def test_gravity_loss(self):
# check against ...
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 407
LEO.periapsis = 407
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.C3 = -1.671
templ = 'Gravity Loss from %3dk LEO with C3 of %5.3f and T/W of %5.3f = %5.3f'
TW = 0.11
print templ % (maneuver.orbit.apoapsis, maneuver.C3, TW,
maneuver.gravity_loss(TW, burns=2))
TW = 0.103
print templ % (maneuver.orbit.apoapsis, maneuver.C3, TW,
maneuver.gravity_loss(TW, burns=2))
TW = 0.165
print templ % (maneuver.orbit.apoapsis, maneuver.C3, TW,
maneuver.gravity_loss(TW, burns=2))
TW = 0.139
print templ % (maneuver.orbit.apoapsis, maneuver.C3, TW,
maneuver.gravity_loss(TW, burns=2))
def test_SKB91(self):
# (check against Borowski hand calcs dated 5/24/91)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/24/91 Ex #1, TLI from 407km circular orbit with C3 = -1 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 407
LEO.periapsis = 407
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = -1
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 3.128, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/24/91 Ex #2, TLI from 481.5km circular orbit with C3 = 1.912 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 481.5
LEO.periapsis = 481.5
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 1.912
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 3.247, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/24/91 Ex #2, TLI from 485km circular orbit with C3 = 1.912 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 485
LEO.periapsis = 485
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 1.912
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 3.246, 0.005)
#
# McDDAC Lunar Shuttle Mission, "8-Burn Profile"
# (check against Borowski hand calcs dated 5/27/91)
#
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (1), LOI into 24hr lunar orbit')
self.logger.info(' with apolune = 15.853 km, perilune = 111.12 km and C3 of 0.808 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
ELO = Orbit()
ELO.body = 'Moon'
ELO.apoapsis = 15853.12
ELO.periapsis = 111.12
maneuver = Maneuver()
maneuver.orbit = ELO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.808
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.2815, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (1a), 30 deg plane change from 24hr lunar orbit')
self.logger.info(' with apolune = 15.853 km, perilune = 111.12 km')
self.logger.info('--------------------------------------------------------------------------------')
ELO = Orbit()
ELO.body = 'Moon'
ELO.apoapsis = 15853.12
ELO.periapsis = 111.12
maneuver = Maneuver()
maneuver.orbit = ELO
maneuver.orbit.inclination = 30 # FIXME: quick&dirty hack, this is the maneuver not the orbit
maneuver.maneuver_type = 'Plane Change'
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 0.119, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (2), circularize lunar orbit at periapsis starting at orbit')
self.logger.info(' with apolune = 15.853 km, perilune = 111.12 km')
self.logger.info('--------------------------------------------------------------------------------')
ELO = Orbit()
ELO.body = 'Moon'
ELO.apoapsis = 15853.12
ELO.periapsis = 111.12
maneuver = Maneuver()
maneuver.orbit = ELO
maneuver.maneuver_type = 'Circularize at Periapsis'
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, .562, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (2), Trans Earth Injection with C3 of 1.486 km2/s2 from')
self.logger.info(' 24 hr lunar orbit with apolune = 15.853 km, perilune = 111.12 km ')
self.logger.info('--------------------------------------------------------------------------------')
LLO = Orbit()
LLO.body = 'Moon'
LLO.apoapsis = 15853.12
LLO.periapsis = 111.12
maneuver = Maneuver()
maneuver.orbit = LLO
maneuver.maneuver_type = 'Departure from Periapsis'
maneuver.C3 = 1.486
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 0.415, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (3), EOC into 481.5 km circular Earth orbit with C3 of 1.378 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 481.5
LEO.periapsis = 481.5
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 1.378
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -3.221, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (4), TLI from 481.5 km circular orbit with C3 = 1.912 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 481.5
LEO.periapsis = 481.5
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 1.912
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 3.246, 0.005)
#
# "4-Burn" Lunar Shuttle Mission
# (check against Borowski hand calcs dated 5/27/91)
#
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (5), LOI into 111.12 km circular orbit with C3 = 0.808 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LLO = Orbit()
