Abstract: 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.

Abstract: A shock simulation test apparatus and method utilize a test plate and formed explosive charges to sever or penetrate one or more portions of a suspended test plate in order to subject any attached test item(s) to a realistic pyroshock stimulus. One or more shock measurement sensors, such as accelerometers, may be attached to the test plate or the test item(s) to measure the response to this shock stimulus. The apparatus and method is flexible in that many different scenarios can be simulated from different test plate materials, charge sizes and types. This method replicates actual end-use source shock environments typical in aerospace applications, but can be extended to any industry having a pyroshock environment and test requirement.

Abstract: A shock simulation test apparatus and method utilize a test plate and formed explosive charges to sever or penetrate one or more portions of a suspended test plate in order to subject any attached test item(s) to a realistic pyroshock stimulus. One or more shock measurement sensors, such as accelerometers, may be attached to the test plate or the test item(s) to measure the response to this shock stimulus. The apparatus and method is flexible in that many different scenarios can be simulated from different test plate materials, charge sizes and types. This method replicates actual end-use source shock environments typical in aerospace applications, but can be extended to any industry having a pyroshock environment and test requirement.