def test_check_FFC_Isp_values(self):
"""test check FFC Isp values"""
geomObj = Geometry(Rthrt=1,
CR=2.5,
eps=62.5,
pcentBell=75,
RupThroat=1.5,
RdwnThroat=1.0,
RchmConv=1.0,
cham_conv_deg=30,
LchmOvrDt=3.10,
LchmMin=2.0,
LchamberInp=None)
effObj = Efficiencies()
effObj.set_const(
'ERE', 0.98) # don't know injector details so set effERE=0.98
# It's an ablative chamber, so some FFC (fuel film cooling) is required... guess about 10%
C = CoreStream(geomObj=geomObj,
effObj=effObj,
pcentFFC=10.0,
Pamb=0.001,
oxName='N2O4',
fuelName='A50',
MRcore=1.6,
Pc=100)
C.reset_attr('Pc', 100)
self.assertAlmostEqual(C('IspDel'), 325.64723, places=2)
self.assertAlmostEqual(C('IspODE'), 338.9201, places=2)
self.assertAlmostEqual(C('IspODF'), 320.4940, places=2)
import webbrowser
import os
from rocketisp.rocket_isp import RocketThruster
from rocketisp.geometry import Geometry
from rocketisp.stream_tubes import CoreStream
from rocketisp.efficiencies import Efficiencies
# create basic Geometry.
# Use "place-holder" of 1 inch for throat radius... correct later with "scale_Rt_to_Thrust"
geomObj = Geometry(Rthrt=1,
CR=2.5, eps=62.5, pcentBell=72.3,
RupThroat=1.5, RdwnThroat=1.0, RchmConv=1.0, cham_conv_deg=30,
LchmOvrDt=3.10, LchmMin=2.0, LchamberInp=None)
effObj = Efficiencies()
effObj.set_const('ERE', 0.98) # don't know injector details so set effERE=0.98
# It's an ablative chamber, so some FFC (fuel film cooling) is required... guess about 15%
core = CoreStream( geomObj=geomObj, effObj=effObj, pcentFFC=15.0,
oxName='N2O4', fuelName='A50', MRcore=1.6, Pc=100 )
R = RocketThruster(name='Apollo SPS',coreObj=core)
# scale geometry to give 20,500 lbf of thrust for current conditions
R.scale_Rt_to_Thrust( 20500 , Pamb=0.0 )
# figure out best mixture ratio to run the engine.
R.set_mr_to_max_ispdel()
# re-scale geometry to give 20,500 lbf of thrust after MR change
R.scale_Rt_to_Thrust( 20500 , Pamb=0.0 )
import os
from rocketisp.rocket_isp import RocketThruster
from rocketisp.geometry import Geometry
from rocketisp.stream_tubes import CoreStream
from rocketisp.efficiencies import Efficiencies
from rocketisp.examples.compare_vals import compare_header, compare
geomObj = Geometry(Rthrt=3,
CR=2.5, eps=55, pcentBell=80,
RupThroat=1.5, RdwnThroat=1.0, RchmConv=1.0, cham_conv_deg=30,
LchmOvrDt=3.10, LchmMin=2.0, LchamberInp=None)
effObj = Efficiencies()
effObj.set_const('ERE', 0.97 )
core = CoreStream( geomObj=geomObj, effObj=effObj,
oxName='N2O4', fuelName='MMH',
MRcore=1.65, Pc=125, pcentFFC=4.5 )
R = RocketThruster(name='Shuttle OMS',coreObj=core, injObj=None)
R.scale_Rt_to_Thrust( 6000 , Pamb=0.0 )
R.set_MRthruster( MRthruster=1.65 )
R.scale_Rt_to_Thrust( 6000 , Pamb=0.0 )
compare_header()
compare('Fvacuum',6000, core('FvacTotal'))
compare('Isp Vacuum', 313.2, core('IspDel'))
compare('Engine Length', 77, geomObj('Ltotal'))
compare('Nozzle ID', 43.09, geomObj('Rexit')*2)
sys.path.insert(0, os.path.abspath("../../")) # needed to find rocketisp development version
from rocketisp.rocket_isp import RocketThruster
from rocketisp.geometry import Geometry
from rocketisp.stream_tubes import CoreStream
from rocketisp.efficiencies import Efficiencies
from rocketisp.examples.compare_vals import compare_header, compare
geomObj = Geometry(Rthrt=Rthrt,
CR=(5.131/2.4724)**2, eps=eps, pcentBell=70,
RupThroat=1.5, RdwnThroat=1.0, RchmConv=1.0, cham_conv_deg=30,
LchmOvrDt=2.4842/2, LchmMin=2.0, LchamberInp=15.0)
effObj = Efficiencies()
effObj.set_const('ERE', 0.9892 )
core = CoreStream( geomObj, effObj, oxName='LOX', fuelName='LH2', MRcore=MRcore,
Pc=Pc, CdThroat=CdThroat)
