An Adaptive Analytic Continuation Technique for the Computation of the Higher Order State Transition Tensors for the Perturbed Two-Body Problem

Tasif, Tahsinul Haque; Elgohary, Tarek A.

doi:10.2514/6.2020-0958

Cited by 3 publications

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“…The RMS errors for the 36 elements of the STM are calculated using Eq. 42 for the four orbit test cases and the results are shown in Tables 2, 3, 4 and 5, [30].…”

Section: Rms Error For the Unperturbed Stmmentioning

confidence: 99%

An Adaptive Analytic Continuation Method for Computing the Perturbed Two-Body Problem State Transition Matrix

Tasif

Elgohary

2020

J Astronaut Sci

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In this work, the Taylor series based technique, Analytic Continuation is implemented to develop a method for the computation of the gravity and drag perturbed State Transition Matrix (STM) incorporating adaptive time steps and expansion order. Analytic Continuation has been developed for the two-body problem based on two scalar variables f and gp and their higher order time derivatives using Leibniz rule. The method has been proven to be very precise and efficient in trajectory propagation. The method is expanded to include the computation of the STM for the perturbed two-body problem. Leibniz product rule is used to compute the partials for the recursive formulas and an arbitrary order Taylor series is used to compute the STM. Four types of orbits, LEO, MEO, GTO and HEO, are presented and the simulations are run for 10 orbit periods. The accuracy of the STM is evaluated via RMS error for the unperturbed cases, symplectic check for the gravity perturbed cases and error propagation for the gravity and drag perturbed orbits. The results are compared against analytical and high order numerical solvers (ODE45, ODE113 and ODE87) in terms of accuracy. The results show that the method maintains double-precision accuracy for all test cases and 1-2 orders of magnitude improvement in linear prediction results compared to ODE87. The present approach is simple, adaptive and can readily be expanded to compute the full spherical harmonics gravity perturbations as well as the higher order state transition tensors.

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“…The RMS errors for the 36 elements of the STM are calculated using Eq. 42 for the four orbit test cases and the results are shown in Tables 2, 3, 4 and 5, [30].…”

Section: Rms Error For the Unperturbed Stmmentioning

confidence: 99%