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A year in orbit: ISS deployment tests radiation detectors for future space missions
The predawn darkness on a cool Florida night was shattered by the ignition of nine Merlin engines on a SpaceX Falcon 9 rocket. The thrust of the engines shook the ground miles away. From a distance, the rocket appeared to slowly rise above the horizon. For the cargo onboard, the launch was anything but gentle, as the ignition of liquid oxygen generated more than 1.5 million pounds of force. After the rocket had been out of sight for several minutes, the booster dramatically returned to Earth with several sonic booms in a captivating show of engineering designed to make space travel less expensive and more sustainable.
Luiz Rogério Araujo de Araujo, Aquilino Senra Martinez, Roberto Schirru, Renato Kahn
Nuclear Technology | Volume 82 | Number 3 | September 1988 | Pages 324-329
Technical Paper | Heat Transfer and Fluid Flow | doi.org/10.13182/NT88-A34133
Articles are hosted by Taylor and Francis Online.
A computerized system that assists pressurized water reactor (PWR) nuclear plant operators in controlling the saturation margin is described. This system continuously calculates and provides the temperature or pressure margin from saturation, and indicates the temperature and pressure values used for its calculation. The reactor core heatup and cooldown rates are also continuously provided by this computer-based system. The saturation curve is represented by a polynomial approximation as a function of temperature or pressure. Twenty-one analog signals of a PWR power plant are acquired by the system for calculating the margin and temperature variation rates. The man/machine interface is done through the visualization panel, which displays the above-mentioned values. Compared to the temperature and pressure values displayed in the visualization panel, the error of margin is always <0.5%.