URGENTTTT !!!!!! WILL DO UPVOTE

/////// Justified assumptions can be made with reasons provided //////

problem statement

A spacecraft spherical in shape traveling through space, with known surface area and an internal Volume. The outer surface of Spacecraft is made of sand which act as thermal shield. The outside temperature when the spacecraft is facing the sun is known and also when the Earth is blocking the direct thermal radiation from the sun. while the crew compartment must be maintained at ambient temperature. Assume heat generation in spacecraft is due to thermal units (Heat generated inside is known) which consists of electronic circuits, engine, and heater along with two human presents in it. The human body also emit heat which known. The heat from the spacecraft can be removed through the radiators installed. How the waste heat will be removed will also be considered. It could be removed in two ways, through cold plates and heat exchangers, both of which are cooled by a circulating water loop. Air and water heat exchangers cool and dehumidify the spacecraft's internal atmosphere. High heat generators are attached to custom-built cold plates. Cold water which is circulated by pump through these heat-exchanging devices to cool the equipment. The excess heat is removed by this very efficient liquid heat-exchange system, which is then send to radiators to reject that heat into space. Instead of actual shape of spacecraft the spherical shape simply the problem up to great extant and provide a good approximation and its difficult to solve it in actual shape.

Required parameters: velocity= 100km/sec Surface area= 30m^2 Internal vol= 10m^3 Max (Outside temp) = 1500c Min (Outside temp) = -170c Ambient temp = 20-25c Heat generation= 10000kj/hr Human body heat= 400kj/hr Sand thermal conductivity= 800j/kg.K Emissivity of sand= 0.96 Cold water circulation pump= 17,000-rpm Thermal emissivity of aluminium= 0.09

To find

1. List out all the required data and physical properties required. Make reasonable realistic assumptions wherever required for clear understanding of the problem. 2. Determine rate of heat transfer and total heat generation in (spherical coordinates r, and ) using energy balance. Take into consideration all the three modes of heat exchange. 3. Design the cooling and heating system by determining the dimensions. 4. Calculate and plot the profile of temperature in the space vehicle under consideration. 5. Select the effective and economical cooling water circulation system.