How Is Delta V Loss Calculated for Spacecraft?

[Bluelogic32]

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?

 

[Greg Bernhardt]

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?

 

[NatSusan]

There are several factors that go into calculating the delta v lost from gravity and atmospheric drag. First, we need to understand what delta v is. Delta v, or change in velocity, is the difference between the initial velocity and the final velocity of an object. In the context of space travel, it is the amount of speed needed to change an object's trajectory or orbit.

To calculate the delta v lost from gravity and atmospheric drag, we need to consider the following factors:

1. Mass and velocity of the spacecraft: The mass and velocity of the spacecraft play a significant role in determining the amount of delta v lost. A heavier spacecraft will experience more drag and require more delta v to maintain its velocity, while a lighter spacecraft will experience less drag and require less delta v.

2. Atmospheric density: The density of the atmosphere at a particular altitude will affect the amount of drag experienced by the spacecraft. The denser the atmosphere, the more drag it will exert on the spacecraft, resulting in a higher delta v loss.

3. Angle of attack: The angle at which the spacecraft enters the atmosphere also plays a role in determining the amount of delta v lost. A steeper angle of attack will result in more drag, while a shallower angle will result in less drag.

4. Drag coefficient: The shape and design of the spacecraft will also affect the amount of drag it experiences. A more streamlined and aerodynamic spacecraft will have a lower drag coefficient, resulting in less delta v loss.

To calculate the exact amount of delta v lost, complex mathematical equations are used, taking into account all the above factors. These calculations are typically done using computer simulations and can vary depending on the specific spacecraft and its trajectory.

The number you mentioned, 1.5 km/s - 2 km/s, is a general estimate and may vary depending on the specific spacecraft and its mission. It is calculated based on historical data and simulations, taking into account the factors mentioned above.

I hope this helps to answer your question. Keep in mind that calculating the exact amount of delta v lost from gravity and atmospheric drag can be a complex and dynamic process, and the numbers may vary depending on the specific circumstances.