Solvers

All names on this page are provided by version 1.0.0 of AstrodynamicalSolvers. For more information, consult the documentation for AstrodynamicalSolvers directly.

AstrodynamicalSolvers

Provides astrodynamical solvers, including Lyapunov and halo orbit correctors.

Extended help

License

Exports

• CR3BSolvers
• Propagation
• convergent_manifold
• divergent_manifold
• halo
• lyapunov
• monodromy
• propagate
• propagate!

Imports

• AstrodynamicalSolvers.CR3BSolvers
• AstrodynamicalSolvers.Propagation
• Base
• DocStringExtensions
• Reexport

CR3BSolvers

Solvers specific to the Circular Restricted Three Body Problem.

Extended Help

Exports

• halo
• lyapunov

Imports

• AstrodynamicalCalculations
• AstrodynamicalModels
• Base
• DocStringExtensions
• LinearAlgebra
• ModelingToolkit
• OrdinaryDiffEqVerner
• StaticArrays

Propagation

Wrappers around SciML differential equation solvers for fast and convenient orbit propagation.

Extended Help

Exports

• convergent_manifold
• divergent_manifold
• monodromy
• propagate
• propagate!

Imports

• AstrodynamicalCalculations
• AstrodynamicalModels
• Base
• DocStringExtensions
• ModelingToolkit
• OrdinaryDiffEqVerner
• SciMLBase
• StaticArrays

convergent_manifold

convergent_manifold(u, μ, Δt; eps, trajectories, kwargs...)

Return a vector of orbits along the manifold which converges to the provided halo orbit.

divergent_manifold

divergent_manifold(u, μ, Δt; eps, trajectories, kwargs...)

Return a vector of orbits along the manifold which diverges from the provided halo orbit.

halo

halo(x, z, ẏ, μ, T; reltol, abstol, maxiters)

WarningCR3BP Dynamics

This computation is valid for Circular Restricted Three Body Problem dynamics.

Iterate on an initial guess for halo orbit conditions.

halo(μ, lagrange; amplitude, phase, hemisphere, kwargs...)

WarningCR3BP Dynamics

This computation is valid for Circular Restricted Three Body Problem dynamics.

Given a nondimensional mass parameter μ, and orbit characteristics, construct an initial guess using Richardson’s analytical solution, and iterate on that guess using a differential corrector.

lyapunov

lyapunov(x, ẏ, μ, T; reltol, abstol, maxiters)

WarningCR3BP Dynamics

This computation is valid for Circular Restricted Three Body Problem dynamics.

Iterate on an initial guess for Lyapunov orbit conditions.

monodromy

monodromy(orbit, Δt; algorithm, reltol, abstol, kwargs...)

Compute the monodromy matrix for any periodic orbit.

monodromy(
    u,
    μ,
    T,
    f;
    algorithm,
    reltol,
    abstol,
    save_everystep,
    kwargs...
)

Solve for the monodromy matrix of the periodic orbit.

propagate

propagate(
    orbit,
    Δt;
    stm,
    algorithm,
    reltol,
    abstol,
    kwargs...
)

Numerically integrate the orbit forward (or backward) in time, and return a new AstrodynamicalOrbit instance with identical parameters to the provided orbit.

propagate!

propagate!(
    orbit,
    Δt;
    stm,
    algorithm,
    reltol,
    abstol,
    kwargs...
)

Numerically integrate the orbit forward (or backward) in time, modifying the state vector in-place within the AstrodynamicalOrbit instance.