HajimeKawahara

HajimeKawahara

    from numpy.polynomial.legendre import legval
    import numpy as np
    import matplotlib.pyplot as	plt
    coeff=np.array([[1.0,2.0,0.2,0.3],[1.0,1.0,0.2,0.7]]).T
    print("coeff shape",np.shape(coeff))
    x=np.linspace(-1.0,1.0,100)
    f=legval(x, coeff, tensor=True)
    print("Lugendre shape",np.shape(f))
    for i in range(0,2):
        plt.plot(x,f[i,:])

HajimeKawahara

    import pkg_resources                                                                                                
    filename="data/mockalbedo"+str(nside)+".fits"
    fitsfile=(pkg_resources.resource_filename('jaxsot', filename))
    mmap=(hp.read_map(fitsfile))

HajimeKawahara

import sys
import argparse
import numpy as np
from astropy import constants as const
from astropy import units as u

def Blambda(T,lamb):
    lamb5=(lamb.to(u.m))**5    
    fac=const.h*const.c/(lamb.to(u.m)*const.k_B*T)
    bl=2.0*(const.c**2)*const.h/lamb5/(np.exp(fac)-1)

HajimeKawahara

import sys
import argparse
import numpy as np
from astropy import constants as const
from astropy import units as u

def Blambda(T,lamb):
    lamb5=(lamb.to(u.m))**5    
    fac=const.h*const.c/(lamb.to(u.m)*const.k_B*T)
    bl=2.0*(const.c**2)*const.h/lamb5/(np.exp(fac)-1)

HajimeKawahara

%General Mission Analysis Tool(GMAT) Script
%Created: 2021-01-22 15:04:08


%----------------------------------------
%---------- Spacecraft
%----------------------------------------

Create Spacecraft Spacecraft;
GMAT Spacecraft.DateFormat = UTCModJulian;

HajimeKawahara

import numpy as np

#compute angular separation [deg] by Vinsenty method
#input [deg deg deg deg]

def sepfast_Vinsenty(ra1,dec1,ra2,dec2):
    fac=np.pi/180.0
    rax1=ra1*fac
    decx1=dec1*fac
    rax2=ra2*fac

HajimeKawahara

HajimeKawahara

HajimeKawahara