def test_MissionSegment(self):
#num_elem = 100
#num_cp = 30
x_range = 9000.0
num_elem = 6
num_cp = 3
altitude = np.zeros(num_elem + 1)
altitude = 10 * np.sin(np.pi * np.linspace(0, 1, num_elem + 1))
x_range *= 1.852
x_init = x_range * 1e3 * (
1 - np.cos(np.linspace(0, 1, num_cp) * np.pi)) / 2 / 1e6
M_init = np.ones(num_cp) * 0.8
h_init = 10 * np.sin(np.pi * x_init / (x_range / 1e3))
model = set_as_top(
MissionSegment(num_elem=num_elem,
num_cp=num_cp,
x_pts=x_init,
surr_file='../crm_surr'))
model.h_pt = h_init
model.M_pt = M_init
model.set_init_h_pt(altitude)
# Initial parameters
model.S = 427.8 / 1e2
model.ac_w = 210000 * 9.81 / 1e6
model.thrust_sl = 1020000.0 / 1e6
model.SFCSL = 8.951 * 9.81
model.AR = 8.68
model.oswald = 0.8
# Add param/obj/constr to make sure they set up.
#gamma_lb = np.tan(-10.0 * (np.pi/180.0))/1e-1
#gamma_ub = np.tan(10.0 * (np.pi/180.0))/1e-1
#model.replace('driver', SimpleDriver())
#model.driver.add_parameter('h_pt', low=0.0, high=20.0)
#model.driver.add_objective('SysFuelObj.fuelburn')
#model.driver.add_constraint('SysHi.h_i = 0.0')
#model.driver.add_constraint('SysHf.h_f = 0.0')
#model.driver.add_constraint('SysTmin.Tmin < 0.0')
#model.driver.add_constraint('SysTmax.Tmax < 0.0')
#model.driver.add_constraint('%.15f < SysGammaBspline.Gamma < %.15f' %
#(gamma_lb, gamma_ub), linear=True)
# Linear GS doesn't work yet
#model.driver.gradient_options.lin_solver = 'petsc_ksp'
model.run()
def test_MissionSegment(self):
num_elem = 100
num_cp = 30
x_range = 150.0
x_init = x_range * 1e3 * (1-np.cos(np.linspace(0, 1, num_cp)*np.pi))/2/1e6
v_init = np.ones(num_cp)*2.3
h_init = 1 * np.sin(np.pi * x_init / (x_range/1e3))
model = set_as_top(MissionSegment(num_elem, num_cp, x_init))
model.h_pt = h_init
model.v_pt = v_init
# Pull velocity from BSpline instead of calculating it.
model.SysSpeed.v_specified = True
# Initial parameters
model.S = 427.8/1e2
model.ac_w = 210000*9.81/1e6
model.thrust_sl = 1020000.0/1e6/3
model.SFCSL = 8.951
model.AR = 8.68
model.oswald = 0.8
model.run()
# Load in original data from pickle
dirname = os.path.abspath(os.path.dirname(__file__))
filename = os.path.join(dirname, 'analysis.p')
old_data = pickle.load(open(filename, 'rb'))
# Some names changed
old_data['Gamma'] = old_data['gamma']
old_data['temp'] = old_data['Temp']
