By Robert Godwin
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Includes the complete group of Apollo 11’s own observations upon returning to earth.
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Additional resources for Apollo 11 : the NASA mission reports
During the coellipt_ c phase, radar tracking data were inserted into the abort guidance system to obtain an independent intercept guidance solution. The primary guidance solution was 6-1/2 minutes later than planned. 5 ft/sec. The line-ofsight rates were low, and the planned braking schedule was used to reach a station-keeping position. In the process of maneuvering the lunar module to the docking attitude, while at the same time avoiding direct sunlight in the forward windows, the platform inadvertently reached gimbal lock.
5). The reduction in throttle setting was predicted to occur 384 seconds after ignition; actual throttle reduction occurred at 386 seconds, indicating nominal performance of the descent engine. The first of five computer alarms occurred approximately 5 minutes after initiation of the descent. 5. Although the alarms did not degrade the performance of any primary guidance or control function, they did interfere with an early assessment by the crew of the landing approach. Arrival at high gate (end of braking phase) to final approach phase program P64 occurred at of 125 ft/sec.
The extravehicular activity preparation checklist was adequate and was closely followed. However, minor items that required a decision in real time or had not been considered before flight required more time than anticipated. 2). This problem had been occasionally encountered using the same equipment before flight. At least i0 minutes were required to connect each unit, and at one point it was thought the connection would not be successfully completed. Considerable difficulty was experienced with voice communications when the extravehicular transceivers were used inside the lunar module.