Is your feature request related to a problem? Please describe.
Rocketpy curetly does not take into account the thrust dependece on the ambient pressure: $(p_e-p_a)A_e$.
It's a important behaviour considering two situations: correction for thrust curves obtained from a static hot fire test performed in a altitude much different from the launch or in-flight corrections for high target altitude flights.
Describe the solution you'd like
Implement a optional method for take that behaviour into acount without crashing the current library behaviour.
Additional context
To do list
Is your feature request related to a problem? Please describe.
Rocketpy curetly does not take into account the thrust dependece on the ambient pressure:$(p_e-p_a)A_e$ .
It's a important behaviour considering two situations: correction for thrust curves obtained from a static hot fire test performed in a altitude much different from the launch or in-flight corrections for high target altitude flights.
Describe the solution you'd like
Implement a optional method for take that behaviour into acount without crashing the current library behaviour.
Additional context
To do list