A vibration isolation/damping satellite mount of a chopped carbon fiber reinforced thermoplastic composite material mainly includes two parts, and the two parts are connected through bolts. Considering the limitation of the molding process, the mount configuration is further optimized, and the mount structure is prepared by using the injection molding process. Furthermore, the vibration isolation/damping satellite mount of the chopped carbon fiber reinforced thermoplastic composite material prepared in the present invention can be used for large loads and complex working conditions, and the connectivity, overall strength stability, vibration isolation performance and service life of the mount all meet the design requirements. The present invention provides an efficient optimization design and manufacturing method for engineering manufacturing of thermoplastic composite materials, and vibration isolation/damping satellite mount manufactured by the method is low in cost, high in practicability and easy to produce on a large scale.

A vibration isolation/damping satellite mount of a chopped carbon fiber reinforced thermoplastic composite material mainly includes two parts, and the two parts are connected through bolts. Considering the limitation of the molding process, the mount configuration is further optimized, and the mount structure is prepared by using the injection molding process. Furthermore, the vibration isolation/damping satellite mount of the chopped carbon fiber reinforced thermoplastic composite material prepared in the present invention can be used for large loads and complex working conditions, and the connectivity, overall strength stability, vibration isolation performance and service life of the mount all meet the design requirements. The present invention provides an efficient optimization design and manufacturing method for engineering manufacturing of thermoplastic composite materials, and vibration isolation/damping satellite mount manufactured by the method is low in cost, high in practicability and easy to produce on a large scale.

A multi-purpose in-situ contamination sampler includes an inner frame surrounded by a plurality of removable or attachable pieces, each of which include of a single witness surface configured to collect both particulate and molecular contamination within an environment on a payload or a spacecraft.

A multi-purpose in-situ contamination sampler includes an inner frame surrounded by a plurality of removable or attachable pieces, each of which include of a single witness surface configured to collect both particulate and molecular contamination within an environment on a payload or a spacecraft.

An elongate flexible waveguide section for radio frequency signals is provided, wherein the waveguide section is corrugated in the longitudinal direction, and the waveguide section is at least partially corrugated in a circumferential direction perpendicular to the longitudinal direction. Also provided is an apparatus for connecting a VHTS antenna system to a spacecraft.

An elongate flexible waveguide section for radio frequency signals is provided, wherein the waveguide section is corrugated in the longitudinal direction, and the waveguide section is at least partially corrugated in a circumferential direction perpendicular to the longitudinal direction. Also provided is an apparatus for connecting a VHTS antenna system to a spacecraft.

A device for orienting a load about a main axis X and a secondary axis Y is disclosed having a first shaft, called transmission shaft, intended to support the load and configured to be rotated about the main axis and the secondary axis, a second shaft configured to be rotated about the main axis X, a third shaft configured to be rotated about a third axis of rotation, in the same direction as the main axis, a first connection component between the transmission shaft and the second shaft, configured to prevent relative movements between the transmission shaft and the second shaft in, on the one hand, a degree of rotational freedom about the main axis X and, on the other hand, three degrees of translational freedom.

A device for orienting a load about a main axis X and a secondary axis Y is disclosed having a first shaft, called transmission shaft, intended to support the load and configured to be rotated about the main axis and the secondary axis, a second shaft configured to be rotated about the main axis X, a third shaft configured to be rotated about a third axis of rotation, in the same direction as the main axis, a first connection component between the transmission shaft and the second shaft, configured to prevent relative movements between the transmission shaft and the second shaft in, on the one hand, a degree of rotational freedom about the main axis X and, on the other hand, three degrees of translational freedom.

Current sensing devices that are capable of surviving harsh ambient environment of ocean worlds, such as Jupiter and Saturn moons are disclosed. The described devices can meet 300 Krad radiation requirements and can survive at cold temperatures down to −184° C. Exemplary implementations of the constituent circuits of the devices are presented. A scheduling algorithm to perform various measurement by the disclosed current sensing devices is also described.

Current sensing devices that are capable of surviving harsh ambient environment of ocean worlds, such as Jupiter and Saturn moons are disclosed. The described devices can meet 300 Krad radiation requirements and can survive at cold temperatures down to −184° C. Exemplary implementations of the constituent circuits of the devices are presented. A scheduling algorithm to perform various measurement by the disclosed current sensing devices is also described.