A device for automatically releasing cremated ashes, including a chamber for containing cremated ashes; and a release mechanism configured to selectively release cremated ashes contained in the chamber to the external environment. The release mechanism includes an annular outer member, and an inner member at least partially radially inward of the outer member. The outer member includes an outlet from the chamber. The release mechanism is configured to translate the inner member and the outer member relative to each other along a common longitudinal axis from a first relative position, in which release of cremated ashes in the chamber through the outlet is inhibited, to a second relative position, in which release of cremated ashes in the chamber through the outlet is enabled. In the first relative position, the inner member is in contact with the outer member so as to cover the outlet. In the second relative position, the inner member is spaced from the outer member.

An example liquid mirror includes a first ionic liquid and a second ionic liquid. The first and second ionic liquids are immiscible with each other. The liquid mirror also includes a plurality of reflective particles configured to self-assemble at an interface between the first and second ionic liquids.

A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.

A spacecraft, reconfigurable from a launch configuration to an on-orbit configuration, includes a main body structure, a manipulator, a first deployable rigid reflector and an attachment arrangement, including at least one hold-down assembly (HDA). In the launch configuration, the HDA is in a fully engaged configuration such that the attachment arrangement mechanically attaches the first reflector with the spacecraft main body structure and prevents relative motion between the first reflector and the spacecraft main body. Reconfiguring the spacecraft from the launch configuration to the on-orbit configuration includes (i) actuating the HDA from the fully engaged configuration to a partially engaged configuration; (ii) grasping and moving the first reflector, with the manipulator, a distance in the first direction; and (iii) moving the first reflector from a first position proximate to the attachment arrangement to a second position proximate to a deployed position associated with the on-orbit configuration.

A spacecraft includes a first deployable module and a second deployable module and is reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable module is adjacent to the second deployable module. The first deployable module includes a first solar array, the first solar array being rotatable, in the on-orbit configuration, about a first axis of rotation, and the second deployable module includes a second solar array, the second solar array being rotatable, in the on-orbit configuration, about a second axis of rotation, the second axis of rotation being separated by a substantial distance from the second axis of rotation.

A deployment device intended to be positioned on a bearing structure, includes a first instrument and a second instrument, a deployment mechanism comprising: a main arm connected to a face of the bearing structure at a first attachment point, on the one hand, and to the first instrument on the other hand, the second instrument being connected to the main arm, a main motor configured to actuate the main arm in relation to the face, a secondary motor configured to actuate the second instrument in relation to the main arm, and in that the two instruments are suitable for passing from a stored configuration, one over the other, on the face of the bearing structure, to a deployed configuration wherein the two instruments are at a distance from one another and from the bearing structure, and/or vice versa.

A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

A stereostructure spacecraft of the present invention comprises multiple deployable beam members, multiple tension members, and a spacecraft for storing the deployable beam members and the tension members. The stereostructure spacecraft is formed by deploying the deployable beam members and the tension members around the spacecraft. The deployable beam members stored in the spacecraft are deployed and arranged equidistantly in directions of multiple rotational symmetry axes, the rotational symmetry axes being rotational symmetry axes of a virtual polyhedron that is formed to have a substantial center of the spacecraft as an origin. The tension members support two end portions of two adjacent deployable beam members with tension. The respective end portions of the deployable beam members are simultaneously supported by three or more of the tension members.

Systems and methods described herein include collapsible and deployable structures that may be used as antenna, collectors, reflectors, or other large structures. The systems and methods may use modular designs so that larger structures may be obtained for space applications.

A device for automatically releasing cremated ashes, including a chamber for containing cremated ashes; and a release mechanism configured to selectively release cremated ashes contained in the chamber to the external environment. The release mechanism includes an annular outer member, and an inner member at least partially radially inward of the outer member. The outer member includes an outlet from the chamber. The release mechanism is configured to translate the inner member and the outer member relative to each other along a common longitudinal axis from a first relative position, in which release of cremated ashes in the chamber through the outlet is inhibited, to a second relative position, in which release of cremated ashes in the chamber through the outlet is enabled. In the first relative position, the inner member is in contact with the outer member so as to cover the outlet. In the second relative position, the inner member is spaced from the outer member.