<gh_stars>10-100
'''
This module provides 1976 Standard Atmosphere constants and calculations.

Adapted from:
<NAME>, <NAME>, and <NAME>: Design and Trajectory Optimization of a Morphing Wing Aircraft
2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; AIAA SciTech Forum, January 2018
'''

from __future__ import division
import numpy as np

# tropopause
epsilon = 500
h_trans = 11000
h_lower = h_trans - epsilon
h_upper = h_trans + epsilon
tropopause_matrix = np.array([
    [h_lower**3, h_lower**2, h_lower, 1],
    [h_upper**3, h_upper**2, h_upper, 1],
    [3*h_lower**2, 2*h_lower, 1, 0],
    [3*h_upper**2, 2*h_upper, 1, 0],
])

# pressure
tmp1 = 1 - 0.0065 * h_lower / 288.16
tmp2 = np.exp(-9.81*epsilon/(288*216.65))
pressure_rhs = np.array([
    101325 * tmp1 ** 5.2561,
    22632 * tmp2,
    (-101325*5.2561*(0.0065/288.16)*tmp1**4.2561),
    (22632 * (-9.81/(288*216.65)) * tmp2)])
pressure_coeffs = np.linalg.solve(tropopause_matrix, pressure_rhs)

# temperature
temp_rhs = np.array([
    288.16 - (6.5e-3) * h_lower,
    216.65,
    -6.5e-3,
    0,
])
temp_coeffs = np.linalg.solve(tropopause_matrix, temp_rhs)

# functions
def get_mask_arrays(h_m):
    tropos_mask = h_m <= h_lower
    strato_mask = h_m >  h_upper
    smooth_mask = np.logical_and(~tropos_mask, ~strato_mask)
    return tropos_mask, strato_mask, smooth_mask

def compute_pressures(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = pressure_coeffs

    p_Pa = np.zeros(len(h_m), dtype=type(h_m[0]))
    p_Pa += tropos_mask * (101325*(1-0.0065*h_m/288.16)**5.2561)
    p_Pa += strato_mask * (22632*np.exp(-9.81*(h_m-h_trans)/(288*216.65)))
    p_Pa += smooth_mask * (a*h_m**3 + b*h_m**2 + c*h_m + d)

    return p_Pa

def compute_pressure_derivs(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = pressure_coeffs

    derivs = np.zeros(len(h_m), dtype=type(h_m[0]))
    derivs += tropos_mask * (101325*5.2561*(-0.0065/288.16) * (1-0.0065*h_m/288.16)**4.2561)
    derivs += strato_mask * (22632*(-9.81/(288*216.65))
        *np.exp(9.81*11000/(288*216.65))*np.exp(-9.81*h_m/(288*216.65)))
    derivs += smooth_mask * (3*a*h_m**2 + 2*b*h_m + c)

    return derivs

def compute_temps(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = temp_coeffs

    temp_K = np.zeros(len(h_m), dtype=type(h_m[0]))
    temp_K += tropos_mask * (288.16 - (6.5e-3) * h_m)
    temp_K += strato_mask * 216.65
    temp_K += smooth_mask * (a * h_m ** 3 + b * h_m ** 2 + c * h_m + d)

    return temp_K

def compute_temp_derivs(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = temp_coeffs

    derivs = np.zeros(len(h_m), dtype=type(h_m[0]))
    derivs += tropos_mask * (-6.5e-3)
    derivs += smooth_mask * (3*a*h_m**2 + 2*b*h_m + c)

    return derivs

'''
This module provides 1976 Standard Atmosphere constants and calculations.

Adapted from:
<NAME>, <NAME>, and <NAME>: Design and Trajectory Optimization of a Morphing Wing Aircraft
2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; AIAA SciTech Forum, January 2018
'''

from __future__ import division
import numpy as np

# tropopause
epsilon = 500
h_trans = 11000
h_lower = h_trans - epsilon
h_upper = h_trans + epsilon
tropopause_matrix = np.array([
    [h_lower**3, h_lower**2, h_lower, 1],
    [h_upper**3, h_upper**2, h_upper, 1],
    [3*h_lower**2, 2*h_lower, 1, 0],
    [3*h_upper**2, 2*h_upper, 1, 0],
])

# pressure
tmp1 = 1 - 0.0065 * h_lower / 288.16
tmp2 = np.exp(-9.81*epsilon/(288*216.65))
pressure_rhs = np.array([
    101325 * tmp1 ** 5.2561,
    22632 * tmp2,
    (-101325*5.2561*(0.0065/288.16)*tmp1**4.2561),
    (22632 * (-9.81/(288*216.65)) * tmp2)])
pressure_coeffs = np.linalg.solve(tropopause_matrix, pressure_rhs)

# temperature
temp_rhs = np.array([
    288.16 - (6.5e-3) * h_lower,
    216.65,
    -6.5e-3,
    0,
])
temp_coeffs = np.linalg.solve(tropopause_matrix, temp_rhs)

# functions
def get_mask_arrays(h_m):
    tropos_mask = h_m <= h_lower
    strato_mask = h_m >  h_upper
    smooth_mask = np.logical_and(~tropos_mask, ~strato_mask)
    return tropos_mask, strato_mask, smooth_mask

def compute_pressures(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = pressure_coeffs

    p_Pa = np.zeros(len(h_m), dtype=type(h_m[0]))
    p_Pa += tropos_mask * (101325*(1-0.0065*h_m/288.16)**5.2561)
    p_Pa += strato_mask * (22632*np.exp(-9.81*(h_m-h_trans)/(288*216.65)))
    p_Pa += smooth_mask * (a*h_m**3 + b*h_m**2 + c*h_m + d)

    return p_Pa

def compute_pressure_derivs(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = pressure_coeffs

    derivs = np.zeros(len(h_m), dtype=type(h_m[0]))
    derivs += tropos_mask * (101325*5.2561*(-0.0065/288.16) * (1-0.0065*h_m/288.16)**4.2561)
    derivs += strato_mask * (22632*(-9.81/(288*216.65))
        *np.exp(9.81*11000/(288*216.65))*np.exp(-9.81*h_m/(288*216.65)))
    derivs += smooth_mask * (3*a*h_m**2 + 2*b*h_m + c)

    return derivs

def compute_temps(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = temp_coeffs

    temp_K = np.zeros(len(h_m), dtype=type(h_m[0]))
    temp_K += tropos_mask * (288.16 - (6.5e-3) * h_m)
    temp_K += strato_mask * 216.65
    temp_K += smooth_mask * (a * h_m ** 3 + b * h_m ** 2 + c * h_m + d)

    return temp_K

def compute_temp_derivs(h_m, tropos_mask, strato_mask, smooth_mask):
    a, b, c, d = temp_coeffs

    derivs = np.zeros(len(h_m), dtype=type(h_m[0]))
    derivs += tropos_mask * (-6.5e-3)
    derivs += smooth_mask * (3*a*h_m**2 + 2*b*h_m + c)

    return derivs
This module provides 1976 Standard Atmosphere constants and calculations.  Adapted from: <NAME>, <NAME>, and <NAME>: Design and Trajectory Optimization of a Morphing Wing Aircraft 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; AIAA SciTech Forum, January 2018 # tropopause # pressure # temperature # functions