Cooling system

Definition and stakes

by NASA,  NASA Project Gemini Familiarization Manual

“ Cooling System SYSTEM DESCRIPTION The spacecraft cooling system consists basically of two identical temperature control circuits functioning independently of each other to provide the cooling requirements for the spacecraft. Each cooling circuit consists of a pump package, thermostatic and directional control valves, various type heat exchangers, radiators, filters, and the necessary plumbing required to provide a closed circuit. The cooling system may be operated in either the primary and/or secondary circuit, and is capable of carrying maximum heat loads in either circuit. ”
Source: Wikisource

by NASA,  NASA Project Gemini Familiarization Manual

“ EVAP PRESS HEATER SWITCH This switch is connected to the evaporator heater and is used to heat the water in the evaporator before dumping.
SYSTEM OPERATION The cooling circuit in which the cooling system operates is dependent upon the temperature loads generated by the equipment, spacecraft phase of flight and the temperature within the spacecraft cabin. Cooling is provided throughout the mission up to pre-retrograde firing. At this time the coolant pump packages are jettisoned with the adapter equipment section, terminating spacecraft cooling.
”
Source: Wikisource

John B. Rathbun,  Practical Hand Book of Gas, Oil and Steam Engines

“ COOLING SYSTEMS The object of the cooling system is not to keep the cylinder cold, but to prevent the heat of the successive explosions from heating the cylinder walls to a degree that would vaporize the lubricating oil and prevent satisfactory lubrication of the cylinder and piston. The hotter the cylinder can be kept without interfering with the lubricating oil, the higher will be the efficiency of the engine and the greater the output of power. ”
Source: Gutenberg

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