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In 1998, the first element of the Earth Observing System, the EOS-AM1 spacecraft, will be launched into a sun-synchronous polar orbit. The EOS-AM1 platform will include five instruments that will form the payload used to provide information on global climate change. The spacecraft will also include a dual frequency (Ku- and S-band) High Gain Antenna (HGA) which will serve as the primary system for transmitting the science data and spacecraft telemetry & command data to the ground via the TRDSS (Tracking and Data Relay Satellite System) network. The HGA assembly consists of a Casgrain reflector subassembly rigidly attached to a box enclosure which contains the Ku-band transponder. The HGA transponder has ten electronic units providing two completely redundant power feeds. Since the TDRSS satellites and the EOS spacecraft are orbiting in different flight paths, data transmission is maintained by continuously repositioning the HGA assembly via a dual-axis gimbal mechanism.

The transient pressure history experienced by spacecraft during launch and ascent creates pressure differences that have to be accounted for in the mechanical design of different spacecraft components. In addition, for high power applications, the venting times must be estimated to ensure that the pressure has dropped below the critical value for corona for both ground testing and in orbit power up. Therefore, an accurate design tool for simulating the venting of multiple enclosures was developed. The Spacecraft Venting Simulation Software (SVSS) calculates the mass flow rates, pressures and pressure differentials for multiple interconnected compartments. The venting can be calculated for circular or annular connections. The flow process can be either isothermal or adiabatic and can simulate various ambient pressure profiles. The mass flow rate is calculated for either a continuum or a molecular flow regime.