from __future__ import division
import numpy as np
from openmdao.api import ExplicitComponent
from .atmospherics_data import get_mask_arrays, compute_pressures, compute_pressure_derivs
[docs]class PressureComp(ExplicitComponent):
'''
This component computes pressure from altitude.
Adapted from:
J.P. Jasa, J.T. Hwang, and J.R.R.A. Martins: 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
'''
def initialize(self):
self.options.declare('num_nodes', types=int)
def setup(self):
num_points = self.options['num_nodes']
self.add_input('h_km', shape=num_points)
self.add_output('p_MPa', shape=num_points, lower=0.)
arange = np.arange(num_points)
self.declare_partials('p_MPa', 'h_km', rows=arange, cols=arange)
def compute(self, inputs, outputs):
num_points = self.options['num_nodes']
h_m = inputs['h_km'] * 1e3
self.tropos_mask, self.strato_mask, self.smooth_mask = get_mask_arrays(h_m)
p_Pa = compute_pressures(h_m, self.tropos_mask, self.strato_mask, self.smooth_mask)
outputs['p_MPa'] = p_Pa / 1e6
def compute_partials(self, inputs, partials):
num_points = self.options['num_nodes']
h_m = inputs['h_km'] * 1e3
derivs = compute_pressure_derivs(h_m, self.tropos_mask, self.strato_mask, self.smooth_mask)
partials['p_MPa', 'h_km'] = derivs * 1e3 / 1e6