koros nekofar

Supplying the energy for the astronaut’s activity is an important factor in space explorations. Space food also reduces the harmful effects of space besides supplying energy. Space food entails a variety of food products, specially created for consumption by astronauts in the outer space. The food has specific properties in order to provide balanced nutrition for individuals working in space, while being easy and safe to store, prepare and consume in theweightless environments of manned spacecraft. Also, foods taken into space must be light-weight, compact, tasty and nutritious. They must also be kept for long periods without refrigeration. A variety of menus of foods provide each astronaut with 2500 or more calories per day. In this paper, the food ingredients required for astronauts and and essential nutritional factors is studied. Additionally, the trend of space food system improvement is mentioned briefly.Furthermore, the effect of situation which exists in the space, like the impact on microgravity, on astronaut’s body, and protection of the astronaut body are mentioned.

In liquid rocket engine design, because of the combustion due to the high temperatures and high rates of heat transfer (1MW / m2 to about 160MW / m2 ) of hot gases to the chamber walls, the cooling thrust chamber is of utmost importance. Also, the thrust chamber cooling design, the selection of appropriate methods, as well as the design and topics related to thrust chamber cooling ducts, double glazing and thermal coating are very important. Liquid propellant engine in the wall of the combustion chamber and nozzle is a necessary part in order to prevent the failure of a cooling system using engine block resistance. In this paper, the combustion process is investigated using a computational fluid dynamics method. To do this, first the similar works in the field are reviewed and then the equations that exist for this process are extracted to determine what equations need to be solved. By examining this method, it was determined that the chosen numerical method could be used to solve the combustion equation. Finally, the simulation results for the geometry in different fluxes are studied which led to acceptable outcomes