Page 27 - Apollo Moonships

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LUNAR MODULE ADAPTER
The Apollo Command-Service Module (CSM) was attached to the third section of the Saturn V rocket (the S-IVB stage) by
a 2-inch-thick aluminum-alloy truncated cone known as the Spacecraft Lunar Module Adapter (SLA). This device, which had a lower section of fixed panels and an upper section
with four deployable panels about 21 feet long, also housed the Lunar Excursion Module (LEM) during the Saturn V launch. The LEM remained attached to the SLA at four places around the joint between the lower and upper sections. These points were equipped with pyrotechnic charges that exploded to release the LEM into space. On the other hand,
the CSM was joined to the SLA by bolts through a flange
that extended around the top edge of the four deployable panels. The CSM was released by a mild explosive train of
28 charges that disengaged the four SLA upper panels when the S-IVB stage went out after placing the Apollo mission in translunar trajectory. Then, the CSM turned 180° to engage the LEM located inside the launch vehicle. As the mother
ship revolved, the four upper panels rotated backwards and opened at an angle of 45°. This action fired the mild explosive train mounted on the outside of the gates to propel them away and avoid a possible collision with the CSM vehicle.
SPACECRAFT SLA PROFILE
J–2 engine
ANGLE OF JETTISON
The panels were pushed away from the SLA at an angle of 110 degrees.
Manufacturer: Height: Diameter: Total weight: Volume: Usable volume:
North American–Rockwell
28 feet
12.79 feet (top)/ 21.65 feet (bottom) 4 050 pounds
6 700 cubic feet
5 000 cubic feet
SPEED OF JETTISON
The deployable panels were jettisoned from the SLA at a speed of 5.5 mph.
Apollo mother ship (CSM)
Command module
S–IVB third stage
section
SLA deployable panel
SLA Lower
Lunar Excursion Module (LEM)
Service Module (SM)
INSTRUMENT UNIT
This cylindrical structure was the nerve center
of the Saturn V rocket. It contained all the electrical and electronic systems needed to control the launch vehicle. Its components included the Environmental Control System, which provided cooling for electronic equipment; the Guidance and Control
System, which determined the course of the rocket through space; the Instrumentation System, which allowed ground control to
track the rocket and monitor their conditions and reactions; the Electrical System, which supplied basic operating power for all systems; and the Structural System, which operated as a load-bearing unit and provided attachment to the components of the Instrument Unit.
Heat exchanger
INSTRUMENT UNIT PROFILE
Measuring distributor
Access door
Batteries
Nitrogen supply
Aluminum ring (Structural system)
Manufacturer: Diameter: Length:
Total weight:
IBM
21.7 feet
3 feet
4 873 pounds
Control distributor
Measuring Rack
Environmental control duct
Launch vehicle digital computer