Also investigated was crew transfer from the CM to the LEM, to determine the requirements for crew performance and, from this, to define human engineering needs. North American concluded that a separate LEM airlock was not needed but that the CSM oxygen supply system's capacity should be increased to effect LEM pressurization.
On November 29, North American presented the results of docking simulations, which showed that the free flight docking mode was feasible and that the 45-kilogram (100-pound) service module (SM) reaction control system engines were adequate for the terminal phase of docking. The simulations also showed that overall performance of the maneuver was improved by providing the astronaut with an attitude display and some form of alignment aid, such as probe.
On October 11, MSC Crew Systems Division (CSD) tested the suit's mobility with the portable life support system (PLSS). CSD researchers found that the PLSS did not restrict the wearer's movement because the suit supported the weight of the PLSS. Shifts in the center of gravity appeared insignificant. The PLSS controls, because of their location, were difficult to operate, which demanded further investigation.
It was acknowledged that a single mission could not serve to "completely define all the spacecraft functional requirements" but "such a mission has considerable value as a standard for various purposes on the Apollo Program."
Specifically, the DRM would be used for weight reporting, electrical power reporting, reliability modeling, engineering simulation, crew task analyses, mission-related Interface Control Documents, and trade-off studies.
As a result of this analysis, MSC directed Grumman to design the LEM ECS with an all-gaseous oxygen storage system.
|Total LEM||14,515 kg (32,000 lbs)|
|Ascent stage inert||2,193 kg (4,835 lbs)|
|Descent stage inert||2,166 kg (4,775 lbs)|
Also, IESD attended a preliminary design review at Autonetics on the signal conditioning equipment (SCE) for the Block II CSM. IESD concurred in several modifications to the Block I design (adding a redundant power supply; hermetic sealing of equipment; and repackaging to fit the equipment bay in Block II CMs). These changes reduced the SCE's weight from 22 to 19 kg (47.5 to 41 lbs) and, because of more efficient power supply, lowered its power consumption from 65 to 35 watts. North American was studying ways of perhaps lightening the SCE even further.
Phillips told ASPO Manager Joseph F. Shea that if he wished to continue to use GE's service in this area, he would support his request with the stipulation that GE's prediction analysis operation be supervised by MSC personnel.
Flight Operations Director Christopher C. Kraft, Jr., conducted the discussion, with Rodney G. Rose, Carl Kovitz, Morris V. Jenkins, William E. Platt, James E. Hannigan, Bruce H. Walton, and William L. Davidson participating.
The major factors (philosophy) identified at the meeting were:
To provide timely weight status to the Configuration Control Board, Systems Engineering Division was given the responsibility of presenting CSM and LM weight status at each weekly Board meeting as follows:
He added, "An uncrowded time line on the lunar surface for the first mission would seem to me more contributory to the advance of science than trying to do so much on the first mission that we do nothing well. . . ."