Early concepts of Apollo had a single computer that was to be unplugged and moved between the CM and LM. This idea was soon abandoned because of contaminant buildup in the connectors:
Electrical wiring problems were experienced during the Mercury 9 flight wherein contaminants (water, urine, sweat, etc.) migrated to exposed electrical terminals in the zero-g environment. These problems led to the decision to seal all Apollo electrical wiring and connectors. However, the Block I Apollo hardware was already designed and was being built in accordance with the in-flight maintenance concept. This meant that many module-to-black-box connectors and many self-mating black-box-to-spacecraft connectors were required. The attempt to make connectors and modules humidity proof was lengthy, sometimes futile, and practically eliminated any possibility of inflight maintenance. The Block II design change involved repacking the crew compartment equipment into completely sealed units and incorporating built-in and switchable redundancy, as well as backup modes, to achieve the desired reliability and to satisfy the lunar rendezvous mission requirements.
Apollo Program Summary Report, page 4-54
How do electrical connectors on the ISS avoid humidity and contaminant problems?