# Don't compare the extra constraint/objective stuff, because we
# don't create comps for them.
old_keys = old_data.keys()
old_keys.remove('gamma')
old_keys.remove('gamma_max')
old_keys.remove('gamma_min')
#old_keys.remove('Tmin')
#old_keys.remove('Tmax')
#old_keys.remove('h_i')
#old_keys.remove('h_f')
#old_keys.remove('wf_obj')
old_keys.remove('CL_tar')
old_keys.remove('thrust_sl')
old_keys.remove('e')
old_keys.remove('Temp')
old_keys.remove('M_pt')
# Find data in model
new_data = {}
comps = [comp for comp in model.list_components() if comp not in ['coupled_solver', 'drag_solver']]
for name in comps:
comp = model.get(name)
for key in old_keys:
if key in comp.list_vars():
new_data[key] = comp.get(key)
old_keys.remove(key)
self.assertEqual(len(old_keys), 0)
for key in new_data.keys():
old = old_data[key]
new = new_data[key]
#diff = np.nan_to_num(abs(new - old) / old)
diff = new-old
#print key
#print old
#print new
assert_rel_error(self, diff.max(), 0.0, 1e-12)
altitude = np.zeros(num_elem + 1)
altitude = 10 * np.sin(np.pi * np.linspace(0, 1, num_elem + 1))
start = time.time()
num_cp = num_cp_init
while num_cp <= num_cp_max:
x_range *= 1.852
x_init = x_range * 1e3 * (
1 - np.cos(np.linspace(0, 1, num_cp) * np.pi)) / 2 / 1e6
M_init = np.ones(num_cp) * 0.82
h_init = 10 * np.sin(np.pi * x_init / (x_range / 1e3))
model = set_as_top(
MissionSegment(num_elem=num_elem,
num_cp=num_cp,
x_pts=x_init,
surr_file='crm_surr'))
model.replace('driver', pyOptSparseDriver())
#model.replace('driver', SimpleDriver())
model.driver.optimizer = 'SNOPT'
model.driver.options = {'Iterations limit': 5000000}
# Add parameters, objectives, constraints
model.driver.add_parameter('h_pt', low=0.0, high=14.1)
model.driver.add_objective('SysFuelObj.fuelburn')
model.driver.add_constraint('SysHBspline.h[0] = 0.0')
model.driver.add_constraint('SysHBspline.h[-1] = 0.0')
model.driver.add_constraint('SysTmin.Tmin < 0.0')
model.driver.add_constraint('SysTmax.Tmax < 0.0')
model.driver.add_constraint('%.15f < SysGammaBspline.Gamma < %.15f' % \
def test_MissionSegment(self):
num_elem = 100
num_cp = 30
x_range = 9000.0
altitude = np.zeros(num_elem + 1)
altitude = 10 * np.sin(np.pi * np.linspace(0, 1, num_elem + 1))
x_range *= 1.852
x_init = x_range * 1e3 * (
1 - np.cos(np.linspace(0, 1, num_cp) * np.pi)) / 2 / 1e6
M_init = np.ones(num_cp) * 0.8
h_init = 10 * np.sin(np.pi * x_init / (x_range / 1e3))
model = set_as_top(
MissionSegment(num_elem=num_elem,
num_cp=num_cp,
x_pts=x_init,
surr_file='../crm_surr'))
model.h_pt = h_init
model.M_pt = M_init
model.set_init_h_pt(altitude)
# Initial parameters
model.S = 427.8 / 1e2
model.ac_w = 210000 * 9.81 / 1e6
model.thrust_sl = 1020000.0 / 1e6
model.SFCSL = 8.951 * 9.81
model.AR = 8.68
model.oswald = 0.8
# Some adjustments to match the case ran for the pickle
#model.SysFuelWeight.fuel_scale = 1e6
#model.SysTau.thrust_scale = 0.072
model.run()
# Load in original data from pickle
dirname = os.path.abspath(os.path.dirname(__file__))
filename = os.path.join(dirname, 'analysis2.p')
old_data = pickle.load(open(filename, 'rb'))
# Some names changed
old_data['Gamma'] = old_data['gamma']
old_data['temp'] = old_data['Temp']
