def test_appr_actTypeB(self, value):
torque_req = np.asarray(value[0])
magfield_b = np.asarray(value[1])
app_torque_exp = np.asarray(value[2])
vel = np.array([5, 6, 7])
pos = np.array([3, 4, 5])
q_BI = np.array([0.5, -0.5, 0.5, -0.5])
q_IB = quatInv(q_BI)
q_BO = qBI2qBO(q_BI, pos, vel)
magfield_i = quatRotate(q_IB, magfield_b)
w_BO_b = np.array([8, 6, 7])
state = np.hstack((q_BO, w_BO_b))
t0 = 0
s = sat.Satellite(state, t0)
s.setVel(vel)
s.setPos(pos)
s.setMag_i(magfield_i)
s.setControl_b(torque_req)
app_torque = act.actuatorTypeB(s)
self.assertTrue(np.allclose(app_torque, app_torque_exp))
def load_satellites(satellites_data_dicts):
"""
Loads the real satellites objects given a list of dictionnaries containing the parameters needed to
instanciate the satellites which has to be simulated
Input : a list of dictionnaries containing the parameters needed to instanciate the satellites which has to be simulated
"""
open("verif.txt", 'a').write("\n\n-------\n Satellites dict received : " +
str(satellites_data_dicts))
satellites_list = []
for satellite_dict in satellites_data_dicts:
for key, val in satellite_dict.items():
if (str(type(val)) == "<class 'list'>"):
satellite_dict[key] = np.array(val)
satellite_dict["corps_ref"] = [
body for body in c_b.CelestialBody.celestial_bodies
if body.name == satellite_dict["corps_ref"]
][0]
new_satellite = sat.Satellite(**satellite_dict)
sat.Satellite.satellites.append(new_satellite)
def test_gyroscope(self): qBO = np.array([.0,0.,0.,1.]) v_w_BI_b = np.array([-3.9999, 4.8575, 0]) v_w_BO_b = v_w_BI_b + qnv.quatRotate(qBO,v_w_IO_o) state = np.hstack((qBO,v_w_BO_b)) sat = satellite.Satellite(state,12.05) sat.setGyroVarBias(np.array((-0.1, 0.1, 0.1))) self.assertTrue(np.allclose(sensor.gyroscope(sat),np.array((-4.0999,4.9575,0.1))))
def test_J2_propagator(self): qBO = np.array([.0,0.,0.,1.]) state = np.hstack((qBO,np.array([-0.1,0.39159385,-0.7]))) sat = satellite.Satellite(state,12.05) sat.setPos(np.array([7070e3,0.,0.])) sat.setVel(np.array([5.60,-5.0,0.0])) v_expected = np.array([7070e3,0.,0.,5.60,-5.0,0.0,12.05]) self.assertTrue(np.allclose(defblock.J2_propagator(sat),v_expected))
def test_zero_torque_ideal_q(self):
mySat = satellite.Satellite(
np.array([1.0, 0., 0., 0., -0.1, 0.39, -0.7]), 12.05)
mySat.setPos(np.array([1e6, 53e5, 0.]))
mySat.setVel(np.array([5.60, -5.0, 0.0]))
mySat.setDisturbance_b(np.array([0., 0., 0.]))
mySat.setControl_b(np.array([0., 0., 0.]))
