Welcome to pykep’s documentation!#
pykep is a coolbox developed at the European Space Agency by its Advanced Concepts Team. Its main purpose is to allow for fast prototyping of research ideas on interplanetary trajectory design. At the library core is the implementation of efficient algorithms allowing to solve the multiple revolutions Lambert’s problem, low-thrust problems, multiple asteroid randezvous problems and more. Support for JPL SPICE, SGP4 propagation and the Heyoka Taylor integration suite is provided.
pykep has been used by the European Space Agency’s Advanced Concepts Team during different Global Trajectory Optimization Competitions GTOC, several research papers as well as for the optimization of preliminary mission scenarios such as in the M-ARGO interplanetary cubesat concept, the phase 0 study for the the Titan and Enceladus Mission (TandEM) and for preliminary mission analysis of the HERA mission.
Main
- API
- Anomalies Conversions
- Global constants
- Orbital Elements
- Epoch class
- Planet class
- User defined planets (UDPLAs)
- Lambert class
- Fly-by routines
- Various approximations for orbital transfers
- Numerical Propagation
- Stark
- Circular Restricted Three Body Problem
- Low-thrust Pontryagin Cartesian TPBVP
- Interplanetary transfer legs
- Trajectory Optimization
- Trajectory Optimization Gym
- The plot module
- Utils
- Spice Utils
- Encoding Utils
- Miscellanea
- Bibliography
Tutorials
- Basic
- Trajectory Optimization
- Point to point low-thrust
- Planet to planet low-thrust
- Multiple Gravity Assist (MGA)
- Multiple Gravity Assist with one DSM (MGA-1DSM)
- Multiple impulses
- Are more impulses needed?
- Low-thrust transfers via indirect methods I (mass-fixed time)
- Low-thrust transfers via indirect methods II (time)
- Primer Vector
- Surrogate Primer Vector
- But is it true?
