A multi-layer insulation includes a plurality of layers that are laminated on each other. A detection layer that is at least one of the plurality of layers has a piezoelectric film, and a pair of electrode parts installed on both surfaces of the piezoelectric film.

A system and method for vaporizing space debris in space. The system includes a spacecraft body, a primary solar concentrator mounted to the spacecraft body that collects and focuses solar flux from the sun, and a secondary solar concentrator positioned at a focal point of the primary solar concentrator that refocuses the focused solar flux. A manipulator arm coupled to the spacecraft body grabs the space debris in space and positions it at a location where the refocused solar flux vaporizes the debris. The secondary solar concentrator can be a point-source concentrator, the primary solar concentrator can be a parabolic mirror, a Fresnel lens or a light focusing element or assembly, and the space debris can be a retired spacecraft or launch vehicle upper stage or component.

A pivot mechanism for guiding in rotation comprises a mobile element connected to a fixed element through flexible connections; with the flexible elements being configured to guide the mobile element according to a rotational movement in a plane, around a pivoting axis perpendicular to the plane; with each of the flexible connections comprising an intermediary junction provided with an expansion slot, the expansion slot being configured to expand during the rotation of the mobile element, so that the mobile element can pivot according to a second angular amplitude that is greater than a first angular amplitude achieved without said expansion slot; with the intermediary junctions being connected to one another by a coupling member; each of the coupling members being configured so as to prevent a movement out of the plane and a lateral movement in the plane of the mobile element. The pivot mechanism has a very high rotational amplitude.

A pivot mechanism for guiding in rotation comprises a mobile element connected to a fixed element through flexible connections; with the flexible elements being configured to guide the mobile element according to a rotational movement in a plane, around a pivoting axis perpendicular to the plane; with each of the flexible connections comprising an intermediary junction provided with an expansion slot, the expansion slot being configured to expand during the rotation of the mobile element, so that the mobile element can pivot according to a second angular amplitude that is greater than a first angular amplitude achieved without said expansion slot; with the intermediary junctions being connected to one another by a coupling member; each of the coupling members being configured so as to prevent a movement out of the plane and a lateral movement in the plane of the mobile element. The pivot mechanism has a very high rotational amplitude.

The present disclosure relates to a mechanism for releasably securing components of a spacecraft together during launch until such time as the mechanism is commanded to release those components. Upon command, the components are then released with extremely low shock forces being transmitted to the previously secured components due to the release.

A sample capture assembly and method of operating is provided. The assembly includes a sampler device configured to retrieve a sample from a surface. A first bellows having a first inlet is fluidly coupled to the sample device, the bellows being selectively movable between a compressed and an extended position. A gate valve having a second inlet is coupled to an end of the first bellows opposite the first inlet. A sample container is fluidly coupled to the gate valve.

A sample capture assembly and method of operating is provided. The assembly includes a sampler device configured to retrieve a sample from a surface. A first bellows having a first inlet is fluidly coupled to the sample device, the bellows being selectively movable between a compressed and an extended position. A gate valve having a second inlet is coupled to an end of the first bellows opposite the first inlet. A sample container is fluidly coupled to the gate valve.

Methods and apparatus for Real-time Satellite Imaging System (10) are disclosed. More particularly, one embodiment of the present invention an imaging sensor (14) on a geostationary satellite having one or more co-collimated telescopes (18). The telescopes (18) illuminate local planes (22) which are sparsely populated with focal plane arrays (24). The focal plane arrays (24) record the entire observable Earth hemisphere at one time, at least once every ten seconds.

A method for capturing and deorbiting space debris includes: providing a space debris capturing device; deploying the space debris capturing device in planetary orbit; determining, via an onboard global positioning system unit, the position and orbit velocity of the space debris capturing device; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device, the second database is smaller than the first database; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device, the third database is smaller than the second database; transferring the space debris capturing device to a position within a capture range of a first space debris target of the third database; capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; repeating the transferring, capturing, and jettisoning steps for all but a final one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

A method for capturing and deorbiting space debris includes: providing a space debris capturing device; deploying the space debris capturing device in planetary orbit; determining, via an onboard global positioning system unit, the position and orbit velocity of the space debris capturing device; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device, the second database is smaller than the first database; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device, the third database is smaller than the second database; transferring the space debris capturing device to a position within a capture range of a first space debris target of the third database; capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; repeating the transferring, capturing, and jettisoning steps for all but a final one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.