# Don't compare the extra constraint/objective stuff, because we
# don't create comps for them.
old_keys = old_data.keys()
old_keys.remove('gamma')
old_keys.remove('CL_tar')
old_keys.remove('Temp')
old_keys.remove('M_i')
old_keys.remove('M_f')
old_keys.remove('h_i')
old_keys.remove('h_f')
old_keys.remove('M_spline')
old_keys.remove('jason')
old_keys.remove('time')
# Find data in model
new_data = {}
comps = [
comp for comp in model.list_components()
if comp not in ['coupled_solver']
]
for name in comps:
comp = model.get(name)
s1 = set(comp.list_vars())
s2 = set(old_keys)
s_int = s1.intersection(s2)
for key in s_int:
new_data[key] = comp.get(key)
old_keys.remove(key)
print old_keys
self.assertEqual(len(old_keys), 0)
for key in new_data.keys():
old = old_data[key]
new = new_data[key]
#diff = np.nan_to_num(abs(new - old) / old)
diff = new - old
print key
print old
print new
assert_rel_error(self, diff.max(), 0.0, 1e-3)
def test_MissionSegment(self):
# define bounds for the flight path angle
gamma_lb = np.tan(-10.0 * (np.pi / 180.0)) / 1e-1
gamma_ub = np.tan(10.0 * (np.pi / 180.0)) / 1e-1
num_elem = 100
num_cp = 30
x_range = 9000.0
altitude = np.zeros(num_elem + 1)
altitude = 10 * np.sin(np.pi * np.linspace(0, 1, num_elem + 1))
x_range *= 1.852
x_init = x_range * 1e3 * (
1 - np.cos(np.linspace(0, 1, num_cp) * np.pi)) / 2 / 1e6
M_init = np.ones(num_cp) * 0.8
h_init = 10 * np.sin(np.pi * x_init / (x_range / 1e3))
model = set_as_top(
MissionSegment(num_elem=num_elem,
num_cp=num_cp,
x_pts=x_init,
surr_file='../crm_surr'))
model.replace('driver', SimpleDriver())
model.h_pt = h_init
model.M_pt = M_init
model.set_init_h_pt(altitude)
# Initial parameters
model.S = 427.8 / 1e2
model.ac_w = 210000 * 9.81 / 1e6
model.thrust_sl = 1020000.0 / 1e6
model.SFCSL = 8.951 * 9.81
model.AR = 8.68
model.oswald = 0.8
model.driver.add_parameter('h_pt', low=0.0, high=20.0)
model.driver.add_objective('SysFuelObj.fuelburn')
model.driver.add_constraint('SysHi.h_i = 0.0')
model.driver.add_constraint('SysHf.h_f = 0.0')
model.driver.add_constraint('SysTmin.Tmin < 0.0')
model.driver.add_constraint('SysTmax.Tmax < 0.0')
model.driver.add_constraint('%.15f < SysGammaBspline.Gamma < %.15f' %
(gamma_lb, gamma_ub),
linear=True)
model.run()
new_derivs = model.driver.calc_gradient(return_format='dict')
# Load in original data from pickle
dirname = os.path.abspath(os.path.dirname(__file__))
filename = os.path.join(dirname, 'derivs2.p')
old_derivs_dict = pickle.load(open(filename, 'rb'))
translate_dict = {
'fuelburn': '_pseudo_2.out0',
'h_i': '_pseudo_3.out0',
'h_f': '_pseudo_4.out0',
'Tmin': '_pseudo_5.out0',
'Tmax': '_pseudo_6.out0'
}
#'gamma': '_pseudo_12.out0'}
for j, key in enumerate(translate_dict.keys()):
old = old_derivs_dict[key]['h_pt']
print 'h_pt', key
openmdao_key = translate_dict[key]
new = new_derivs[openmdao_key]['h_pt']
diff = new - old
print 'old', old
print 'new', new
assert_rel_error(self, diff.max(), 0.0, 2e-5)
for i in xrange(0, num_elem):
old = old_derivs_dict['gamma'][i]['h_pt']
#print 'h_pt', 'gamma'+str(i)
new = new_derivs['_pseudo_7.out0']['h_pt'][i, :]
diff = new - old
#print 'old', old
#print 'new', new
assert_rel_error(self, diff.max(), 0.0, 2e-5)
# define bounds for the flight path angle
gamma_lb = np.tan(-35.0 * (np.pi/180.0))/1e-1
gamma_ub = np.tan(35.0 * (np.pi/180.0))/1e-1
takeoff_speed = 83.3
landing_speed = 72.2
altitude = 10 * np.sin(np.pi * np.linspace(0,1,num_elem+1))
start = time.time()
x_range *= 1.852
x_init = x_range * 1e3 * (1-np.cos(np.linspace(0, 1, num_cp)*np.pi))/2/1e6
M_init = np.ones(num_cp)*0.82
h_init = 10 * np.sin(np.pi * x_init / (x_range/1e3))
model.add('seg1', MissionSegment(num_elem=num_elem, num_cp=num_cp,
x_pts=x_init, surr_file='crm_surr'))
# Initial value of the parameter
model.seg1.h_pt = h_init
model.seg1.M_pt = M_init
model.seg1.set_init_h_pt(altitude)
