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So basically I was trying to design a low thrust maneuver to increase the apogee of the spacecraft.

I solved it separately and got some thrust profile (thrust and it's direction as a function of time). Now I want to verify my calculations, that applying that particular thrust leads to the same final orbit as I had predicted.

Can I use GMAT for this purpose?
If yes, then how?

Are there any resources available online?

Ola Ström
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Aryan
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    Although it's for a different purpose, the procedure discussed in this answer might be made to work here, though approximating low continuous thrust as a lot of small impulses is not ideal. There may be better solutions. How do you parameterize your thrust? A lookup table of vectors? An analytical function of time? A constant vector? – uhoh Nov 17 '21 at 23:42
  • Oh, also see this answer: "R2015a: GMAT now supports modelling of electric propulsion systems." – uhoh Nov 17 '21 at 23:44
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    @uhoh thanks for linking to my answer. I also believe that's the best way to solve Aryan's problem. In fact, I've solved a similar problem (low thrust orbit raising for a constellation) before using the Python interface. – ChrisR Nov 18 '21 at 05:36

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