def set_coe(self, coe, units = None, rv = True):
if units != None:
from unit_conversions import converter
coe[2] = converter(coe[2], units, 'Radians')
coe[3] = converter(coe[3], units, 'Radians')
coe[4] = converter(coe[4], units, 'Radians')
coe[5] = converter(coe[5], units, 'Radians')
# reset coe
self.sma = coe[0]
self.e = coe[1]
self.i = coe[2]
self.RAAN = coe[3]
self.AOP = coe[4]
self.f = coe[5]
self.coe = [self.sma, self.e, self.i, self.RAAN, \
self.AOP, self.f]
# reset r, v
if rv:
from auxiliary import coe2rv
self.r, self.v = coe2rv(self.coe, self.Mu)
# recalculate additional useful orbital parameters
#+ E: eccentricy anomaly
#+ M: mean anomaly
#+ T: orbital period
#+ n: mean motion
from auxiliary import f2E, E2M, orbitalperiod
from math import pi
self.E = f2E(self.e, self.f)
self.M = E2M(self.e, self.E)
self.T = orbitalperiod(self.Mu, self.sma)
self.n = 2.0*pi / self.T
def set_e(self, e):
self.e = e
# reset e in coe list
self.coe[1] = e
# reset the r and v vectors
from auxiliary import coe2rv
self.r, self.v = coe2rv(self.coe, self.Mu)
# reset
#+ E: eccentricy anomaly
#+ M: mean anomaly
from auxiliary import f2E, E2M
self.E = f2E(self.e, self.f)
self.M = E2M(self.e, self.E)
def set_f(self, f, units = None):
if units != None:
from unit_conversions import converter
f = converter(f, units, 'Radians')
self.f = f
# reset f in coe list
self.coe[5] = f
# reset the r and v vectors
from auxiliary import coe2rv
self.r, self.v = coe2rv(self.coe, self.Mu)
# reset
#+ E: eccentricy anomaly
#+ M: mean anomaly
from auxiliary import f2E, E2M
self.E = f2E(self.e, self.f)
self.M = E2M(self.e, self.E)
def set_parameters(self, body, altitude = 400.0):
import solarsystem_objects_parameters as ss
# setup parameters for the requested body if available
# first see if the user is requesting the 'Earth' or
#+ if the body is not on the given list, then default
#+ to the 'Earth'
if body == 'earth' or body not in ss.list:
self.name = 'earth'
# default classical orbital elements is
#+ earth about sun
self.sma = ss.earth['SemiMajor']
self.e = ss.earth['Eccentricity']
self.i = ss.earth['Inclination']
self.RAAN = 0.0
self.AOP = 0.0
self.f = 0.0
# epoch (Julian Date), default January 3rd 2014
#+ which is roughly when the Earth is at periapsis
self.epoch = 2456660.500000 * 86400.0
# mass and mu of the body
self.mass = ss.earth['Mass']
self.mu = ss.earth['Mu']
# radius of body
self.radius = ss.earth['Radius']
# set the gravitational constant of 'self'
#+ central body
self.Mu = ss.sun['Mu']
if body == 'sun':
self.name = 'sun'
# default classical orbital elements is
#+ earth about sun
self.sma = 0.0
self.e = 0.0
self.i = 0.0
self.RAAN = 0.0
self.AOP = 0.0
self.f = 0.0
# epoch (Julian Date), default January 3rd 2014
#+ which is roughly when the Earth is at periapsis
self.epoch = 2456660.500000 * 86400.0
# mass and mu of the body
self.mass = ss.sun['Mass']
self.mu = ss.sun['Mu']
# radius of body
self.radius = ss.sun['Radius']
# set the gravitational constant of 'self'
#+ central body
self.Mu = ss.sun['Mu']
if body == 'moon':
self.name = 'moon'
# default classical orbital elements is
#+ earth about sun
self.sma = ss.moon['SemiMajor']
self.e = ss.moon['Eccentricity']
self.i = ss.moon['Inclination']
self.RAAN = 0.0
self.AOP = 0.0
self.f = 0.0
# epoch (Julian Date), default January 3rd 2014
#+ which is roughly when the Earth is at periapsis
self.epoch = 2456660.500000 * 86400.0
# mass and mu of the body
self.mass = ss.moon['Mass']
self.mu = ss.moon['Mu']
# radius of body
self.radius = ss.moon['Radius']
# set the gravitational constant of 'self'
#+ central body
self.Mu = ss.earth['Mu']
if body == 'mars':
self.name = 'mars'
# default classical orbital elements is
#+ earth about sun
self.sma = ss.mars['SemiMajor']
self.e = ss.mars['Eccentricity']
self.i = ss.mars['Inclination']
self.RAAN = 0.0
self.AOP = 0.0
self.f = 0.0
# epoch (Julian Date), default January 3rd 2014
#+ which is roughly when the Earth is at periapsis
self.epoch = 2456660.500000 * 86400.0
# mass and mu of the body
self.mass = ss.mars['Mass']
self.mu = ss.mars['Mu']
# radius of body
self.radius = ss.mars['Radius']
# set the gravitational constant of 'self'
#+ central body
self.Mu = ss.sun['Mu']
if body == 'LEO':
self.name = 'leo_spacecraft'
# default classical orbital elements is
#+ spacecraft about earth
from math import pi
self.sma = ss.earth['Radius'] + altitude
self.e = 0.0
self.i = 28.5 * pi / 180.0
self.RAAN = 0.0
self.AOP = 0.0
self.f = 0.0
# epoch (Julian Date), default January 3rd 2014
#+ which is roughly when the Earth is at periapsis
self.epoch = 2456660.500000 * 86400.0
# mass and mu of the body
self.mass = 1000.0
self.mu = 0.0
# set the gravitational constant of 'self'
#+ central body
self.Mu = ss.earth['Mu']
# place the classical orbital elements into an array
self.coe = [self.sma, self.e, self.i, self.RAAN, \
self.AOP, self.f]
# calculate the r, v vectors for 'self'
#+ based on the classical orbital elements 'coe'
from auxiliary import coe2rv
self.r, self.v = coe2rv(self.coe, self.Mu)
# calculate additional useful orbital parameters
#+ E: eccentricy anomaly
#+ M: mean anomaly
#+ T: orbital period
#+ n: mean motion
from auxiliary import f2E, E2M, orbitalperiod
from math import pi
self.E = f2E(self.e, self.f)
self.M = E2M(self.e, self.E)
self.T = orbitalperiod(self.Mu, self.sma)
self.n = 2.0*pi / self.T
