#Test the data type of output

def test_gg_data_type(self):

sat = Satellite(np.array([1.,0.,0.,0.,0.,0.,0.]),13.)

sat.setPos(np.array([7070e3,0.,0.]))

result = dist.gg_torque(sat)

self.assertEqual(type(result),np.ndarray)

#Take position vector to be eigen vector of m_INERTIA along with q =[1,0,0,0] thus torque will be zero

l, w = np.linalg.eig(m_INERTIA)

@data(7070e3*w[:,0],7070e3*w[:,1],7070e3*w[:,2])

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)

print result

#test the data type of the output

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

#test the data type of the output

def test_solar_torque_type(self):

sat = Satellite(np.array([1.,0.,0.,0.,0.,0.,0.]),13.)

sat.setPos(np.array([7070e3,0.,0.]))

result = dist.gg_torque(sat)

self.assertEqual(type(result),np.ndarray)

def test_solar_torque_value(self):

state = np.array([1.,0.,0.,0.,0.1,-0.02,-0.2])

mySat = Satellite(state,128.05)

v_sv_i=np.array([1.0,0.0,0.0]) #sun vector in eci frame

mySat.setSun_i(v_sv_i)

result = dist.solar_torque(mySat)

print result