https://github.com/nunorc/yspacepy

Y-Space companion Python package
https://github.com/nunorc/yspacepy

astronomy python

Last synced: about 1 month ago
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Y-Space companion Python package

• Host: GitHub
• URL: https://github.com/nunorc/yspacepy
• Owner: nunorc
• License: mit
• Created: 2018-09-30T12:26:04.000Z (over 6 years ago)
• Default Branch: master
• Last Pushed: 2021-03-24T16:51:00.000Z (about 4 years ago)
• Last Synced: 2025-04-09T21:54:43.343Z (about 1 month ago)
• Topics: astronomy, python
• Language: Python
• Homepage: http://y-space.pw/
• Size: 2.72 MB
• Stars: 0
• Watchers: 1
• Forks: 0
• Open Issues: 0
• Metadata Files:
  • Readme: README.rst
  • License: LICENSE.txt

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README

        

yspacepy

========

Installation

------------

.. code-block:: bash

    $ pip install yspacepy

Astronomical Bodies

-------------------

.. code-block:: python

    >>> from yspacepy.bodies import earth

    >>> earth

    Body(name='Earth', mass=5.972e+24 kg, radius=6371000.0 m, mu=398589196000000.0 m3 / s2)

    >>> earth.radius

    

    >>> earth.radius.to('km')

    

    >>> earth.radius.to('km').value

    6371.0

Orbital Mechanics

-----------------

Earth orbit around the Sun example.

.. code-block:: python

    import numpy as np

    from yspacepy.bodies import sun, earth

    from yspacepy.orbmech import OrbitPropagator, plot_orbits

    # initial conditions of orbital parameters

    r_mag = sun.radius.value + 1.496e11

    v_mag = 30000

    # initial position and velocity vectors

    state0 = np.array([r_mag, 0, 0, 0, v_mag, 0])

    # timespan

    tspan = 3.5e7

    # time step

    dt = 86400.0

    # propagate orbit

    sun_earth = OrbitPropagator(state0, tspan, dt, sun, coes=False)

    # plot orbit

    plot_orbits([sun_earth], labels=['Earth'], cb=sun)# plot orbit

ISS low earth orbit around the Earth example.

.. code-block:: python

    import numpy as np

    from yspacepy.bodies import sun, earth

    from yspacepy.orbmech import OrbitPropagator, plot_orbits

    # initial conditions of orbital parameters

    r_mag = earth.radius.value + 4e5

    v_mag = np.sqrt(earth.mu.value/r_mag)

    # initial position and velocity vectors

    state0 = np.array([r_mag, 0, 0, 0, v_mag, 0])

    # timespan

    tspan = 100 * 60.0

    # time step

    dt = 100.0

    earth_iis = OrbitPropagator(state0, tspan, dt, earth, coes=False)

    # plot orbit

    plot_orbits([earth_iis], labels=['IIS'], cb=earth)

Acknowledgements

----------------

Thank you Alfonso Gonzalez for

`Orbital Mechanics with Python `_

that are the base for the orbital mechanics modules.