How Is Delta V Loss Calculated for Spacecraft?

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SUMMARY

Delta V loss for spacecraft is primarily calculated by considering gravitational forces and atmospheric drag during ascent. For low Earth orbit (LEO), an additional delta V of 1.5 km/s to 2 km/s is required to overcome drag, a figure derived from empirical data and simulations. These calculations involve complex modeling of atmospheric density, spacecraft velocity, and trajectory. Understanding these factors is crucial for accurate mission planning and fuel efficiency.

PREREQUISITES
  • Understanding of orbital mechanics
  • Familiarity with atmospheric drag equations
  • Knowledge of delta V and its significance in space missions
  • Experience with spacecraft trajectory simulations
NEXT STEPS
  • Research the equations governing atmospheric drag on spacecraft
  • Study delta V budgeting for various space missions
  • Explore simulation tools like STK (Systems Tool Kit) for trajectory analysis
  • Learn about the effects of gravity losses during launch phases
USEFUL FOR

Aerospace engineers, mission planners, and students in astrodynamics seeking to understand delta V calculations and their implications for spacecraft design and mission success.

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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