# Calculate velocity from the Mach we have specified.
model.seg1.SysSpeed.v_specified = False
# Initial design parameters
model.seg1.S = 427.8/1e2
model.seg1.ac_w = 210000*9.81/1e6
model.seg1.thrust_sl = 1020000.0/1e6
model.seg1.SFCSL = 8.951*9.81
model.seg1.AR = 8.68
altitude = np.zeros(num_elem+1)
altitude = 10 * np.sin(np.pi * np.linspace(0,1,num_elem+1))
start = time.time()
num_cp = num_cp_init
while num_cp <= num_cp_max:
x_range *= 1.852
x_init = x_range * 1e3 * (1-np.cos(np.linspace(0, 1, num_cp)*np.pi))/2/1e6
#v_init = np.ones(num_cp)*2.5
M_init = np.ones(num_cp)*0.8
#M_init = np.ones(num_cp)*0.82
h_init = 10 * np.sin(np.pi * x_init / (x_range/1e3))
model = set_as_top(MissionSegment(num_elem=num_elem, num_cp=num_cp,
x_pts=x_init, surr_file=os.path.join('..','src','pyMission','crm_surr')))
model.replace('driver', pyOptSparseDriver())
#model.replace('driver', SimpleDriver())
model.driver.optimizer = 'SNOPT'
model.driver.options = {'Iterations limit': 5000000,
'Print file': os.path.join('plotting','weight_sweep_data','SNOPT_%d_print.out' % k)
}
# Add parameters, objectives, constraints
model.driver.add_parameter('h_pt', low=0.0, high=14.1)
model.driver.add_objective('SysFuelObj.fuelburn')
model.driver.add_constraint('SysHi.h_i = 0.0')
model.driver.add_constraint('SysHf.h_f = 0.0')
model.driver.add_constraint('SysTmin.Tmin < 0.0')
model.driver.add_constraint('SysTmax.Tmax < 0.0')
def test_MissionSegment(self):
# define bounds for the flight path angle
gamma_lb = np.tan(-10.0 * (np.pi / 180.0)) / 1e-1
gamma_ub = np.tan(10.0 * (np.pi / 180.0)) / 1e-1
num_elem = 10
num_cp = 5
x_range = 150.0
x_init = x_range * 1e3 * (
1 - np.cos(np.linspace(0, 1, num_cp) * np.pi)) / 2 / 1e6
v_init = np.ones(num_cp) * 2.3
h_init = 1 * np.sin(np.pi * x_init / (x_range / 1e3))
model = set_as_top(MissionSegment(num_elem, num_cp, x_init))
model.replace('driver', SimpleDriver())
