.. DO NOT EDIT.
.. THIS FILE WAS AUTOMATICALLY GENERATED BY SPHINX-GALLERY.
.. TO MAKE CHANGES, EDIT THE SOURCE PYTHON FILE:
.. "auto_examples/initial_mass.py"
.. LINE NUMBERS ARE GIVEN BELOW.

.. only:: html

    .. note::
        :class: sphx-glr-download-link-note

        :ref:`Go to the end <sphx_glr_download_auto_examples_initial_mass.py>`
        to download the full example code.

.. rst-class:: sphx-glr-example-title

.. _sphx_glr_auto_examples_initial_mass.py:


Initial Mass Calculation
========================

Example calculation of aircraft initial mass

.. GENERATED FROM PYTHON SOURCE LINES 8-63




.. rst-class:: sphx-glr-script-out

 .. code-block:: none

    cruiseFuelFlow: 0.698252094246702 [kg/s]
    breguetLeducInitialMass: 52118.39521362933 [kg]
    initMass: 52118.39521362933 [kg]






|

.. code-block:: Python


    from pyBADA.bada3 import Bada3Aircraft
    from pyBADA import trajectoryPrediction as TP
    from pyBADA import atmosphere as atm
    from pyBADA import conversions as conv


    # calculate estimations for the fuel flow, and aircraft initial mass
    AC = Bada3Aircraft(badaVersion="DUMMY", acName="J2M")

    deltaTemp = 0  # deviation from ISA temperature [K or deg C]
    M = 0.7  # Mach number [-]
    altitude = conv.ft2m(30000)  # cruise altitude[m]
    distance = conv.nm2m(100)  # flown distance [NM]
    payload = 80  # payload mass [% of the maximum payload mass]
    fuelReserve = 3600  # reserve of the fuel [s]
    flightPlanInitialMass = None  # planned initial/takeoff mass [kg]

    # fuel flow in cruise
    cruiseFuelFlow = TP.cruiseFuelConsumption(
        AC=AC, altitude=altitude, M=M, deltaTemp=deltaTemp
    )

    # in case of no wind, the ground speed is the same as true airspeed
    [theta, delta, sigma] = atm.atmosphereProperties(
        h=altitude, DeltaTemp=deltaTemp
    )
    TAS = atm.mach2Tas(Mach=M, theta=theta)
    GS = TAS

    # distance based initial mass
    breguetLeducInitialMass = TP.breguetLeducInitialMass(
        AC=AC,
        distance=distance,
        GS=GS,
        cruiseFuelFlow=cruiseFuelFlow,
        payload=payload,
        fuelReserve=fuelReserve,
    )

    # calculation of initial mass taking into account flight plan data and aircraft flight envelope
    initMass = TP.getInitialMass(
        AC=AC,
        distance=distance,
        altitude=altitude,
        M=M,
        payload=payload,
        fuelReserve=fuelReserve,
        flightPlanInitialMass=flightPlanInitialMass,
        deltaTemp=deltaTemp,
    )

    print(f"cruiseFuelFlow: {cruiseFuelFlow} [kg/s]")
    print(f"breguetLeducInitialMass: {breguetLeducInitialMass} [kg]")
    print(f"initMass: {initMass} [kg]")


.. rst-class:: sphx-glr-timing

   **Total running time of the script:** (0 minutes 0.005 seconds)


.. _sphx_glr_download_auto_examples_initial_mass.py:

.. only:: html

  .. container:: sphx-glr-footer sphx-glr-footer-example

    .. container:: sphx-glr-download sphx-glr-download-jupyter

      :download:`Download Jupyter notebook: initial_mass.ipynb <initial_mass.ipynb>`

    .. container:: sphx-glr-download sphx-glr-download-python

      :download:`Download Python source code: initial_mass.py <initial_mass.py>`

    .. container:: sphx-glr-download sphx-glr-download-zip

      :download:`Download zipped: initial_mass.zip <initial_mass.zip>`


.. only:: html

 .. rst-class:: sphx-glr-signature

    `Gallery generated by Sphinx-Gallery <https://sphinx-gallery.github.io>`_