چكيده به لاتين
this dissertation, the satellite heat control subsystem and temperature control methods are introduced and then, considering the active heat control methods,its performance and prototype construction are analyzed and analyzed.Satellites need a temperature control subsystem mainly for two reasons, which is responsible for controlling the temperature of satellite sections and structures. The electrical and mechanical components of a satellite are typically only efficient in a certain temperature range.Also, most materials have contractile and expansion thermophysical properties, so they change shape with temperature.Temperature control of space systems is mainly done in two ways, active and inactive In the active method, unlike the inactive method, the input energy is required, this method is mainly used in human travel.In the construction of the prototype, the Joule-Thomson system is used and by combining the thermoelectric converter of the air conditioner, the efficiency coefficient is higher and the temperature is lower.Types of cryogenic systems include open cycle and closed cycle. In the closed cycle type, cryogenic elements can be in liquid or solid form, which in solid state is superior to liquid, and that is the lifespan of cryogenic.In the cryogenic type, the closed type can be mentioned in two forms: active and impact, which in the active model of the Stirling system is a clear example of use in spacecraft, and the impact model is another type of closed cycle cryogen.Jules Thompson's system is one of the examples used in space missions. In making this sample, by using thermoelectric cooler as an electrical module that generates refrigeration, it is located in the primary converter part of the condenser output and evaporator output in the third layer of this part and reduces the temperature in the superheat part.Thermoelectric coolers usually have a temperature difference of about degrees Celsius due to their power and c This type of combination is used for the first time in this system.an be used according to the ambient temperature.In previous models, cascading systems were used In this type of model, it has higher power consumption and weight than the integrated model. The device has the ability to reduce the temperature by a difference of degrees Celsius.Which changes according to the position of the satellite in space in the evaporator unit.
