Solve the averaged low-thrust optimal control transfer problem
Project description
README
Preambule
The application solves the averaged optimal minimum time orbit transfer problem. It is initially inspired by [MIPELEC] that uses the averaged optimal control formulation. This application however includes important upgrade, such as:
- different terminal conditions
- inclusion of zonal gravitational field perturbation to model secular evolution of node and apoapsis lines, around an oblate body.
IMPORTANT WARNINGS
- The optimal control is the solution of the averaged optimal control problem.
- It cannot be used as such for high fidelity propagation,
- It cannot currently be used for rendezvous problems (e.g. interplanetary)
- The solution starts diverging from the non-averaged optimal control problem solution for very large thrust accelerations.
Running under python
Installation from repository
pip install realoot
The module works with Python 3.
Installation from sources
Please follow the instructions in COMPILE.
Example Usage
Import
import realoot.main as lt
Then either, as for the application, open a script file with
problemDefinition, problemContext = lt.readXml("examples/ex2.xml")
lt.solve(problemDefinition, problemContext, problemSolution, True)
Or define manually your problem filling the structure
problemContext = lt.LtProblemContext()
problemDefinition = lt.LtProblemDefinition()
Then call
lt.solve(problemDefinition, problemContext, problemSolution, True)
Please see the examples for details.
You will need matplotlib
to run the examples.
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