Orbital Escape Trajectories | Orbital Mechanics with Python 24

In this video I go over three kinds of escape trajectories. Impulsive, low thrust, and multiple impulsive orbit raising. I show an example where an escape trajectory from apogee and another from perigee compare, as well as mention the importance of knowing where the moon is. I then show an example of a low thrust spiral trajectory, along with its keplerian orbital elements.

Pre-req videos:

Optional videos:

Link to NASA website on SpaceIL's Beresheet lunar spacecraft:

Link to Wikipedia page covering several types of norms:

[colinthomas]

Hi Alfonso..
Have got the first part working, but have a minor issue with the low thrust second part.

In the orbit propagator, I am getting:
AttributeError: 'OrbitPropagator' object has no attribute 'default_thrust_func'

This comes from the statement in OP:

#check for custom thrust function
if

else:
if self.perts['thrust']:


but, I have checked back, and can't find what the default_thrust_func was defined as :-(
The statement seems to have been added in video 18
Could you drop this function in a reply ?
In the meanwhile I'll head to the Lamberts problem 25/26

best regards

Colin

[mariuszmilewski]

My velocities at apogee are different
and
OP sending that:
self.y[0, :]=self.r0.tolist()+self.v0.tolist()+self.mass0]
AttributeError: 'list' object has no attribute 'tolist'

it's not my day :)