Deprecate TaylorInterpolant in favour of TaylorSolution

src/PlanetaryEphemeris.jl

@@ -2,13 +2,16 @@ module PlanetaryEphemeris
 
 # __precompile__(false)
 
-export PE, au, yr, sundofs, earthdofs, c_au_per_day, μ, NBP_pN_A_J23E_J23M_J2S_threads!, DE430!,
-       semimajoraxis, eccentricity, inclination, longascnode, argperi, longperi, trueanomaly, ecanomaly, meananomaly,
-       timeperipass, lrlvec, eccentricanomaly, meanan2truean, meanmotion, time2truean, su, ea, mo, au, yr, daysec, clightkms,
-       c_au_per_day, c_au_per_sec, c_cm_per_sec, J2000, R_sun, α_p_sun, δ_p_sun, au, UJ_interaction, de430_343ast_ids, Rx, Ry,
-       Rz, ITM_und, ITM1, ITM2, R_moon, τ_M, k_2M, JSEM, CM, SM, n1SEM, n2M, J2E, J2EDOT, RE, k_20E, k_21E, k_22E, τ_0p, τ_1p,
-       τ_2p, τ_0, τ_1, τ_2, ω_E, EMRAT, TaylorInterpolant, ssb_posvel_pN, nbodyind, propagate, t2c_jpl_de430,
-       c2t_jpl_de430, pole_rotation, selecteph2jld2, save2jld2andcheck, numberofbodies, selecteph, kmsec2auday, auday2kmsec
+export PE, au, yr, sundofs, earthdofs, c_au_per_day, μ, NBP_pN_A_J23E_J23M_J2S_threads!,
+    DE430!, semimajoraxis, eccentricity, inclination, longascnode, argperi, longperi,
+    trueanomaly, ecanomaly, meananomaly, timeperipass, lrlvec, eccentricanomaly,
+    meanan2truean, meanmotion, time2truean, su, ea, mo, au, yr, daysec, clightkms,
+    c_au_per_day, c_au_per_sec, c_cm_per_sec, J2000, R_sun, α_p_sun, δ_p_sun, au,
+    UJ_interaction, de430_343ast_ids, Rx, Ry, Rz, ITM_und, ITM1, ITM2, R_moon, τ_M,
+    k_2M, JSEM, CM, SM, n1SEM, n2M, J2E, J2EDOT, RE, k_20E, k_21E, k_22E, τ_0p, τ_1p,
+    τ_2p, τ_0, τ_1, τ_2, ω_E, EMRAT, ssb_posvel_pN, nbodyind, propagate, t2c_jpl_de430,
+    c2t_jpl_de430, pole_rotation, selecteph2jld2, save2jld2andcheck, numberofbodies,
+    selecteph, kmsec2auday, auday2kmsec
 
 using AutoHashEquals
 using TaylorIntegration, LinearAlgebra
@@ -23,12 +26,27 @@ import Base: convert, reverse, show, join, zero, iszero
 import Dates: julian2datetime
 import JLD2: writeas
 
+@doc raw"""
+    kmsec2auday(pv)
+    auday2kmsec(pv)
+Convert a `[x, y, z, v_x, v_y, v_z]` state vector between [km, sec] and [au, day].
+""" kmsec2auday, auday2kmsec
+
+function kmsec2auday(pv)
+    pv /= au          # (km, km/sec) -> (au, au/sec)
+    pv[4:6] *= daysec # (au, au/sec) -> (au, au/day)
+    return pv
+end
+
+function auday2kmsec(pv)
+    pv *= au          # (au, au/day) -> (km, km/day)
+    pv[4:6] /= daysec # (km, km/day) -> (km, km/sec)
+    return pv
+end
+
 include("constants.jl")
 include("jpl-de-430-431-earth-orientation-model.jl")
 include("initial_conditions.jl")
-include("interpolation/TaylorInterpolant.jl")
-include("interpolation/TaylorInterpolantSerialization.jl")
-include("interpolation/TaylorInterpolantNSerialization.jl")
 include("propagation.jl")
 include("osculating.jl")
 include("barycenter.jl")