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Reducing the amount of physical testing is of importance in the aeronautical industry, where each physical test represents a significant cost. Apart from the cost aspect, it may also be difficult or hazardous to carry out physical testing. Specific to the aeronautic industry are also the relatively long development cycles, implying long periods of uncertainty during product development. In any industry a common viewpoint is that of verification, validation, and uncertainty quantification using simulation models are critical activities for a successful development of a product. In Aeronautical application, the design of store's structural equipments needs to be certified in accordance with MIL-T-7743F [1]. This paper focuses on a case study for shock analysis, whereby an attempt has been made to reduce the cost of certification by way of replacing the actual physical testing by a reliable high fidelity FE simulation.

The capabilities of micro satellites continue to grow more sophisticated with each passing year, allowing them to be used to carryout different types of missions those once required with much large satellite platforms. The miniaturization of electronic components enabled to develop satellites of small size, ranging 10–100 kg. The benefits of developing the micro satellite leads to shorter development times and much lower costs than for larger satellite while achieving high levels of performance and capability. This paper summarizes the preliminary design, i.e. selection of suitable structural configuration and vibration analysis of a micro satellite structure of mass not exceeding 50kg. The envelope allowed for the satellite as a secondary payload by polar satellite launch vehicle is 600*600*600 mm3. Since it is a spinning satellite having spin rates between 4 to 8 rpm, the Moment of Inertia about the spinning axis should be greater than other two axes by at least 11%.

In recent years satellites of small sizes have been in development. Since electronic components are miniaturized and efficient, it is possible to develop satellite of small dimensions. The spirit of development of the small satellite in the world has been encompassed by the slogan “faster, better, smaller, cheaper”. The classes of satellite, which have the mass ranging from 10–100 kg, is called the micro-satellite. There are number of analysis like sensitivity analysis, vibration analysis, dynamic analysis and thermal analysis to be carried out in the development of the micro satellite both theoretically and experimentally. This paper discusses the free vibration analysis of a micro-satellite of mass less than 60kg. The micro satellite considered for this analysis is a spinning cuboids structure of 600mmx600mmx600mm dimensions with 18 subsystems positioned so as to meet the C.G and M.I. constraints.