from __future__ import division
import numpy as np

from openmdao.api import ExplicitComponent

class TrueAirspeedComp(ExplicitComponent):
    '''
    Computes true airspeed from equivalent airspeed and density

    Inputs
    ------
    fltcond|rho : float
        Density (vector, kg/m3)
    fltcond|Ueas : float
        Equivalent airspeed (vector, m/s)

    Outputs
    -------
    fltcond|Utrue : float
        True airspeed (vector, m/s)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length) (default 1)
    '''

    def initialize(self):
        self.options.declare('num_nodes', types=int)

    def setup(self):
        num_points = self.options['num_nodes']

        self.add_input('fltcond|Ueas', units='m / s', shape=num_points)
        self.add_input('fltcond|rho', units='kg * m**-3', shape=num_points)
        self.add_output('fltcond|Utrue', units='m / s', shape=num_points)

        arange = np.arange(num_points)
        self.declare_partials('fltcond|Utrue', 'fltcond|Ueas', rows=arange, cols=arange)
        self.declare_partials('fltcond|Utrue', 'fltcond|rho', rows=arange, cols=arange)

    def compute(self, inputs, outputs):
        rho_isa_kgm3 = 1.225
        outputs['fltcond|Utrue'] = inputs['fltcond|Ueas']*np.sqrt(rho_isa_kgm3/inputs['fltcond|rho'])

    def compute_partials(self, inputs, partials):
        rho_isa_kgm3 = 1.225
        partials['fltcond|Utrue', 'fltcond|Ueas'] = np.sqrt(rho_isa_kgm3/inputs['fltcond|rho'])
        partials['fltcond|Utrue', 'fltcond|rho'] = inputs['fltcond|Ueas']*np.sqrt(rho_isa_kgm3)*(-1/2)*inputs['fltcond|rho']**(-3/2)

class EquivalentAirspeedComp(ExplicitComponent):
    '''
    Computes equivalent airspeed from true airspeed and density

    Inputs
    ------
    fltcond|rho : float
        Density (vector, kg/m3)
    fltcond|Utrue : float
        True airspeed (vector, m/s)

    Outputs
    -------
    fltcond|Ueas : float
        Equivalent airspeed (vector, m/s)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length) (default 1)
    '''

    def initialize(self):
        self.options.declare('num_nodes', types=int)

    def setup(self):
        num_points = self.options['num_nodes']

        self.add_output('fltcond|Ueas', units='m / s', shape=num_points)
        self.add_input('fltcond|rho', units='kg * m**-3', shape=num_points)
        self.add_input('fltcond|Utrue', units='m / s', shape=num_points)

        arange = np.arange(num_points)
        self.declare_partials('fltcond|Ueas', 'fltcond|Utrue', rows=arange, cols=arange)
        self.declare_partials('fltcond|Ueas', 'fltcond|rho', rows=arange, cols=arange)

    def compute(self, inputs, outputs):
        rho_isa_kgm3 = 1.225
        outputs['fltcond|Ueas'] = inputs['fltcond|Utrue']*np.sqrt(inputs['fltcond|rho'] / rho_isa_kgm3)

    def compute_partials(self, inputs, partials):
        rho_isa_kgm3 = 1.225
        partials['fltcond|Ueas', 'fltcond|Utrue'] = np.sqrt(inputs['fltcond|rho'] / rho_isa_kgm3)
        partials['fltcond|Ueas', 'fltcond|rho'] = (1/2)*inputs['fltcond|Utrue']*(inputs['fltcond|rho'] / rho_isa_kgm3)**(-1/2) / rho_isa_kgm3
from __future__ import division
import numpy as np

from openmdao.api import ExplicitComponent

class TrueAirspeedComp(ExplicitComponent):
    '''
    Computes true airspeed from equivalent airspeed and density

    Inputs
    ------
    fltcond|rho : float
        Density (vector, kg/m3)
    fltcond|Ueas : float
        Equivalent airspeed (vector, m/s)

