<p>There's a mountain of readily available information, of which the following is one example.  From   <a href="http://spaceflight101.com/goes-r/goes-r-spacecraft/" rel="nofollow noreferrer">GOES page</a></p>
<h2>edit</h2>
<p>There is more information there about the thrust produced, so I suspect you can calculate the total delta-kinetic energy available.</p>
<blockquote>
<p>A2100 has been used for over 40 missions and is available in different versions catered to specific mission needs in terms of
dimensions and power availability with satellite mass varying between
2,000 and 6,740 Kilograms.</p>
<p>Each GOES-R-class satellite is 6.1 by 5.6 by 3.9 meters in size and has a dry mass of 2,857 Kilograms. At liftoff, the satellite
weighs 5,192 Kilograms, loaded with propellants to support a mission
of at least 14 years.<br />
GOES-R, S, T, U launches with a propellant and pressurant load of
2,335 Kilograms with Mixed Oxides of Nitrogen and Hydrazine acting as
main propellant components and Helium gas used for the pressurization
of tanks.</p>
</blockquote>

CC BY-SA 4.0
2019-07-06T14:43:35.447Z
2019-07-06T14:43:35.447Z
2020-06-17T09:47:40.653Z
Carl Witthoft
<p>I'm wondering - how much delta-v do typical geostationary satellites carry with them once they get into the orbit for things like orbital adjustment or movement to the graveyard orbit?</p>

CC BY-SA 4.0
2019-07-06T12:45:34.640Z
Probably more of a Space Exploration question.
Barry Jenakuns
CC BY-SA 4.0
2019-07-06T14:37:16.003Z
"Delta-V" is shorthand for an expenditure of energy.   The energy required to change the satellite's kinetic energy ( $\frac{mv^2}{2}$ )  depends on the satellite's mass as well as the total stored energy in the propellant.
Carl Witthoft
CC BY-SA 4.0
2019-07-07T03:10:42.630Z
@CarlWitthoft no, delta-v really is meant to express the available amount of velocity change that a spacecraft is capable of, or a maneuver requires. It is a measure of *specific energy* which is energy divided by mass. It's a bit hand-waving because the mass changes as propellant is depleted, but it's a real thing in spaceflight.
uhoh
CC BY-SA 4.0
2019-07-07T03:12:11.807Z
@JanDoggen "because it belongs on" is never a close reason. If it's off-topic here then state that it's off-topic here. I agree that a good place is Space SE, but new users reading your comment can get the idea that if they think a question is better asked somewhere else, or they think it "belongs" somewhere else, then that in and of itself is a close reason, which it isn't.
uhoh
CC BY-SA 4.0
2019-07-07T04:32:35.173Z
I'm voting to close this question as off-topic because it is not about Astronomy as defined in the help center; see [What topics can I ask about here?](https://astronomy.stackexchange.com/help/on-topic). However, it is a good candidate for asking in [Space Exploration SE](https://space.stackexchange.com/). You can consider just deleting here and posting there instead, or wait for it to be closed and see if it gets migrated.
uhoh
<artificial-satellite>
How much delta-v does a typical geostationary satellite carry?
ThePiachu
# How much delta-v does a typical geostationary satellite carry?

(Asked by: username_0 on 2019-07-06)

I'm wondering - how much delta-v do typical geostationary satellites carry with them once they get into the orbit for things like orbital adjustment or movement to the graveyard orbit?

**Tags:** artificial-satellite
> **Comments:**
> **username_1**: Probably more of a Space Exploration question.  
> **username_2**: "Delta-V" is shorthand for an expenditure of energy.   The energy required to change the satellite's kinetic energy ( $\frac{mv^2}{2}$ )  depends on the satellite's mass as well as the total stored energy in the propellant.  
> **username_3**: @CarlWitthoft no, delta-v really is meant to express the available amount of velocity change that a spacecraft is capable of, or a maneuver requires. It is a measure of *specific energy* which is energy divided by mass. It's a bit hand-waving because the mass changes as propellant is depleted, but it's a real thing in spaceflight.  
> **username_3**: @JanDoggen "because it belongs on" is never a close reason. If it's off-topic here then state that it's off-topic here. I agree that a good place is Space SE, but new users reading your comment can get the idea that if they think a question is better asked somewhere else, or they think it "belongs" somewhere else, then that in and of itself is a close reason, which it isn't.  
> **username_3**: I'm voting to close this question as off-topic because it is not about Astronomy as defined in the help center; see [What topics can I ask about here?](https://astronomy.stackexchange.com/help/on-topic). However, it is a good candidate for asking in [Space Exploration SE](https://space.stackexchange.com/). You can consider just deleting here and posting there instead, or wait for it to be closed and see if it gets migrated.  

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## 1 answers

### Answer by username_2 on 2019-07-06. Score: 0

There's a mountain of readily available information, of which the following is one example. From [GOES page](http://spaceflight101.com/goes-r/goes-r-spacecraft/)

## edit

There is more information there about the thrust produced, so I suspect you can calculate the total delta-kinetic energy available.

> A2100 has been used for over 40 missions and is available in different versions catered to specific mission needs in terms of
> dimensions and power availability with satellite mass varying between
> 2,000 and 6,740 Kilograms.
>
> Each GOES-R-class satellite is 6.1 by 5.6 by 3.9 meters in size and has a dry mass of 2,857 Kilograms. At liftoff, the satellite
> weighs 5,192 Kilograms, loaded with propellants to support a mission
> of at least 14 years.  
> GOES-R, S, T, U launches with a propellant and pressurant load of
> 2,335 Kilograms with Mixed Oxides of Nitrogen and Hydrazine acting as
> main propellant components and Helium gas used for the pressurization
> of tanks.


---

