Design a solid or hybrid upper stage propulsion module (pm) with the capability to boost a 181 kg payload from a 352 km circular orbit to a 704 km circular orbit. of the 181 kg payload, 125 kg is allocated for the experimental satellite, leaving no more than 56 kg for the pm. show your design’s a) throat area b) exit area c) exhaust velocity d) mass flow rate state any assumptions that you make. hint, it takes 0.52 m/s to raise the orbit 1 km at an altitude of 352 km.

oil flow is a highly convective flow compared to water flow at normal temperature and pressure.

the clapeyron equation (also called the clausius-clapeyron equation) relates the slope of a reaction line on a phase diagram to fundamental thermodynamic properties.

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i dont know the answer but good luck

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