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.

An apparatus includes a primary device, a secondary device, and an umbilical system. The umbilical system comprises an umbilical linking the primary device and the secondary device, and a control system configured alter a directionality of the umbilical during deployment of the secondary device away from the primary device by at least controlling a configuration of a shape memory material comprising the umbilical.

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.

Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

Spacecraft servicing devices or pods and related methods may be configured to be deployed from a carrier spacecraft and include at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The spacecraft servicing devices may be configured to be transported from an initial orbit to another orbit after the spacecraft servicing device is deployed from the carrier spacecraft.

A suspending release device for observing a drop vibration attitude change of a lander and a test method are provided. The device includes a bench system, a lifting system fixed to the bench system, a horizontal frame system, an attitude control system, and a suspending release system hinged to the attitude control system. The horizontal frame system may slide vertically on the bench system and may drive the attitude control system to slide horizontally. A test lander is fixed to a release sliding block. The release sliding block is locked with a main load bearing block. An attitude of the test lander when releasing is adjusted. The horizontal frame system is lifted to a predetermined height. Guide rods are indirectly driven to release the sliding block by a motor. The whole lander falls freely and touches the ground to collide, and the process is recorded by a high-speed camera.

A suspending release device for observing a drop vibration attitude change of a lander and a test method are provided. The device includes a bench system, a lifting system fixed to the bench system, a horizontal frame system, an attitude control system, and a suspending release system hinged to the attitude control system. The horizontal frame system may slide vertically on the bench system and may drive the attitude control system to slide horizontally. A test lander is fixed to a release sliding block. The release sliding block is locked with a main load bearing block. An attitude of the test lander when releasing is adjusted. The horizontal frame system is lifted to a predetermined height. Guide rods are indirectly driven to release the sliding block by a motor. The whole lander falls freely and touches the ground to collide, and the process is recorded by a high-speed camera.

A tether is a net that kinks and is automatically deformed upon tension release. The tether has a length of several kilometers to several tens of kilometers upon deployment and is capable of shrinking to have a length of approximately several tens of meters to several hundreds of meters by kinking and automatically being deformed when the tension is released because of cutting or the like.