Gravity/burn loss in finite-burn maneuver

Using GMAT for specific types of missions.

Gravity/burn loss in finite-burn maneuver

Postby rossella » Thu Jun 29, 2017 5:26 pm

I am working on a project in which I need to make a plot of the velocity loss (coming from using finite-burn instead of impulsive burn) in function of thrust over weight ratio, keeping the same orbit.
The problem is, I do not know how to define uniquely an orbit in GMAT.
In the mission sequence I put the command "propagate" with stopping conditions "Apoapsis", and then "achieve" to RMAG= 12000 km, and then "achieve" again to ECC=0.25, in order to uniquely define the orbit with apoapsis and eccentricity; BUT changing the T/W, I could see from the Command summary the SMA changes, which means I am in another orbit.
I read the manual but I could not find any section in which it was explained.
Can someone help me? :?
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