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_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]))
