal composition for providing additional heat during re-entry of the space vehicle into the atmosphere by an exothermic reaction of the metallo-thermal composition. The destruction of the space vehicle element is expedited by the additional heat provided by the heat generating part. The heat generating part is at least partially integrated within the space vehicle element or at least partially surrounds a portion of the space vehicle element. The application further relates to a corresponding method of manufacturing a space vehicle element configured to be destroyed during re-entry of the space vehicle into the atmosphere.

The invention relates to a device and a method for the connection and linear separation of two elements, such as the two stages of a spacecraft, consisting in using a tube containing a pyrogenic-type material and a glue arranged around the tube, particularly in contact with the elements. The pyrotechnic triggering of the pyrogenic material causes heating and the melting or carbonisation of the glue and the separation of the two elements.

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.

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.

Described is an actuator module (100; 200; 300; 400) for releasing an equipment component, e.g. of a satellite or a rocket, comprising a module base forming a guide sleeve (4; 304), a release body (2; 202; 302) for coupling to the equipment component and inserted into the guide sleeve, which release body (2; 202; 302) is movable relative to the guide sleeve (4; 304) along a sleeve axis thereof from a standby position to a working position, a blocking body (8; 408) mounted on the guide sleeve (4; 304), which, in its blocking position, blocks the release body (2; 202; 302) against movement out of the standby position into the working position and, in its release position, allows movement of the release body (2; 202; 302) from the standby position into the working position, and an actuator unit for moving the blocking body (4; 408) from the blocking position to the release position, the actuator unit comprising at least one actuator wire (12; 13) of shape memory material secured with the wire ends to the module base and coupled to the blocking body for applying an activating force.

A separation adapter for attaching a payload onto a payload dispenser is provided. The separation adapter comprise a rigid structure comprising: a plurality of payload attachment, each payload attachment means operates separately from the other payload attachments means, and is adapted to securely fasten the payload to the rigid structure in a releasable manner, and at least one payload dispenser attachment means, the at least one payload dispenser attachment means is adapted to securely attach the rigid structure to the payload dispenser in a non-releasable fixed manner A method for attaching a payload onto a payload dispenser using a separation adapter and a payload dispenser for carrying a payload of a satellite launch vehicle are also provided.