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How Computer-Based Artifacts Shape Cognition and Collaboration
Published in David D. Woods, Sidney Dekker, Richard Cook, Leila Johannesen, Nadine Sarter, Behind Human Error, 2017
David D. Woods, Sidney Dekker, Richard Cook, Leila Johannesen, Nadine Sarter
One well-known accident where this representational deficiency contributed to the incident evolution was the Apollo 13 mission (see Murray and Cox, 1989, for an account of mission control activities during the accident). In this accident, an explosion occurred in the oxygen portion of the cryogenics system (oxygen tank 2). One mission controller (the electrical, environmental, and communication controller or EECOM) monitoring this system was examining a screen filled with digital values (see Figure 10.2 for a recreation of this display 8 minutes before the explosion, the CSM ECS CRYO TAB display). Then he and most of the other mission controllers began seeing indications of trouble in the systems that they were responsible for monitoring. Among a host of anomalous indications, EECOM noticed that oxygen tank 2 was depressurized (about 19 psi). It took a precious 54 minutes as a variety of hypotheses were pursued before the team realized that the “command module was dying” and that an explosion in the oxygen portion of the cryogenics system was the source of the trouble. The display had hidden the critical event: two digital values, out of 54 changing digital numbers, had changed anomalously (see Figures 10.2, 10.3, and 10.4).
Chemical Rocket Propellants
Published in D.P. Mishra, Fundamentals of Rocket Propulsion, 2017
Liquid oxygen is the most widely used cryogenic liquid oxidizer propellant along with liquid hydrogen and kerosene for large rocket engine applications as it can provide higher specific impulse. It can be blended with alcohol, jet fuel, and gasoline. Its boiling temperature is 90 K at atmospheric pressure and needs cryogenic system. Hence, liquid oxygen tank and pipe line systems must be insulated properly. Each liquid oxygen tank must be provided with an external drainage system to avoid condensation of moisture. However it is preferred over other oxidizers due to its higher performance. Besides, it is noncorrosive and nontoxic in nature. It was used along with alcohol for the very first time in the V2 missile. Also, along with hydrogen it has found applications in Atlas, Thor, Titan, Saturn boosters, Space Shuttle, Centaur upper stage, GSLV(MkI & II), and so on.
A Novel Approach to Simplified Respirometric Oxygen Demand Determinations
Published in John M. Bell, Proceedings of the 43rd Industrial Waste Conference May 10, 11, 12, 1988, 1989
Cadena Fernando, Aleksander Drohobyczer, Martha I. Beach, David Barnes
Another unique feature of this unit is the oxygen source. Oxygen is supplied to the reactor from a regulated (high-pressure) oxygen tank (breathing or welding grade). Whenever the computer senses a low-pressure signal from the vacuum switch a signal is sent through the DACS to open a solenoid valve. A very consistent oxygen volume is delivered before the valve closes. This oxygen source system insures constant oxygen content in the reactor, and fully isolates the system from the ambient atmos phere. Replacement of oxygen at the same rate as it is being consumed prevents low dissolved oxygen, or anaerobic conditions in the sample (a common malady in systems that rely on atmospheric oxygen).
Reviews of fuel cells and energy storage systems for unmanned undersea vehicles
Published in Energy Sources, Part A: Recovery, Utilization, and Environmental Effects, 2020
Jun Lu, Tian Tang, Chao Bai, Huizhong Gao, Junguang Wang, Cheng Li, Yuke Gao, Zhaoyuan Guo, Xiao Zong
Urashima shown in Figure 3 is the first Japanese UUV powered by PEMFCs. The Japan Agency for Maritime Earth Science and Technology (JAMSTEC) started its development in 1998 (Yoshida et al. 2010). The specifications of Urashima are shown in Table 1. Mitsubishi Heavy Industries (MHI), Ltd. developed its PEMFC system, which consists of two 2 kW fuel cell stacks, recirculation blowers, humidifiers, a heat exchanger, and reaction water storage tank. The whole system is mounted inside a titanium alloy pressure vessel for safety concern. Hydrogen is stored in an AB5 rare earth alloy metal hydride in another pressure vessel which is separated from the fuel cell pressure vessel. The metal hydride releases the hydrogen using heat transferred from the stack through coolant water (Yoshida et al. 2009). Oxygen is stored in a compressed oxygen tank of 0.5 m3 volume at 14.7 MPa. In February 2005, Urashima performed a 317 km autonomous cruise continuously at a depth of 800 m, with an average speed of 3 knots (Toshio et al. 2004). The maximum efficiency of the fuel cells was about 54% at a typical speed. Clear and precise sea floor images were obtained by Urashima.