    Outputs
    -------
    fltcond|Utrue : float
        True airspeed (vector, m/s)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length) (default 1)
    '''

    def initialize(self):
        self.options.declare('num_nodes', types=int)

    def setup(self):
        num_points = self.options['num_nodes']

        self.add_input('fltcond|Ueas', units='m / s', shape=num_points)
        self.add_input('fltcond|rho', units='kg * m**-3', shape=num_points)
        self.add_output('fltcond|Utrue', units='m / s', shape=num_points)

        arange = np.arange(num_points)
        self.declare_partials('fltcond|Utrue', 'fltcond|Ueas', rows=arange, cols=arange)
        self.declare_partials('fltcond|Utrue', 'fltcond|rho', rows=arange, cols=arange)

    def compute(self, inputs, outputs):
        rho_isa_kgm3 = 1.225
        outputs['fltcond|Utrue'] = inputs['fltcond|Ueas']*np.sqrt(rho_isa_kgm3/inputs['fltcond|rho'])

    def compute_partials(self, inputs, partials):
        rho_isa_kgm3 = 1.225
        partials['fltcond|Utrue', 'fltcond|Ueas'] = np.sqrt(rho_isa_kgm3/inputs['fltcond|rho'])
        partials['fltcond|Utrue', 'fltcond|rho'] = inputs['fltcond|Ueas']*np.sqrt(rho_isa_kgm3)*(-1/2)*inputs['fltcond|rho']**(-3/2)

class EquivalentAirspeedComp(ExplicitComponent):
    '''
    Computes equivalent airspeed from true airspeed and density

    Inputs
    ------
    fltcond|rho : float
        Density (vector, kg/m3)
    fltcond|Utrue : float
        True airspeed (vector, m/s)

    Outputs
    -------
    fltcond|Ueas : float
        Equivalent airspeed (vector, m/s)

    Options
    -------
    num_nodes : int
        Number of analysis points to run (sets vec length) (default 1)
    '''

    def initialize(self):
        self.options.declare('num_nodes', types=int)

    def setup(self):
        num_points = self.options['num_nodes']

        self.add_output('fltcond|Ueas', units='m / s', shape=num_points)
        self.add_input('fltcond|rho', units='kg * m**-3', shape=num_points)
        self.add_input('fltcond|Utrue', units='m / s', shape=num_points)

        arange = np.arange(num_points)
        self.declare_partials('fltcond|Ueas', 'fltcond|Utrue', rows=arange, cols=arange)
        self.declare_partials('fltcond|Ueas', 'fltcond|rho', rows=arange, cols=arange)

    def compute(self, inputs, outputs):
        rho_isa_kgm3 = 1.225
        outputs['fltcond|Ueas'] = inputs['fltcond|Utrue']*np.sqrt(inputs['fltcond|rho'] / rho_isa_kgm3)

    def compute_partials(self, inputs, partials):
        rho_isa_kgm3 = 1.225
        partials['fltcond|Ueas', 'fltcond|Utrue'] = np.sqrt(inputs['fltcond|rho'] / rho_isa_kgm3)
        partials['fltcond|Ueas', 'fltcond|rho'] = (1/2)*inputs['fltcond|Utrue']*(inputs['fltcond|rho'] / rho_isa_kgm3)**(-1/2) / rho_isa_kgm3
Computes true airspeed from equivalent airspeed and density      Inputs     ------     fltcond|rho : float         Density (vector, kg/m3)     fltcond|Ueas : float         Equivalent airspeed (vector, m/s)      Outputs     -------     fltcond|Utrue : float         True airspeed (vector, m/s)      Options     -------     num_nodes : int         Number of analysis points to run (sets vec length) (default 1) Computes equivalent airspeed from true airspeed and density      Inputs     ------     fltcond|rho : float         Density (vector, kg/m3)     fltcond|Utrue : float         True airspeed (vector, m/s)      Outputs     -------     fltcond|Ueas : float         Equivalent airspeed (vector, m/s)      Options     -------     num_nodes : int         Number of analysis points to run (sets vec length) (default 1)