Titlebook: Apollo; The Definitive Sourc Richard W. Orloff,David M. Harland Book 2006 Springer-Verlag New York 2006 Apollo.Orloff.Reference.Statistical

软膏

Sums of an Even Number of Squaresthe Block II heat shield for entry at lunar return conditions. These objectives were satisfactorily accomplished..The spacecraft subsystems operated satisfactorily in all respects. Performance of the guidance and control subsystems was equal to or better than predictions. All sequencing and computat

Brittle

Apollo 4: The first test of the Saturn V 9 November 1967,ional operations performed by the guidance computer were correct. The environmental control subsystem maintained the cabin pressure and temperature within required limits. The thermal protection subsystem survived the lunar entry environment satisfactorily. The erosion of the heat shield was between 2.5 and 7.6 mm.

Pessary

刺耳

Book 2006ew the planned lunar landing of a three-man spaceship named Apollo in the mid-1970s. In 1962, it was decided that a specialized vehicle would accompany the main spacecraft, to make the lunar landing while the mothership remained in lunar orbit. To send these vehicles to the Moon would require the de

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Valves

,Saturn I: Development program 1961–1965,s had required to be shut down, and in that case the vehicle had compensated for its loss. But despite its rapid development and flight record the Saturn I had been overtaken by events and was declared obsolete.

Dysplasia

AS-201: The first flight of the Saturn IB: a CSM on a ballistic arc 26 February 1966,ome of the flight measurements were corrupted by an electrical short circuit. In order to provide the time to diagnose and rectify the fault in the SPS engine, AS-202 was rescheduled after AS-203, which was to be an S-IVB development flight that would not carry a spacecraft.

Apoptosis

AS-203: The second flight of the Saturn IB: evaluating the S-IVB 5 July 1966,g coasting flight provided sufficient ullage to maintain the hydrogen settled in its tank, as would be required on a Saturn V dispatching a lunar mission. The simulated restart verified the chilldown and recirculation systems of the J-2 engine. AS-203 was therefore a successful test of the S-IVB sta

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