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orbital-simulation

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poliastro / poliastro

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`Maneuver.lambert` sometimes generates negative times of flight and crashes

astrojuanlu
astrojuanlu commented Nov 12, 2021

Example:

In [25]: Maneuver.lambert(gto2, geo)
---------------------------------------------------------------------------
AssertionError                            Traceback (most recent call last)
<ipython-input-25-f36ab89d597a> in <module>
----> 1 Maneuver.lambert(gto2, geo)

~/Projects/LSF/poliastro/library/src/poliastro/maneuver.py in lambert(cls, orbit_i, orbit_f, method, short,
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bug good first issue

HussainAbdi / Gravity-Simulator

N-body space simulator that uses the Runge-Kutta 4 numerical integration method to solve two first order differential equations derived from the second order differential equation that governs the motion of an orbiting celestial. Also has preset demos for two-body and three-body circular orbits which use parametric equations. Uses the SFML (Simple and Fast Multimedia Library) library: https://www.sfml-dev.org

c-plus-plus simulator simulation space orbit planet gravity numerical-methods n-body-simulator orbital-simulation celestial-bodies orbits numerical-integration runge-kutta n-body celestial rk4 gravity-simulate runge-kutta-methods
  • Updated Jun 2, 2017
  • C++

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