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updated 10 months ago

Kepler State Transition Matrix (MEX) by Rody Oldenhuis

Rody Oldenhuis (view profile)

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

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updated 1 year ago

Convert Keplerian Orbital Elements to a State Vector by Darin Koblick

Darin Koblick (view profile)

Convert orbital elements to a state vector, or a state vector back to orbital elements. (keplerian, orbital elements, aerospace)

orb2rv(p,e,i,O,o,nu,truLon,argLat,lonPer,mu)

rv2orb(r,v,mu)

test_orb2rv.m

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updated 3 years ago

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

Darin Koblick (view profile)

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 5 years ago

Orbital Mechanics Library by Richard Rieber

Richard Rieber (view profile)

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 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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