Designing a MATLAB Lunar Lander: Finding v

AI Thread Summary
The discussion revolves around designing a MATLAB program for a lunar lander simulation, focusing on calculating thrust based on fuel burn rate. The user seeks to determine the exhaust velocity (v) for the lunar lander, given the maximum and minimum thrust values of 44.4 kN and 4.7 kN, respectively, and a fuel mass of 8165 kg. Specific impulse is noted as 311 seconds, leading to an estimated exhaust speed of approximately 3050 m/s. However, the user struggles to find reliable sources that directly cite these values. The conversation emphasizes the need for accurate data to complete the programming task effectively.
negatifzeo
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Homework Statement


The task is to design a MATLAB program reminiscent of the text-based lunar lander games. Ol, that's not that bad. My problem comes from the research, specifically determining what thrust will be provided from what rate of fuel burned. I know that thrust=(dm/dt)v where v is the relative velocity of the exhaust. I know the max thrust the lunar lander was capable of was 44.4 kN and the min was 4.7 kN. I know the lander had 8165 kg of N204/Aerozine-50 as fuel. Does anyone have any idea what v is or how I can find it?
 
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Several sources specifies the specific impulse to 311 sec which gives an exhaust speed of around 3050 m/s.
 
Thank you so much. Do you think you could post a link to one of these sources? Normally I'm capable when using the google; I don't know why this information has been so difficult for me to find.
 
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