result = x_dot_BI(mySat, 12.06, mySat.getState())
self.assertTrue(np.allclose(2. * result[0:4], [0., -0.1, 0.39, -0.7]))
def createTrspFile(path):
# First of all load the trsp
print("Loading trsp")
trsps = json.load(
open(DATA["scripts_update_cache_dir"] +
DATA["scripts_update_trsp_file"]))
print("Getting category numbers")
trspcat = set()
for trsp in trsps:
trspcat.add(trsp['norad_cat_id'])
print("Filling satellite data")
satellites = []
numSats = 0
for file in DATA["scripts_update_files"]:
print("Extracting satellites from %s" % file)
f = open(DATA["scripts_update_cache_dir"] + file, 'r')
if int(DATA["scripts_update_linesneeded"]) == 3:
numSats = 0
i = 0
for line in f:
if i == 0: # Name of the sat
name = line.rstrip()
elif i == 1:
tle1 = line.rstrip()
elif i == 2:
tle2 = line.rstrip()
i += 1
if i == 3:
sat = satellite.Satellite(
name, file[:-4], tle1, tle2,
DATA["scripts_update_baseurl"] + file)
if sat.cat in trspcat:
for trsp in trsps:
if sat.cat == trsp['norad_cat_id']:
sat.addTrsp(trsp)
satellites.append(sat)
i = 0
numSats += 1
print("Extraction successful, imported %d satellites" % numSats)
f.close()
print("Collecting data, total %d satellites" % len(satellites))
def obj_dict(obj):
return obj.__dict__
print("Writing content to %s" %
(path + DATA["scripts_update_result_file"]))
with open(path + DATA["scripts_update_result_file"], 'w') as outfile:
json.dump(satellites, outfile, default=obj_dict)
print("Data was written successfully")
def test_kinematics_explicitly(self): qBO = np.array([0.254,-0.508,np.sqrt(1-0.4**2-0.254**2-0.508**2),0.4]) vel = np.array([5.60,-5.0,0.0]) state = np.hstack((qBO,np.array([0.10050588,-0.05026119,-0.3014887]))) mySat = satellite.Satellite(state,128.05) mySat.setVel(vel) mySat.setDisturbance_b(np.array([10e-10,-4e-6,-3e-5])) mySat.setControl_b(np.array([1e-5,1e-5,-8e-4])) result = x_dot_BO(mySat) self.assertTrue(np.allclose(result,[0.11475622, 0.06438473, -0.04115242, 0.08290271, 0.00632537, 0.00313621, -0.56264705]))
def test_currentToTorque(self,value): #converts control torque to voltage wiht help of earth's field
v_magnetic_field_i= np.asarray(value[1])
v_state=np.asarray(value[0])
v_current=np.asarray(value[4]) #first element should be time then next three are currents
mySat = satellite.Satellite(v_state,1.0)
mySat.setMag_i(v_magnetic_field_i)
torque = currentToTorque(v_current, mySat)
result= torque
self.assertTrue(np.allclose(result,np.asarray(value[5])))
def test_zero_torque_rates_ideal_q(
self): #zero torque, zero initial angular velocity, aligned frames
mySat = satellite.Satellite(np.array([1.0, 0., 0., 0., 0., 0., 0.]),
12.0)
mySat.setPos(np.array([1e6, 0., 0.]))
mySat.setVel(np.array([5.0, 5.0, 0.0]))
mySat.setDisturbance_b(np.array([0., 0., 0.]))
mySat.setControl_b(np.array([0., 0., 0.]))
result = x_dot_BI(mySat, 12.0, mySat.getState())
self.assertTrue(np.allclose(result, [0., 0., 0., 0., 0., 0., 0.]))
def test_inertia_eigenvec(self, value):
q = np.array([1., 0., 0., 0.])
mySat = satellite.Satellite(np.hstack((q, value)), 128.05)
mySat.setPos(np.array([1e6, 53e5, 0.]))
mySat.setVel(np.array([5.60, -5.0, 0.0]))
mySat.setDisturbance_b(np.array([0., 0., 0.]))
mySat.setControl_b(np.array([0., 0., 0.]))
result = x_dot_BI(mySat, 128.08, mySat.getState())
self.assertTrue(np.allclose(result[4:7], [0., 0., 0.]))
