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The designing phase:
some parameters used in the designing process of Thermal Control System. There are,

• the environment used for spacecraft has to operate
• the total amount of heat dispersed on board the spacecraft
• the distribution of the thermal dispersed inside the spacecraft
• the temperature of heat requirements of the differ equipment items
• the configuration of the spacecraft, and its verification and reliability requirements

The environment of Thermal control techniques:
for all the spacecraft, the incoming energy from the Sun and the heat send outs to deep space are usually the major environmental interactions. Depends on the spacecraft's attitude and orbit, other parameters can have a major influence on the thermal control design. For sample, the type of the attitude stabilization used can affect the TCS design. In general, spin stabilization is more benign, as the rotation cause to an average of the flux inputs. Three axis stabilized spacecraft needs a greater protection against short term differs in energy input from the Earth or Sun.

Special orbits
The design of missions for the long term observation of the particular phenomena need a fixed, stable environment and tend to make use of stable orbits needing low station keeping requirements, far away from any celestial body. Scientific spacecraft like as scientific mission of SOHO and COBRAS SAMBA, are typical kind of the class of mission. The spacecraft are Sun pointed and have one side fixed illuminated and all other faces are opened to deep space. Serially, the Thermal Control System design can be optimized likely to be easily and there are very special temperature requirements for insufficient electrical power for the heaters.

Deep space and planetary exploration:
This class of mission includes most number of various sub scenarios depending on the particular celestial body. In General, the mission duration and the need for high intensive thermal conditions, like as cruises it’s very close or far away from the low orbiting of the sun and very hot or very cold celestial bodies and descents through the hostile of atmospheres, and survival in the high intensive environments on the surfaces of the bodies visited. The challenge for the Thermal control system is to provide enough rejection of heat capability during the hot acting parts and still the survive the cold inactive ones. The major problem is often the provision of the power and energy required for that survival part.