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WebMAE 113 – Fundamentals of Propulsion – WINTER 2024 HOMEWORK ASSIGNMENT # 5 (Due at 11:59PM on February 20, 2024) Problem 1: Consider a two-stage rocket designed for a 1,000-kg payload. The two stages, which are identical, have I sp = 400 s, m ST 1 = m ST 2 = 1 , 000 kg, and m PR 1 = m PR 2 = 5 , 000 kg. Web3 Apr 2024 · The Case for Additive Manufacturing in Propulsion 3 • Metal Additive Manufacturing (AM) can provide significant advantages for lead time and cost over traditional manufacturing for rocket engines. • Lead times reduced by 2-10x • Cost reduced by more than 50% • Complexity is inherent in liquid rocket engines and AM provides new … WebAA284a Advanced Rocket Propulsion Stanford University Thermal Efficiency: Note that for larger nozzle expansion ratios for which the temperature ratio is large, the thermal … hamilton elementary school in stockton