A method and apparatus for deploying a space structure. The space structure is secured to a base with release mechanisms that engage features of the space structure when the base is in a first position. The base is moved from the first position to a second position to deploy the space structure. The release mechanisms are moved at substantially a same time to disengage from the features and release the space structure from the base without imparting a transverse load to the space structure when the base moves from the first position towards the second position to deploy the space structure.

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.

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.