def test_zero_torque_ideal_q(self): #zero torque, random initial angular velocity, aligned frames qBO = np.array([.0,0.,0.,1.]) vel = np.array([5.60,-5.0,0.0]) state = np.hstack((qBO,np.array([-0.1,0.39159385,-0.7]))) mySat = satellite.Satellite(state,12.05) mySat.setVel(vel) mySat.setDisturbance_b(np.array([0.,0.,0.])) mySat.setControl_b(np.array([0.,0.,0.])) result = x_dot_BO(mySat) self.assertTrue(np.allclose(result,[-0.05,0.1957969257,-0.35, 0., 0.00453874, -0.00185081, -0.00168015]))
def test_ctrlTorqueToVoltage(self,value): #converts control torque to voltage wiht help of earth's field
v_magnetic_field_i= np.asarray(value[1])
v_state=np.asarray(value[0])
v_ctrlTorque=np.asarray(value[2])
mySat = satellite.Satellite(v_state,1.0)
mySat.setMag_i(v_magnetic_field_i)
mySat.setControl_b(v_ctrlTorque)
voltage = ctrlTorqueToVoltage(mySat)
result= voltage
self.assertTrue(np.allclose(result, np.asarray(value[3])))
def test_constant(self): t0 = 0.0 mySat = satellite.Satellite(np.array([1.0,0.,0.,0.,0.,0.,0.]),t0) t = 10 mySat.setPos(np.array([1e6,0.,0.])) mySat.setVel(np.array([5.0,5.0,0.0])) h = 0.1 for i in range(0,int(t/h)): updateStateTimeRK4(mySat,f_constant,h) mySat.setTime(t0+(i+1)*h) self.assertTrue(np.allclose([10.0,10.0,10.0],mySat.getW_BO_b()))
def test_GPS(self): qBO = np.array([.0,0.,0.,1.]) v_w_BI_b = np.array([-3.9999, 4.8575, 0]) v_w_BO_b = v_w_BI_b + qnv.quatRotate(qBO,v_w_IO_o) state = np.hstack((qBO,v_w_BO_b)) sat = satellite.Satellite(state,3.132) v_pos_i = np.array([5000,5000,6000]) v_vel_i = np.array([7e3,0,0]) sat.setPos(v_pos_i) sat.setVel(v_vel_i) result=sensor.GPS(sat) self.assertTrue(np.allclose(result,np.array((5000,5000,6000,7e3,0,0,3.132))))
def test_dynamics(self,value): t0 = 0. h = value v_q_BO = np.array([0.4,0.254,-0.508,0.71931912]) v_w_BO_b = frames.wBIb2wBOb(np.array([0.1,-0.05,-0.3]),v_q_BO,v_w_IO_o) mySat1 = satellite.Satellite(np.hstack((v_q_BO, v_w_BO_b)),t0) mySat1.setPos(np.array([1e6,53e5,0.])) mySat1.setVel(np.array([5.60,-5.0,0.0])) mySat1.setDisturbance_b(np.array([10e-10,-4e-6,-3e-5])) mySat1.setControl_b(np.array([1e-5,1e-5,-8e-4])) updateStateTimeRK4(mySat1,x_dot_BO,h) x1 = mySat1.getState() mySat2 = satellite.Satellite(np.hstack((v_q_BO, v_w_BO_b)),t0) mySat2.setPos(np.array([1e6,53e5,0.])) mySat2.setVel(np.array([5.60,-5.0,0.0])) mySat2.setDisturbance_b(np.array([10e-10,-4e-6,-3e-5])) mySat2.setControl_b(np.array([1e-5,1e-5,-8e-4])) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))) k1 = h*x_dot_BO(mySat2) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))+0.5*k1) k2 = h*x_dot_BO(mySat2) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))+0.5*(k2)) k3 = h*x_dot_BO(mySat2) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))+k3) k4 = h*x_dot_BO(mySat2) error_state = np.hstack((v_q_BO,v_w_BO_b)) + (1./6.)*(k1 + 2.*k2 + 2.*k3 + k4) if (error_state[3]<0): error_state[0:4]=-1*error_state[0:4] error_state[0:4]=error_state[0:4]/np.linalg.norm(error_state[0:4]) self.assertTrue(np.allclose(error_state,x1))
def test_kinematics_explicitly(self):
state = np.array([
0.4, 0.254, -0.508,
np.sqrt(1 - 0.4**2 - 0.254**2 - 0.508**2), 0.1, -0.05, -0.3
])
mySat = satellite.Satellite(state, 128.05)
mySat.setPos(np.array([1e6, 53e5, 0.]))
