Spacecraft thermal control
In spacecraft design, the function of the thermal control system (TCS) is to keep all the spacecraft's component systems within acceptable temperature ranges during all mission phases. It must cope with the external environment, which can vary in a wide range as the spacecraft is exposed to the extreme coldness found in the shadows of deep space or to the intense heat found in the unfiltered direct sunlight of outer space. A TCS must also moderate the internal heat generated by the operation of the spacecraft it serves. A TCS can eject heat passively through the  simple and natural infrared radiation of the spacecraft itself, or actively through an externally mounted infrared radiation coil. Thermal control is essential to guarantee the optimal performance and success of the mission because if a component is subjected to temperatures which are too high or too low, it could be damaged or its performance could be severely affected. Thermal control is also necessary to keep specific components (such as optical sensors, atomic clocks, etc.) within a specified temperature stability requirement, to ensure that they perform as efficiently as possible. Active or passive systems. The thermal control subsystem can be composed  of both passive and active items and works in two ways: Passive thermal control system (PTCS) components include: Active thermal control system (ATCS) components include: Environment. For a spacecraft the main environmental interactions are the energy coming from the Sun and the heat radiated to deep space. Other parameters also influence the thermal control system design such as the spacecraft's altitude, orbit, attitude stabilization, and spacecraft shape. Different types of orbit, such as low Earth orbit and geostationary orbit, also affect the design of the thermal control system. Temperature requirements. The temperature requirements of the instruments and equipment on  board are the main factors in the design of the thermal control system. The goal of the TCS is to keep all the instruments working within their allowable temperature range. All of the electronic instruments on board the spacecraft, such as cameras, data-collection devices, batteries, etc., have a fixed operating temperature range. Keeping these instruments in their optimal operational temperature range is crucial for every mission. Some examples of temperature ranges include Current technologies. Coating. Coatings are the simplest and least expensive of the TCS techniques. A coating may be paint or a more sophisticated chemical applied to the  surfaces of the spacecraft to lower or increase heat transfer. The characteristics of the type of coating depends on their absorptivity, emissivity, transparency, and reflectivity. The main disadvantage of coating is that it degrades quickly due to the operating environment. Multilayer insulation (MLI). Multilayer insulation (MLI) is the most common passive thermal control element used on spacecraft. MLI prevents both heat losses to the environment and excessive heating from the environment. Spacecraft components such as propellant tanks, propellant lines, batteries, and solid rocket motors are also covered in MLI blankets to maintain ideal operating temperature. MLI consist of an outer  cover layer, interior layer, and an inner cover layer. The outer cover layer needs to be opaque to sunlight, generate a low amount of particulate contaminates, and be able to survive in the environment and temperature to which the spacecraft will be exposed. Some common materials used for the outer layer are fiberglass woven cloth impregnated with PTFE Teflon, PVF reinforced with Nomex bonded with polyester adhesive, and FEP Teflon. The general requirement for the interior layer is that it needs to have a low emittance. The most commonly used material for this layer is Mylar aluminized on one or  both sides. The interior layers are usually thin compared to the outer layer to save weight and are perforated to aid in venting trapped air during launch. The inner cover faces the spacecraft hardware and is used to protect the thin interior layers. Inner covers are often not aluminized in order to prevent electrical shorts. Some materials used for the inner covers are Dacron and Nomex netting. Mylar is not used because of flammability concerns. MLI blankets are an important element of the thermal control system. Louvers. Louvers are active thermal control elements that are used in many different forms . Most commonly they are placed over external radiators, louvers can also be used to control heat transfer between internal spacecraft surfaces or be placed on openings on the spacecraft walls. A louver in its fully open state can reject six times as much heat as it does in its fully closed state, with no power required to operate it. The most commonly used louver is the bimetallic, spring-actuated, rectangular blade louver also known as venetian-blind louver. Louver radiator assemblies consist of five main elements: baseplate, blades, actuators, sensing elements, and structural elements. Heaters. Heaters are used in thermal  control design to protect components under cold-case environmental conditions or to make up for heat that is not dissipated. Heaters are used with thermostats or solid-state controllers to provide exact temperature control of a particular component. Another common use for heaters is to warm up components to their minimal operating temperatures before the components are turned on. Radiators. Excess waste heat created on the spacecraft is rejected to space by the use of radiators. Radiators come in several different forms, such as spacecraft structural panels, flat-plate radiators mounted to the side of the spacecraft, and panels deployed  after the spacecraft is on orbit. Whatever the configuration, all radiators reject heat by infrared (IR) radiation from their surfaces. The radiating power depends on the surface's emittance and temperature. The radiator must reject both the spacecraft waste heat and any radiant-heat loads from the environment. Most radiators are therefore given surface finishes with high IR emittance to maximize heat rejection and low solar absorptance to limit heat from the Sun. Most spacecraft radiators reject between 100 and 350 W of internally generated electronics waste heat per square meter. Radiators' weight typically varies from almost nothing, if an  existing structural panel is used as a radiator, to around 12 kg/m for a heavy deployable radiator and its support structure. The radiators of the International Space Station are clearly visible as arrays of white square panels attached to the main truss. Heat pipes. Heat pipes use a closed two-phase liquid-flow cycle with an evaporator and a condenser to transport relatively large quantities of heat from one location to another without electrical power. Events. A major event in the field of space thermal control is the International Conference on Environmental Systems, organized every year by AIAA. Another  is the European Space Thermal Analysis Workshop Sun shield. In spacecraft design, a Sun shield restricts or reduces heat caused by sunlight hitting a spacecraft. An example of use of a thermal shield is on the Infrared Space Observatory. The ISO sunshield helped protect the cryostat from sunlight, and it was also covered with solar panels. Not to be confused with the concept of a global-scale Sun shield in geoengineering, often called a Space sunshade or "Sun shield", in which the spacecraft itself is used to block sunlight to a planet. An example of a sunshield in spacecraft design  is the sunshield on the James Webb Space Telescope.