Delta-V Correction needed after launch?

[alexandicity]

Hi guys,

I want to know - roughly - how much delta-V a satellite must expend to get from its launch insertion orbit to its final orbit.

Let us assume that we're putting a LEO craft up. The launcher is has the performance to reach this orbit, and is launched at the right time and inclination. In "theory", it will place the satellite in exactly the right orbit and nothing other than attitude control is needed. In practice, these launchers are crude instruments and almost all satellites will need to correct their orbits.

Similarly, we can all calculate the delta-V needed by a GTO craft to reach a GEO orbit, but do we need to add more delta-V to compensate for errors due to the launch vehicle (which would typically insert to GTO).

Any ideas how I might go about estimating these corrections? Will they be in the order of 1, 10, 100 or 1000+ ms^-1?

Thanks!

 

[AndyW]

Hi there,

Calculating the delta-V required for a satellite to reach its final orbit can be a complex task, as it depends on a number of factors such as the launch vehicle's performance, the desired final orbit, and any errors or deviations during launch. However, there are a few general guidelines that can help estimate the corrections needed for a LEO or GTO satellite.

For a LEO satellite, the delta-V required to reach its final orbit can range from 1-100 m/s, depending on the specific orbit and launch conditions. This includes both corrections for launch vehicle errors and any adjustments needed for the satellite's own propulsion system. Generally, the closer the satellite is to its desired orbit after launch, the less delta-V will be needed for corrections.

For a GTO satellite, the delta-V required to reach GEO can be significantly higher, ranging from 100-1000+ m/s. This is due to the fact that a GTO orbit is a highly elliptical orbit, and the satellite will need to circularize its orbit to reach GEO. In addition, as you mentioned, the launch vehicle's performance and any deviations during launch can also impact the required delta-V.

To estimate the corrections needed for a specific satellite, it is best to consult the manufacturer's specifications and perform a detailed analysis using orbital mechanics equations. In general, the corrections for a LEO satellite will be in the order of 1-100 m/s, while those for a GTO satellite will be in the order of 100-1000+ m/s. I hope this helps!