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updated 3 months ago

Kepler State Transition Matrix (MEX) by Rody Oldenhuis

Compute Kepler state transition matrix for an arbitrary number of time steps. M and C++ version. (aeronautics, aerospace, kepler)

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updated 2 years ago

Vectorized Picard-Chebyshev Method by Darin Koblick

Vectorized Picard-Chebyshev Method used for the analysis of the 2012 ASME Conference paper 87878 (orbit propagation, kepler, picard chebyshev)

PicardChebyshevDemo()

VMPCM(ode,tau,x_guess,omega1,omega2,errTol,varargin)

keplerUniversal(r0,v0,t,mu)

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updated 2 years ago

Gauss-Jackson Eighth-Order ODE Solver (Fixed Step Size) by Darin Koblick

Gauss-Jackson Eight-Order MultiStep Predictor-Corrector using ODE113 in its startup procedure. (gauss jackson, ode, propagator)

GJ8(FirstOrderODE,SecondOrderODE,tspan,h,y0,dy0,ddy0,opti...

GJ8_Demo()

keplerUniversal(r0,v0,t,mu)

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updated 2 years ago

Vectorized Analytic Two Body Propagator (Kepler Universal Variables) by Darin Koblick

Analytic propagation routine uses universal variables to solve a single formula for all orbit types (kepler, keplerian, universal variable)

KeplerUniversalVsSTK()

keplerUniversal(r0,v0,t,mu)

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updated 3 years ago

Bulirsch-Stoer Propagator/Integrator by Darin Koblick

Implementation of the Bulirsch-Stoer algorithm for purposes of numerical orbit propagation. (bulirschstoer, propagation, ode)

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updated 4 years ago

Interplanetary Mission Planner & Verifier by Stephen Walker

Modeling and verification of interplanetary missions using Kepler & Newton. (newton, kepler, voyager)

pol2cartd(th,r,z)

predictor(craft_v,angle1, source_planet,target_planet )

transition(vel_in, theta_in_d, planet, miss )

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updated almost 5 years ago

Orbital Mechanics Library by Richard Rieber

A compilation of all of the functions I wrote for my orbital mechanics class (aerospace, aeronautics, aerodef)

CalcEA(M,ecc,tol)

Groundtrack(Kepler,GMSTo,Tf,fig,dT,s,mu)

Hohmann(R_init,R_fin,U)

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updated almost 6 years ago

Keplerian State Transition Matrix by Dmitry Savransky

Given initial positions and velocities, calculate the keplerian state transition matrix for an orbit (aerospace, aeronautics, aerodef)

keplerSTM(x0,dt,mu)

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updated almost 8 years ago

Solve Kepler's Equation for E by John Shelton

Calculates Eccentric Anomaly given Mean Anomaly (aerospace, aeronautics, aerodef)

solve_Kepler_for_E(Me, e, tol)

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