by the external mounting of the panel to the core structure preferably using a statically determinate mount that renders the module even less susceptible to vibration transferred from the core structure external mounting removes the panel from the primary structure load path which provides the freedom to adjust the stiffness as desired the use of smaller than conventional equipment panels renders them less responsive to acoustic vibration because the dimensions of the panels are very much less than the wavelengths of the low frequency acoustic energy that is of concern when launching the spacecraft other steps to minimize the vibration response include adding perforations to the equipment panels providing an air gap between adjacent panels adjusting the bending stiffness of the panels to reduce acoustic coupling and damping the vibrations in the panels application_number US 77047896 A description as shown in the drawings for purposes of illustration the present invention pertains to a spacecraft electronics equipment module and more particularly to techniques for reducing the vibration response in a spacecraft electronics equipment module in the past spacecraft modules have been housed in boxes rigidly mounted on a spacecraft core structure and have been thermally and structurally dependent on the core structure this arrangement has exposed the electronic and other equipment to acoustic vibration generated at launch and to launch transients transmitted through the spacecraft structure in accordance with.