model.h_pt = h_init
model.v_pt = v_init
# Pull velocity from BSpline instead of calculating it.
model.SysSpeed.v_specified = True
# Initial parameters
model.S = 427.8 / 1e2
model.ac_w = 210000 * 9.81 / 1e6
model.thrust_sl = 1020000.0 / 1e6 / 3
model.SFCSL = 8.951
model.AR = 8.68
model.oswald = 0.8
model.driver.add_parameter('h_pt', low=0.0, high=20.0)
model.driver.add_objective('SysFuelObj.wf_obj')
model.driver.add_constraint('SysHi.h_i = 0.0')
model.driver.add_constraint('SysHf.h_f = 0.0')
model.driver.add_constraint('SysTmin.Tmin < 0.0')
model.driver.add_constraint('SysTmax.Tmax < 0.0')
model.driver.add_constraint('%.15f < SysGammaBspline.Gamma < %.15f' % \
(gamma_lb, gamma_ub), linear=True)
model.run()
new_derivs = model.driver.workflow.calc_gradient()
# Load in original data from pickle
dirname = os.path.abspath(os.path.dirname(__file__))
filename = os.path.join(dirname, 'derivs.p')
old_derivs_dict = pickle.load(open(filename, 'rb'))
for i in range(0, 4):
old_derivs = old_derivs_dict['h_pt' + str(i)]
print 'h_pt' + str(i)
for j, key in enumerate(['wf_obj', 'h_i', 'h_f', 'Tmin', 'Tmax']):
old = old_derivs[key]
new = new_derivs[j, i]
#diff = np.nan_to_num(abs(new - old) / old)
diff = new - old
print key
print old
print new
assert_rel_error(self, diff.max(), 0.0, 1e-5)
x_range = 15000.0
# define bounds for the flight path angle
gamma_lb = np.tan(-10.0 * (np.pi / 180.0)) / 1e-1
gamma_ub = np.tan(10.0 * (np.pi / 180.0)) / 1e-1
start = time.time()
num_cp = num_cp_init
while num_cp <= num_cp_max:
x_init = x_range * 1e3 * (
1 - np.cos(np.linspace(0, 1, num_cp) * np.pi)) / 2 / 1e6
v_init = np.ones(num_cp) * 2.3
h_init = 1 * np.sin(np.pi * x_init / (x_range / 1e3))
model = set_as_top(MissionSegment(num_elem, num_cp, x_init))
model.replace('driver', pyOptSparseDriver())
model.driver.optimizer = 'SNOPT'
#opt_dict = {'Iterations limit': 1000000,
# 'Major iterations limit': 1000000,
# 'Minor iterations limit': 1000000 }
#model.driver.options = opt_dict
# Add parameters, objectives, constraints
model.driver.add_parameter('h_pt', low=0.0, high=20.0)
model.driver.add_objective('SysFuelObj.wf_obj')
model.driver.add_constraint('SysHi.h_i = 0.0')
model.driver.add_constraint('SysHf.h_f = 0.0')
model.driver.add_constraint('SysTmin.Tmin < 0.0')
model.driver.add_constraint('SysTmax.Tmax < 0.0')
model.driver.add_constraint('%.15f < SysGammaBspline.Gamma < %.15f' % \
# define bounds for the flight path angle
gamma_lb = np.tan(-35.0 * (np.pi/180.0))/1e-1
gamma_ub = np.tan(35.0 * (np.pi/180.0))/1e-1
takeoff_speed = 83.3
landing_speed = 72.2
takeoff_M = takeoff_speed / np.sqrt(1.4*287*288)
landing_M = landing_speed / np.sqrt(1.4*287*288)
# Convert from NMi to km
x_range *= 1.852
x_init = x_range * 1e3 * (1-np.cos(np.linspace(0, 1, num_cp)*np.pi))/2/1e6
M_init = 0.5 * np.sin(np.pi * x_init / (x_range/1e3)) + 0.3
h_init = 10 * np.sin(np.pi * x_init / (x_range/1e3))
model = set_as_top(MissionSegment(num_elem=num_elem, num_cp=num_cp,
x_pts=x_init, surr_file='../crm_surr'))
model.replace('driver', pyOptSparseDriver())
#model.replace('driver', SimpleDriver())
model.driver.optimizer = 'SNOPT'
# Initial design parameters
model.S = 427.8/1e2
model.ac_w = 210000*9.81/1e6
model.thrust_sl = 1020000.0/1e6
model.SFCSL = 8.951*9.81
model.AR = 8.68
model.oswald = 0.8
# Needs to use the old propulsion model
model.SysTau.thrust_scale = 0.072
