def test_check_pos_vel_transformation(self):
r = np.array([1e6, -2.03, -3.0])
v = np.array([2.0e3, 2.8, -73.2])
self.assertTrue(
np.allclose(fr.ecif2orbit(r, v, r),
[0., 0., -1 * np.linalg.norm(r)]))
self.assertTrue(
np.allclose(fr.ecif2orbit(r, v, np.cross(v, r)),
[0., np.linalg.norm(np.cross(v, r)), 0.]))
def test_e2o_matrix_orthogonality(self, value):
r = np.asarray(value[0:3])
v = np.asarray(value[3:6])
v_x = fr.ecif2orbit(r, v, np.array([1.0, 0.0, 0.0]))
v_y = fr.ecif2orbit(r, v, np.array([0.0, 1.0, 0.0]))
v_z = fr.ecif2orbit(r, v, np.array([0.0, 0.0, 1.0]))
self.assertEqual(type(v_z), np.ndarray)
m = np.array([v_x, v_y, v_z])
mT = m.transpose()
I = np.dot(m, mT)
self.assertTrue(np.allclose(I[0, :], [1., 0., 0.]))
self.assertTrue(np.allclose(I[1, :], [0., 1., 0.]))
self.assertTrue(np.allclose(I[2, :], [0., 0., 1.]))
def getSun_o(self): #get sun vector in orbit v_sun_o = fs.ecif2orbit(self.v_pos_i,self.v_vel_i,self.v_sun_i) return v_sun_o
def getMag_o(self): #return mag in orbit v_mag_o = fs.ecif2orbit(self.v_pos_i,self.v_vel_i,self.v_mag_i) return v_mag_o
Sat4.setMag_i(arr3)
mag_i=Sat4.getMag_i()
if (mag_i==arr3).all():
print ("setMag_i and getMag_i correct")
else:
print ("setMag_i and getMag_i incorrect")
#Case 1 velocity and position are integer
Sat4.setPos(arr1)
v_Pos_i=Sat4.getPos()
Sat4.setVel(arr2)
v_vel_i=Sat4.getVel()
a=Sat4.getSun_o()
b=fs.ecif2orbit(v_Pos_i,v_vel_i,w)
if (a==b).all():
print ("getSun_o correct")
else:
print ("getSun_o incorrect")
#Case 2 velocity integer and position float
Sat4.setPos(arr3)
v_Pos_i=Sat4.getPos()
Sat4.setVel(arr2)
v_vel_i=Sat4.getVel()
a=Sat4.getSun_o()
b=fs.ecif2orbit(v_Pos_i,v_vel_i,w)
if (a==b).all():
Rz = np.array([[math.cos(z), math.sin(-z), 0.0],
[math.sin(z), math.cos(z), 0.0], [0.0, 0.0, 1.0]])
R_orbit2body = Rx.dot(Ry).dot(Rz)
for i in range(N):
#setting time
advitiy.setTime(T[i])
dt = T[1] - T[0]
#getting light, sun vector, position, velocity from csv files
light = light_output[i, 1]
v_sun_i = si_output[i, 1:4].copy()
v_pos_i = sgp_output[i, 1:4].copy()
v_vel_i = sgp_output[i, 4:7].copy()
#calculating sun vector body and orbit frame
v_sun_o = f.ecif2orbit(v_pos_i, v_vel_i, v_sun_i)
v_sun_b = R_orbit2body.dot(v_sun_o)
#setting attributes to satellite
advitiy.setPos(v_pos_i)
advitiy.setVel(v_vel_i)
advitiy.setSun_i(v_sun_i)
#advitiy.setSun_o(v_sun_o)
advitiy.setSun_b_m(v_sun_b)
advitiy.setLight(light)
power_arr = pow.power(advitiy)
#energy=energy+power_arr[6]*dt
energy_output[j, 0] = j
energy_output[j, 1] = energy_output[
j, 1] + power_arr[0] * dt #for each side:x,-x,y,-y,z,-z
def getSatMag_o(self): #return mag in orbit
v_sat_mag_o = fs.ecif2orbit(self.J2Data[0:3], self.J2Data[3:6],
self.v_mag_i)
return v_sat_mag_o
def getSatSun_o(self): #get sun vector in orbit
v_sat_sun_o = fs.ecif2orbit(self.J2Data[0:3], self.J2Data[3:6],
self.v_sun_i)
return v_sat_sun_o
