Changes

=== Requirements on Structures ===

====Launch Loading Requirements====

The satellite is carried to its orbit by a launch vehicle in a flight lasting about 17 minutes for Low Earth Orbits. During this period, the vehicle experiences high levels of acceleration, vibrations and shocks which are transmitted to the payloads attached to the flight decks of the vehicle. Launch loads experienced include static loads, vibration loads, acoustic loads and shocks and impose certain strict requirements on the structure of the satellite. Satellite structure should be able to withstand these loads during launch. All the components should be safe and working after the launch. The loading specification for which the launch vehicle interface is tested is assumed to be the loading data for the satellite during launch.

====Transportation and Handling Requirements====

The satellite, once integrated, needs to be handled and transported to the launch site. For this purpose the structures team needs to design a handle for the satellite and a satellite box for transportation. Many factors such as electrostatic charge, vibration, contamination from humidity, pressure management, thermal control needs to be looked at. <br \>

==Thermals ==

The atmosphere above the height of 500 km above Earth comprises of too thin to moderate ambient thermal conditions and consequently, the environment above such a height is prone to extremes of temperature, being directly exposed to solar radiation and deep space. So, the Thermals subsystem needs to ensure all the electrical components of the satellite are well within their operating range. <br \>

Various different methods are employed to ensure the thermal stability. The major two divisions being Active and Passive thermal control. By employing these methods iteratively and analysing the results for different initial conditions, the Thermals team tries to come up with the best possible solution, with minimum increase in mass or power requirements.

===Requirements on Thermals ===

=== Stiffness Requirements ===

To ensure the launch loading requirements listed earlier, mechanical subsystem poses stiffness requirements on the other subsystems. The other subsystems need to ensure that PCBs and other components comply with these requirements so that they have natural frequency well above natural frequency of the launch vehicle. <br \><br \>

'''Note:''' All the requirements listed are the generic set of requirements for a satellite. There could be more requirements sure other constraints from a particular mission.

* ADAMS

* ANSYS