def test_solar_torque_value(self): qBI = np.array([0.,0.,0.,1.]) wBIb = np.array([0.1,-0.02,-0.2]) v_pos_i = np.array([7070e3,0.,0.]) v_vel_i = np.array([0,2e3,6e3]) qBO = fs.qBI2qBO(qBI,v_pos_i,v_vel_i) wBOB = fs.wBIb2wBOb(wBIb,qBO,v_w_IO_o) sat = Satellite(np.hstack((qBO,wBOB)),13.) sat.setQ_BI(qBI) v_sv_i=np.array([1.0,0.0,0.0]) #sun vector in eci frame sat.setSun_i(v_sv_i) sat.setLight(1) dist.solarTorqueb(sat) result = sat.getsolarDisturbance_b() self.assertTrue(np.allclose(result,[ 0.00000000e+00,-3.66624000e-11,3.17376000e-10]))
def test_solar_torque_type(self): qBI = np.array([0.,0.,0.,1.]) wBIb = np.array([0.,0.,0.]) v_pos_i = np.array([7070e3,0.,0.]) v_vel_i = np.array([0,2e3,6e3]) qBO = fs.qBI2qBO(qBI,v_pos_i,v_vel_i) wBOB = fs.wBIb2wBOb(wBIb,qBO,v_w_IO_o) sat = Satellite(np.hstack((qBO,wBOB)),13.) sat.setQ_BI(qBI) sat.setPos(np.array([7070e3,0.,0.])) v_sv_i=np.array([1.0,0.0,0.0]) sat.setSun_i(v_sv_i) sat.setLight(1) dist.solarTorqueb(sat) result = sat.getsolarDisturbance_b() self.assertEqual(type(result),np.ndarray)
Advitiy.setLight(m_light_output[i * int(Nmodel / Ncontrol) + k, 1])
Advitiy.setSun_i(m_si_output_b[i * int(Nmodel / Ncontrol) + k,
1:4])
Advitiy.setMag_i(
m_magnetic_field_i[(i + 1) * int(Nmodel / Ncontrol) + k, 1:4])
# disturbance torque
if (distbool == 0):
# getting default disturbance torque (zero in our case)
Advitiy.setDisturbance_b(defblock.disturbance(Advitiy))
if (distbool == 1):
# getting disturbance torque by disturbance model
dist.ggTorqueb(Advitiy)
dist.aeroTorqueb(Advitiy)
dist.solarTorqueb(Advitiy)
torque_dist_gg[i * int(Nmodel / Ncontrol) +
k, :] = Advitiy.getggDisturbance_b()
torque_dist_aero[i * int(Nmodel / Ncontrol) +
k, :] = Advitiy.getaeroDisturbance_b()
torque_dist_solar[i * int(Nmodel / Ncontrol) +
k, :] = Advitiy.getsolarDisturbance_b()
torque_dist_total[
i * int(Nmodel / Ncontrol) +
k, :] = torque_dist_gg[i * int(Nmodel / Ncontrol) +
k, :] + torque_dist_aero[
i * int(Nmodel / Ncontrol) +
k, :] + torque_dist_solar[
i * int(Nmodel / Ncontrol) +
k, :]
for i in range(0, N - 1):
if math.fmod(i, N / 100) == 0 and i > 5:
print 100 * i / N
#Set satellite parameters
Advitiy.setLight(m_light_output[i, 1])
Advitiy.setState(m_state[i, :])
Advitiy.setTime(t0 + i * MODEL_STEP)
Advitiy.setPos(m_sgp_output_i[i, 1:4])
Advitiy.setVel(m_sgp_output_i[i, 4:7])
Advitiy.setSun_i(m_si_output_i[i, 1:4])
#calculate the disturbance torques
v_torque_gg_b = dist.ggTorqueb(Advitiy).copy()
v_torque_aero_b = dist.aeroTorqueb(Advitiy).copy()
v_torque_solar_b = dist.solarTorqueb(Advitiy).copy()
v_torque_total_b = (v_torque_gg_b + v_torque_aero_b + v_torque_solar_b)
Advitiy.setDisturbance_b(v_torque_total_b)
m_torque_dist[i, :] = v_torque_total_b.copy()
v_state_next = np.zeros((1, 7))
#Use rk4 solver to calculate the state for next step
for j in range(0, int(MODEL_STEP / h)):
v_state_next = sol.rk4Quaternion(Advitiy, x_dot, h)
Advitiy.setState(v_state_next.copy())
Advitiy.setTime(t0 + i * MODEL_STEP + (j + 1) * h)
m_state[i + 1, :] = v_state_next.copy()