R = RocketThruster(name='RL10',coreObj=core, injObj=None, calc_CdThroat=False,
noz_regen_eps=eps)
R.scale_Rt_to_Thrust( Fvac, Pamb=0.0 , use_scipy=False )
compare_header()
compare('Fvacuum',Fvac, core('FvacTotal'))
compare('Isp Vacuum', Isp, core('IspDel'))
compare('Cstar ODE', cstarODE, core('cstarODE'))
print()
compare('Fuel Flow Rate', wdotFuel, core('wdotFlCore'))
sys.path.insert(0, os.path.abspath("../../")) # needed to find rocketisp development version
from rocketisp.rocket_isp import RocketThruster
from rocketisp.geometry import Geometry
from rocketisp.stream_tubes import CoreStream
from rocketisp.efficiencies import Efficiencies
from rocketisp.examples.compare_vals import compare_header, compare
geomObj = Geometry(Rthrt=Rthrt,
CR=CR, eps=eps, pcentBell=70,
RupThroat=1.5, RdwnThroat=1.0, RchmConv=1.0, cham_conv_deg=30,
LchmOvrDt=2.4842/2, LchmMin=2.0, LchamberInp=Lcham)
effObj = Efficiencies()
effObj.set_const('ERE', cstarEff )
core = CoreStream( geomObj, effObj, oxName='LOX', fuelName='LH2', MRcore=MRcore,
Pc=Pc)
R = RocketThruster(name='RLIOA-3-3',coreObj=core, injObj=None, noz_regen_eps=eps)
#R.scale_Rt_to_Thrust( Fvac, Pamb=0.0 , use_scipy=False )
compare_header()
compare('Fvacuum',Fvac, core('FvacTotal'))
compare('Isp Vacuum', Isp, core('IspDel'))
compare('Cstar ODE', cstarODE, core('cstarODE'))
compare('Efficiency Cf/Noz', effCfODE, effObj('Noz'))
print()
from rocketisp.efficiencies import Efficiencies
geomObj = Geometry(Rthrt=5.868 / 2,
CR=2.5,
eps=150,
pcentBell=80,
RupThroat=1.5,
RdwnThroat=1.0,
RchmConv=1.0,
cham_conv_deg=30,
LchmOvrDt=3.10,
LchmMin=2.0,
LchamberInp=16)
effObj = Efficiencies()
effObj.set_const('Mix', 0.997329)
effObj.set_const('Em', 0.99644)
effObj.set_const('Kin', 0.975011)
effObj.set_const('BL', 0.9795)
effObj.set_const('Div', 0.994775)
core = CoreStream(geomObj,
effObj,
oxName='N2O4',
fuelName='MMH',
MRcore=1.85,
Pc=150,
CdThroat=0.995,
Pamb=14.7,
pcentFFC=14.0,
ko=0.035)
"""
model the XLR-134
"""
from rocketisp.rocket_isp import RocketThruster
from rocketisp.geometry import Geometry
from rocketisp.stream_tubes import CoreStream
from rocketisp.efficiencies import Efficiencies
geomObj = Geometry(Rthrt=1,
CR=3.0, eps=767.9, pcentBell=80,
RupThroat=1.5, RdwnThroat=1.0, RchmConv=1.0, cham_conv_deg=30,
LchmOvrDt=3.10, LchmMin=2.0, LchamberInp=None)
effObj = Efficiencies()
effObj.set_const('ERE', (490.45-8.6)/490.45)
core = CoreStream( geomObj, effObj, oxName='LOX', fuelName='LH2', MRcore=6.0,
Pc=510 )
R = RocketThruster(name='xlr134',coreObj=core, injObj=None)
R.scale_Rt_to_Thrust( 500 , Pamb=0.0 , use_scipy=False )
R.summ_print()
dpFuelInp = 200
geomObj = Geometry(Rthrt=Rt,
CR=CR,
eps=eps,
pcentBell=pcentBell,
RupThroat=0.5,
RdwnThroat=1.0,
RchmConv=0.5,
cham_conv_deg=30,
LchmOvrDt=3,
LchmMin=2.0,
LchamberInp=Lcham)
effObj = Efficiencies()
effObj.set_const('ERE', 0.975)
effObj.set_const('Noz', 0.933177) # Huzel based on frozen Isp
core = CoreStream(geomObj,
effObj,
oxName=oxName,
fuelName=fuelName,
MRcore=MR,
Pc=Pc,
Pamb=14.7,
CdThroat=1.0,
adjCstarODE=0.978196,
adjIspIdeal=1.0084418978404621)
C = RocketThruster(name='Huzel A-1', coreObj=core, calc_CdThroat=False)
dpFuelInp = 25
geomObj = Geometry(Rthrt=Rt,
CR=CR,
eps=eps,
pcentBell=pcentBell,
RupThroat=0.5,
RdwnThroat=1.0,
RchmConv=0.5,
cham_conv_deg=30,
LchmOvrDt=3,
LchmMin=2.0,
LchamberInp=Lcham)
effObj = Efficiencies()
effObj.set_const('ERE', 0.98)
effObj.set_const('Noz', 0.946901)
core = CoreStream(geomObj,
effObj,
oxName=oxName,
fuelName=fuelName,
MRcore=MR,
Pc=Pc,
Pamb=14.7,
CdThroat=1.0,
adjCstarODE=0.975554,
adjIspIdeal=1.01214)
C = RocketThruster(name='Huzel A-4', coreObj=core, calc_CdThroat=False)