LLO.body = 'Moon'
LLO.apoapsis = 111.12
LLO.periapsis = 111.12
maneuver = Maneuver()
maneuver.orbit = LLO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.808
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.844, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 5/27/91 (5), Trans Earth Injection with C3 of 1.486 km2/s2 from')
self.logger.info(' 24 hr lunar orbit with apolune = 15.853 km, perilune = 111.12 km ')
self.logger.info('--------------------------------------------------------------------------------')
LLO = Orbit()
LLO.body = 'Moon'
LLO.apoapsis = 111.12
LLO.periapsis = 111.12
maneuver = Maneuver()
maneuver.orbit = LLO
maneuver.maneuver_type = 'Departure from Periapsis'
maneuver.C3 = 1.486
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 0.977, 0.005)
def test_SKB92(self):
# (check against Borowski hand calcs dated 10/9/92)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2007 Cargo (1), TMI from 407km circular orbit with C3 = 13.41 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 407
LEO.periapsis = 407
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 13.41
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 3.776, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2007 Cargo (2), MOC into 250km x 33840km orbit with C3 = 6.35 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
MEO = Orbit()
MEO.body = 'Mars'
MEO.apoapsis = 250
MEO.periapsis = 33840
maneuver = Maneuver()
maneuver.orbit = MEO
maneuver.maneuver_type = 'Capture at Apoapsis'
maneuver.C3 = 6.35
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.837, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2009 Tanker (1) TMI from 407km circular orbit with C3 = 10.30 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 407
LEO.periapsis = 407
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 10.30
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 3.640, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2009 Tanker (2) MOC into 250km x 33840km orbit with C3 = 6.10 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
MEO = Orbit()
MEO.body = 'Mars'
MEO.apoapsis = 250
MEO.periapsis = 33840
maneuver = Maneuver()
maneuver.orbit = MEO
maneuver.maneuver_type = 'Capture at Apoapsis'
maneuver.C3 = 6.10
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.814, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2009 Crew (1) TMI from 407km circular orbit with C3 = 30.65 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 407
LEO.periapsis = 407
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 30.65
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 4.506, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2009 Crew (2) MOC into 250km x 33840km orbit with C3 = 6.10 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
MEO = Orbit()
MEO.body = 'Mars'
MEO.apoapsis = 250
MEO.periapsis = 33840
maneuver = Maneuver()
maneuver.orbit = MEO
maneuver.maneuver_type = 'Capture at Apoapsis'
maneuver.C3 = 27.40
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -2.508, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 10/9/92 2009 Crew (3) TEI from 250km x 33840km orbit with C3 = 17.31 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
MEO = Orbit()
MEO.body = 'Mars'
MEO.apoapsis = 250
MEO.periapsis = 33840
maneuver = Maneuver()
maneuver.orbit = MEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 17.31
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, 1.762, 0.005)
def test_SKB00(self):
# "90 Day" Study LeRC Data *All Propulsive Optimized Trajectory
# 2016 Opposition Mars Mission
# (check against Borowski hand calcs dated 6/30/00)
# define Orbits
LEO = Orbit()
LEO.body = 'Earth'
LEO.apoapsis = 407
LEO.periapsis = 407
MEO = Orbit()
MEO.body = 'Mars'
MEO.apoapsis = 250
MEO.periapsis = 33840
HEEO = Orbit()
HEEO.body = 'Earth'
HEEO.apoapsis = 71136
HEEO.periapsis = 500
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 6/30/00 2016 Opposition (1), TMI from LEO with C3 = 14.06 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = LEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 14.06
dV_TMI = maneuver.calculate_dV()
assert_rel_error(self, dV_TMI, 3.805, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 6/30/00 2016 Opposition (2), MOC into MEO with Vinf = 5.31 km/s')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = MEO
maneuver.maneuver_type = 'Capture at Apoapsis'
maneuver.C3 = 5.31**2
dV_MOC = maneuver.calculate_dV()
assert_rel_error(self, dV_MOC, -2.563, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 6/30/00 2016 Opposition (3) TEI from MEO with C3 = 50.552 km2/s2')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = MEO
maneuver.maneuver_type = 'Departure from Apoapsis'
maneuver.C3 = 50.552
dV_TEI = maneuver.calculate_dV()
