You signed in with another tab or window. Reload to refresh your session.You signed out in another tab or window. Reload to refresh your session.You switched accounts on another tab or window. Reload to refresh your session.Dismiss alert
Right now, they're just Vectors of Orbit structures. This could be so much better for many reasons, including lots of memory allocation necessary to get a high degree of precision for trajectory calculations, and more.
Ideas for Improvement
Allow for returning ODESolution structures from propagate with a odesolution=Val{true} switch, and manually add methods for applying astrodynamics calculations
I don't like that solution. Is there another?
OrbitalTrajectories.jl
While watching Julia-related talks online, I found the OrbitalTrajectories.jl talk. Turns out OrbitalTrajectories also uses DifferentialEquations for propagating orbits (no surprises there). What is interesting is that the ODESolution object is returned directly from the propagation. That allows for interpolating by epoch, and access to DifferentialEquationshelper methods.
Conclusion
The Trajectory design by OrbitalTrajectories is far more robust. This should be the default, and a simple Vector of Orbit structures should be available via vec=Val{true}
The text was updated successfully, but these errors were encountered:
Trajectories could be better!
Right now, they're just
Vector
s ofOrbit
structures. This could be so much better for many reasons, including lots of memory allocation necessary to get a high degree of precision for trajectory calculations, and more.Ideas for Improvement
ODESolution
structures frompropagate
with aodesolution=Val{true}
switch, and manually add methods for applying astrodynamics calculationsI don't like that solution. Is there another?
OrbitalTrajectories.jl
While watching Julia-related talks online, I found the OrbitalTrajectories.jl talk. Turns out
OrbitalTrajectories
also usesDifferentialEquations
for propagating orbits (no surprises there). What is interesting is that theODESolution
object is returned directly from the propagation. That allows for interpolating by epoch, and access toDifferentialEquations
helper methods.Conclusion
Trajectory
design byOrbitalTrajectories
is far more robust. This should be the default, and a simpleVector
ofOrbit
structures should be available viavec=Val{true}
The text was updated successfully, but these errors were encountered: