How Is Delta V Loss Calculated for Spacecraft?

AI Thread Summary
Delta V loss for spacecraft is primarily calculated by considering the effects of gravity and atmospheric drag during ascent. The additional delta V required to achieve low Earth orbit, estimated between 1.5 km/s to 2 km/s, is derived from empirical data and simulations that account for drag coefficients and atmospheric density profiles. Calculations typically involve integrating the forces acting on the spacecraft over its trajectory. Understanding these factors is crucial for mission planning and optimizing fuel efficiency. Further insights into the specific calculations can enhance comprehension of delta V requirements in various atmospheric conditions.
Bluelogic32
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How do you calculate how much delta v is lost from gravity and atmospheric drag?
I've been looking for days but I can't find anything that actually tells me how it's calculated.
For example it takes 1.5 km/s - 2 km/s extra delta v for a low Earth orbit because of drag loss, how was that number calculated?
 
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Thanks for the post! Sorry you aren't generating responses at the moment. Do you have any further information, come to any new conclusions or is it possible to reword the post?
 

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