# COMPUTATIONAL TODO

## Completed steps
- implement 'launch function as a function' portion
- substitute the transition functions into the optimality conditions.

## Next steps
- create the iterated optimality conditions
- use these optimality conditions to create a loss function
- add boundary conditions to loss function
- get a basic gradient descent/optimization of launch function working.
- add satellite deorbit to model.
- turn this into a framework in a module, not just a single notebook (long term goal)