A method for determining, by reanalysis, a vibratory environment of a coupled vehicle/passenger system. A vehicle is subjected to external forces Fext and is coupled to a new passenger including multiple payloads (e.g., x=I, . . . N payload(s)). At the level of vehicle/passenger interfaces Ix, the method comprising a step DET1) for determining, based on reference interfacial acceleration γ.sub.x_ref of a reference passenger, the interfacial acceleration γ.sub.x′ relative to the new passenger.

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.

Embodiments of the disclosure are directed to a vibration control system and a vibration control device for structurally isolating a load from a vibration source. In various embodiments a vibration isolation device includes a first and support structure and a sidewall extending between and defining a body of the vibration isolation component. In embodiments the sidewall is configured to structurally support the load. In embodiments the sidewall includes one or more lattice portions occupying at least part of a total area of the sidewall, the lattice portions configured to attenuate a transfer of vibrations through the sidewall between the first and second support structures for reducing vibration transfer from the spacecraft vibration source and the load. In embodiments the body of the vibration isolation device is approximately the same as a component without one or more lattice portions such that the payload interface cone is a drop-in replacement.

A satellite is disclosed, including a body having an additively manufactured wall panel and a communication device connected to the body. The wall panel includes a facesheet and a stiffening structure extending from a first side of the facesheet. The communication device is configured to send and receive data while in space.

A reaction compensation device includes a drive mechanism driving a first movable part with respect to a base, a reaction mass drive mechanism driving a second movable part with respect to the base; and a first relative position sensor measuring a relative position between the first movable part and the base. There is also a second relative position sensor measuring a relative position between the second movable part and the base, a first control system controlling the drive mechanism by taking in a signal outputted from the first relative position sensor as a feedback signal in response to a command value, and a second control system correcting the command value using a correction parameter for adjusting a difference between mass properties of the drive mechanism and reaction mass drive mechanism and for controlling the reaction mass drive mechanism.