aerosandbox.library.propulsion_small_solid_rocket
=================================================

.. py:module:: aerosandbox.library.propulsion_small_solid_rocket


Attributes
----------

.. autoapisummary::

   aerosandbox.library.propulsion_small_solid_rocket.n
   aerosandbox.library.propulsion_small_solid_rocket.lamb
   aerosandbox.library.propulsion_small_solid_rocket.a_0
   aerosandbox.library.propulsion_small_solid_rocket.strand_reduction_factor
   aerosandbox.library.propulsion_small_solid_rocket.zeta_c_star
   aerosandbox.library.propulsion_small_solid_rocket.chamber_pressure_max
   aerosandbox.library.propulsion_small_solid_rocket.W_OM_VALID_RANGE
   aerosandbox.library.propulsion_small_solid_rocket.OUT_OF_RANGE_ERROR_STRING
   aerosandbox.library.propulsion_small_solid_rocket.oxamides


Functions
---------

.. autoapisummary::

   aerosandbox.library.propulsion_small_solid_rocket.burn_rate_coefficient
   aerosandbox.library.propulsion_small_solid_rocket.c_star
   aerosandbox.library.propulsion_small_solid_rocket.dubious_min_combustion_pressure
   aerosandbox.library.propulsion_small_solid_rocket.gamma
   aerosandbox.library.propulsion_small_solid_rocket.expansion_ratio_from_pressure
   aerosandbox.library.propulsion_small_solid_rocket.thrust_coefficient


Module Contents
---------------

.. py:data:: n
   :value: 0.402


.. py:data:: lamb
   :value: 6.2


.. py:data:: a_0

.. py:data:: strand_reduction_factor
   :value: 0.8695652173913044


.. py:data:: zeta_c_star
   :value: 0.9


.. py:data:: chamber_pressure_max
   :value: 2000000.0


.. py:data:: W_OM_VALID_RANGE
   :value: (0, 0.22)


.. py:data:: OUT_OF_RANGE_ERROR_STRING
   :value: '{:.3f} is outside the model valid range of {:.3f} <= w_om <= {:.3f}'


.. py:function:: burn_rate_coefficient(oxamide_fraction)

   Burn rate vs oxamide content model.
   Valid from 0% to 15% oxamide. # TODO IMPLEMENT THIS

   :returns:

             propellant burn rate coefficient
                 [units: pascal**(-n) meter second**-1].
   :rtype: a


.. py:function:: c_star(oxamide_fraction)

   Characteristic velocity vs. oxamide content model.
   Valid from 0% to 20% oxamide. # TODO IMPLEMENT THIS

   :returns: ideal characteristic velocity [units: meter second**-1].
   :rtype: c_star


.. py:function:: dubious_min_combustion_pressure(oxamide_fraction)

   Minimum pressure for stable combustion vs. oxamide content model.

   Note: this model is of DUBIOUS accuracy. Don't trust it.


.. py:function:: gamma(oxamide_fraction)

   Ratio of specific heats vs. oxamide content model.

   :returns: Exhaust gas ratio of specific heats [units: dimensionless].
   :rtype: gamma


.. py:function:: expansion_ratio_from_pressure(chamber_pressure, exit_pressure, gamma, oxamide_fraction)

   Find the nozzle expansion ratio from the chamber and exit pressures.

   See :ref:`expansion-ratio-tutorial-label` for a physical description of the
   expansion ratio.

   Reference: Rocket Propulsion Elements, 8th Edition, Equation 3-25

   :param chamber_pressure: Nozzle stagnation chamber pressure [units: pascal].
   :type chamber_pressure: scalar
   :param exit_pressure: Nozzle exit static pressure [units: pascal].
   :type exit_pressure: scalar
   :param gamma: Exhaust gas ratio of specific heats [units: dimensionless].
   :type gamma: scalar

   :returns: Expansion ratio :math:`\epsilon = A_e / A_t` [units: dimensionless]
   :rtype: scalar


.. py:function:: thrust_coefficient(chamber_pressure, exit_pressure, gamma, p_a=None, er=None)

   Nozzle thrust coefficient, :math:`C_F`.

   The thrust coefficient is a figure of merit for the nozzle expansion process.
   See :ref:`thrust-coefficient-label` for a description of the physical meaning of the
   thrust coefficient.

   Reference: Equation 1-33a in Huzel and Huang.

   :param chamber_pressure: Nozzle stagnation chamber pressure [units: pascal].
   :type chamber_pressure: scalar
   :param exit_pressure: Nozzle exit static pressure [units: pascal].
   :type exit_pressure: scalar
   :param gamma: Exhaust gas ratio of specific heats [units: dimensionless].
   :type gamma: scalar
   :param p_a: Ambient pressure [units: pascal]. If None,
               then p_a = exit_pressure.
   :type p_a: scalar, optional
   :param er: Nozzle area expansion ratio [units: dimensionless]. If None,
              then p_a = exit_pressure.
   :type er: scalar, optional

   :returns: The thrust coefficient, :math:`C_F` [units: dimensionless].
   :rtype: scalar


.. py:data:: oxamides