assert_rel_error(self, dV_TEI, 3.978, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 6/30/00 2016 Opposition (4), EOC into HEEO with Vinf = 5.56 km/s')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = HEEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 5.56**2
dV_EOC = maneuver.calculate_dV()
assert_rel_error(self, dV_EOC, -1.799, 0.005)
total_dV = abs(dV_TMI) + abs(dV_MOC) + abs(dV_TEI) + abs(dV_EOC)
self.logger.info('Total Ideal Delta V = '+str(total_dV))
assert_rel_error(self, total_dV, 12.145, 0.005)
def test_SKB13(self):
# Borowski notes dated 3/17/13
# check against Laura Burke results in e-mail dated 9/20/12
LEO = Orbit()
LEO.body = 'Earth'
LEO.periapsis = 407
LEO.apoapsis = 407
LEO.inclination = 28.5
HEEO_24hr = Orbit()
HEEO_24hr.body = 'Earth'
HEEO_24hr.periapsis = 500
HEEO_24hr.apoapsis = 71136
HEEO_48hr = Orbit()
HEEO_48hr.body = 'Earth'
HEEO_48hr.periapsis = 500
HEEO_48hr.apoapsis = 120702
LLO_110 = Orbit()
LLO_110.body = 'Moon'
LLO_110.periapsis = 110
LLO_110.apoapsis = 110
LLO_300 = Orbit()
LLO_300.body = 'Moon'
LLO_300.periapsis = 300
LLO_300.apoapsis = 300
def test_SKB12(self):
# check against Borowski hand calcs dated 9/17/12
# define Orbits
LEO_407 = Orbit()
LEO_407.body = 'Earth'
LEO_407.apoapsis = 407
LEO_407.periapsis = 407
LEO_500 = Orbit()
LEO_500.body = 'Earth'
LEO_500.apoapsis = 500
LEO_500.periapsis = 500
LEO_700 = Orbit()
LEO_700.body = 'Earth'
LEO_700.apoapsis = 700
LEO_700.periapsis = 700
MEO = Orbit()
MEO.body = 'Mars'
MEO.apoapsis = 250
MEO.periapsis = 33840
HEEO = Orbit()
HEEO.body = 'Earth'
HEEO.apoapsis = 71136
HEEO.periapsis = 500
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (1), EOC into HEEO with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = HEEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.482, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (1), EOC into HEEO with Vinf = 5.882 km/s (from Apophis)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = HEEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 5.882**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -1.950, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (2), EOC into LEO_500 with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = LEO_500
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -3.187, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (2), EOC into LEO_407 with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = LEO_407
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -3.208, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (3), EOC into LEO_500 with Vinf = 5.882 km/s (from Apophis)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = LEO_500
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 5.882**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -4.655, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (3), EOC into LEO_407 with Vinf = 5.882 km/s (from Apophis)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = LEO_407
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 5.882**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -4.668, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12 (4), EOC into LEO_700 with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
maneuver = Maneuver()
maneuver.orbit = LEO_700
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -3.143, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12, EOC into 6 hour EEO with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
EEO = Orbit()
EEO.body = 'Earth'
EEO.apoapsis = 20238
EEO.periapsis = 500
# check the derivation of the 6hr orbit
self.logger.info(EEO.orbit_from_period(6*3600, 500))
maneuver = Maneuver()
maneuver.orbit = EEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -1.203, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12, EOC into 9 hour EEO with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
EEO = Orbit()
EEO.body = 'Earth'
EEO.apoapsis = 30633
EEO.periapsis = 500
# check the derivation of the 9hr orbit
self.logger.info('(calculated periapsis=%1.1f, apoapsis=%1.1f)' % EEO.orbit_from_period(9*3600, 500))
maneuver = Maneuver()
maneuver.orbit = EEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.914, 0.005)
self.logger.info('--------------------------------------------------------------------------------')
self.logger.info('SKB 9/17/12, EOC into 12 hour EEO with Vinf = 0.855 km/s (from 2000SG344)')
self.logger.info('--------------------------------------------------------------------------------')
EEO = Orbit()
EEO.body = 'Earth'
EEO.apoapsis = 39910
EEO.periapsis = 500
# check the derivation of the 9hr orbit
self.logger.info('(calculated periapsis=%1.1f, apoapsis=%1.1f)' % EEO.orbit_from_period(12*3600, 500))
maneuver = Maneuver()
maneuver.orbit = EEO
maneuver.maneuver_type = 'Capture at Periapsis'
maneuver.C3 = 0.855**2
dV = maneuver.calculate_dV()
assert_rel_error(self, dV, -0.755, 0.005)