Apollo 13 (AS-508): Houston, we have a problem. The Apollo 13 mission was launched at 2: 13 p. m. EST, April 11, 1970 from launch complex 39 A at Kennedy Space Center. The space vehicle crew consisted of James A. Lovell, Jr.
commander, John L. Swig ert, Jr. , command module pilot and Fred W. H aise, Jr. lunar module pilot. The Apollo 13 Mission was planned as a lunar landing mission but was aborted en route to the moon after about 56 hours of flight due to loss of service module cryogenic oxygen and consequent loss of capability to generate electrical power, to provide oxygen and to produce water.
Spacecraft systems performance was nominal until the fans in cryogenic oxygen tank 2 were turned on at 55: 53: 18 ground elapsed time (GET).
About 2 seconds after energizing the fan circuit, a short was indicated in the current from fuel cell 3, which was supplying power to cryogenic oxygen tank 2 fans. Within several additional seconds, two other shorted conditions occurred. Electrical shorts in the fan circuit ignited the wire insulation, causing temperature and pressure to increase within cryogenic oxygen tank 2. When pressure reached the cryogenic oxygen tank 2 relief valve full-flow conditions of 1008 psi, the pressure began decreasing for about 9 seconds, at which time the relief valve probably reseated, causing the pressure to rise again momentarily. About a quarter of a second later, a vibration disturbance was noted on the command module accelerometers.
The Term Paper on Lunar Module Tank Crew Apollo
During a modification of Oxygen Tank No. 2 by NASA contractor, North American Rockwell, it was inadvertently dropped about 2 inches, which caused undetected damage to the interior assemblies. This damage eventually led the failure of the $400-million Apollo 13 mission. The crew of Apollo 13 was responsible for several scientific experiments that were to be carried out during the mission. ...
The next series of events occurred within a fraction of a second between the accelerometer disturbances and the data loss. A tank line burst, because of heat, in the vacuum jacket pressurizing the annulus and, in turn, causing the blow-out plug on the vacuum jacket to rupture. Some mechanism in bay 4 combined with the oxygen buildup in that bay to cause a rapid pressure rise which resulted in separation of the outer panel. The panel struck one of the dishes of the high-gain antenna. The panel separation shock closed the fuel cell 1 and 3 oxygen reactant shut-off valves and several propellant and helium isolation valves in the reaction control system. Data were lost for about 1.
8 seconds as the high-gain antenna switched from narrow beam to wide beam, because of the antenna being hit and damaged. As a result of these occurrences, the CM was powered down and the LM was configured to supply the necessary power and other consumables. The CSM was powered down at approximately 58: 40 GET. The surge tank andre pressurization package were isolated with approximately 860 psi residual pressure (approx.
6. 5 lbs of oxygen total).
The primary water glycol system was left with radiators bypassed. All LM systems performed satisfactorily in providing the necessary power and environmental control to the spacecraft.
The requirement for lithium hydroxide to remove carbon dioxide from the spacecraft atmosphere was met by a combination of the CM and LM cartridges since the LM cartridges alone would not satisfy the total requirement. The crew, with direction from Mission Control, built an adapter for the CM cartridges to accept LM hoses. The service module was jettisoned at approximately 138 hours GET, and the crew observed and photographed the bay-4 area where the cryogenic tank anomaly had occurred. At this time, the crew remarked that the outer skin covering for bay-4 had been severely damaged, with a large portion missing. The LM was jettisoned about 1 hour before entry, which was performed nominally using primary guidance and navigation system.
