def test_aero(self):
sat = Satellite(
np.array([np.sqrt(0.5), -np.sqrt(0.5), 0., 0., 0.1, 0.23, 0.]),
13.)
sat.setPos(np.array([0., 0., 7e6]))
sat.setVel(np.array([0, 2e3, 6e3]))
result = dist.aero_torque(sat)
print result
def test_inertia_eigenvec(self, value):
state = np.array([1., 0., 0., 0., 0.1, -0.02, -0.2])
mySat = Satellite(state, 128.05)
mySat.setPos(value)
mySat.setVel(np.array([5.60, -5.0, 0.0]))
result = dist.gg_torque(mySat)
self.assertTrue(np.allclose(result, [0., 0., 0.]))
def test_aero_type(self):
sat = Satellite(
np.array([np.sqrt(0.5), -np.sqrt(0.5), 0., 0., 0.1, 0.23, 0.]),
13.)
sat.setPos(np.array([0., 0., 7e6]))
sat.setVel(np.array([0, 2e3, 6e3]))
result = dist.aero_torque(sat)
self.assertEqual(type(result), np.ndarray)
def test_aero_value(self):
sat = Satellite(
np.array([np.sqrt(0.5), -np.sqrt(0.5), 0., 0., 0.1, 0.23, 0.]),
13.)
sat.setPos(np.array([0., 0., 7e6]))
sat.setVel(np.array([0, 2e3, 6e3]))
result = dist.aero_torque(sat)
print result
self.assertTrue(
np.allclose(result,
[2.99654080e-10, -2.57065600e-11, -7.71196800e-11]))
def test_aero_type(self):
qBI = np.array([-np.sqrt(0.5), 0., 0., np.sqrt(0.5)])
wBIb = np.array([0.1, 0.23, 0.])
v_pos_i = np.array([0., 0., 7e6])
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.setPos(np.array([0., 0., 7e6]))
sat.setVel(np.array([0, 2e3, 6e3]))
dist.aeroTorqueb(sat)
result = sat.getaeroDisturbance_b()
self.assertEqual(type(result), np.ndarray)
def test_inertia_eigenvec(self, value):
qBI = np.array([0., 0., 0., 1.])
wBIb = np.array([0.1, -0.02, -0.2])
v_pos_i = value
v_vel_i = np.array([5.60, -5.0, 0.0])
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.setPos(value)
sat.setVel(v_vel_i)
dist.ggTorqueb(sat)
result = sat.getggDisturbance_b()
self.assertTrue(np.allclose(result, [0., 0., 0.]))
def test_gg_data_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([2.0e3, 2.8, -73.2])
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.setPos(np.array([7070e3, 0., 0.]))
sat.setVel(v_vel_i)
dist.ggTorqueb(sat)
result = sat.getggDisturbance_b()
self.assertEqual(type(result), np.ndarray)
def test_aero_value(self): qBI = np.array([-np.sqrt(0.5),0.,0.,np.sqrt(0.5)]) wBIb = np.array([0.1,0.23,0.]) v_pos_i = np.array([0.,0.,7e6]) 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([0.,0.,7e6])) sat.setVel(np.array([0,2e3,6e3])) dist.aeroTorqueb(sat) result = sat.getaeroDisturbance_b() self.assertTrue(np.allclose(result, [2.99654080e-10,-2.57065600e-11,-7.71196800e-11]))
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.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)
sat.setPos(v_pos_i)
sat.setVel(v_vel_i)
dist.solarTorqueb(sat)
result = sat.getsolarDisturbance_b()
self.assertEqual(type(result), np.ndarray)
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.)
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)
sat.setPos(v_pos_i)
sat.setVel(v_vel_i)
dist.solarTorqueb(sat)
result = sat.getsolarDisturbance_b()
self.assertTrue(
np.allclose(result,
[0.00000000e+00, -3.66624000e-11, 3.17376000e-10]))