GeneralAstrodynamics.jl

Common astrodynamics calculations, with units!

Warning

The functionality in this package has being split into constituent packages, including AstrodynamicalModels.jl AstrodynamicalCalculations.jl, AstrodynamicalSolvers.jl, and more. GeneralAstrodynamics.jl is currently being refactored into a super-package, which re-exports the functionality in its constituent packages. Look out for v1.0!

JuliaCon Talk

Check out GeneralAstrodynamics in action at JuliaCon 2021! The talk Going to Jupiter with Julia walks through a simple Jupiter mission design while gently introducing astrodynamics, Julia, and GeneralAstrodynamics.

Features

Restricted Two-body Problem (R2BP)

• Structures for Cartesian and Keplerian states, and R2BP systems
• Functions which implement common R2BP equations
• Kepler and Lambert solvers
• Orbit propagation and plotting

Circular Restricted Three-body Problem (CR3BP)

• Structures for dimensioned and normalized Cartesian states, and dimensioned and normalized CR3BP systems
• Functions which implement common CR3BP equations
• Analytical and iterative (numerical) Halo orbit solvers
• Unstable and stable Halo orbit manifold computation
• Orbit propagation and plotting
• Zero-velocity curve computation and plotting

N-body Problem (NBP)

• This was implemented in a previous package version, and is currently being refactored

Envisioned Usage

using GeneralAstrodynamics

orbit = rand(R2BPOrbit)
trajectory = propagate(orbit, orbital_period(orbit))

furnsh(
    de440s(),                   # position and velocity data for nearby planets
    latest_leapseconds_lsk(),   # timekeeping, parsing epochs
    gm_de440(),                 # mass parameters for major solar system bodies
    pck00011(),                 # physical properties of major solar system bodies
)

μ = reduced_mass(
  gm("earth"),
  gm("moon"),
)

orbit, T = let
  u, T = halo(μ, 2; amplitude=1e-2)

  CR3BPOrbit(CartesianState(u), CR3BParameters(μ)), T
end

trajectory = propagate(orbit, T)