mySat.setVel(np.array([5.60, -5.0, 0.0]))
mySat.setDisturbance_b(np.array([10e-10, 0., 0.]))
mySat.setControl_b(np.array([1e-5, 0., 0.]))
result = x_dot_BI(mySat, 128.08, mySat.getState())
self.assertTrue(
np.allclose(result[0:4], [0.082498, 0.114183, 0.064066, -0.04095]))
def test_magmeter(self, value):
qBI = np.asarray(value[0])
v_sv_i = np.asarray(value[1])
v_pos_i = np.array([1e6, -2.03, -3.0])
v_vel_i = np.array([2.0e3, 2.8, -73.2])
qBO = frames.qBI2qBO(qBI, v_pos_i, v_vel_i)
state = np.hstack((qBO, np.zeros(3)))
mySat = satellite.Satellite(state, 12.0)
mySat.setQ_BI(qBI)
result = defblock.magmeter(mySat, v_sv_i)
v_expected = value[2], value[3]
self.assertTrue(np.allclose(result, v_expected))
def test_magnetometer(self): qBO = np.array([.0,0.,0.,1.]) v_w_BI_b = np.array([-3.9999, 4.8575, 0]) v_w_BO_b = v_w_BI_b + qnv.quatRotate(qBO,v_w_IO_o) state = np.hstack((qBO,v_w_BO_b)) sat = satellite.Satellite(state,12.05) v_pos_i = np.array([1e6,-2.03,-3.0]) v_vel_i = np.array([2.0e3,2.8,-73.2]) sat.setPos(v_pos_i) sat.setVel(v_vel_i) qOI = np.array([-0.70697614, -0.01353643, 0.70697824, 0.01353791]) Magi = qnv.quatRotate(qnv.quatInv(qOI),np.array((2.3e-6,3.4e-6,3.1e-6))) sat.setMag_i(Magi) self.assertTrue(np.allclose(sensor.magnetometer(sat),np.array((2.3e-6,3.4e-6,3.1e-6))))
def test_ramp1(self):
t0 = 0.
mySat = satellite.Satellite(np.array([1.0, 0., 0., 0., 0., 0., 0.]),
t0)
t = 10
h = 0.1
for i in range(0, int(t / h)):
x1 = rk4(mySat, f_ramp, h)
mySat.setState(x1.copy())
mySat.setTime(t0 + (i + 1) * h)
self.assertTrue(
np.allclose([51.0, 50.0, 50.0, 50.0, 50.0, 50.0, 50.0],
mySat.getState()))
def test_Bdot(self, value):
mag1 = np.asarray(value[0])
mag2 = np.asarray(value[1])
mag_exp = np.asarray(value[2])
iniState = np.array([1., 0., 0., 0., 0., 0., 0.])
s = sat.Satellite(iniState, 0)
s.setMag_b_m_p(mag1)
s.setMag_b_m_c(mag2)
detcon.cons.k = 0.004252756437794863
magMoment = detcon.magMoment(s)
#print magMoment
self.assertTrue(np.allclose(magMoment, mag_exp))
def test_dynamics(self): t0 = 0. h = 0.001 v_q_BO = np.array([0.4,0.254,-0.508,0.71931912]) v_w_BO_b = frames.wBIb2wBOb(np.array([0.1,-0.05,-0.3]),v_q_BO,v_w_IO_o) mySat1 = satellite.Satellite(np.hstack((v_q_BO, v_w_BO_b)),t0) mySat1.setPos(np.array([1e6,53e5,0.])) mySat1.setVel(np.array([5.60,-5.0,0.0])) mySat1.setDisturbance_b(np.array([10e-10,-4e-6,-3e-5])) mySat1.setControl_b(np.array([1e-5,1e-5,-8e-4])) rk4Quaternion(mySat1,x_dot_BO,h) x1 = mySat1.getState() mySat2 = satellite.Satellite(np.hstack((v_q_BO, v_w_BO_b)),t0) mySat2.setPos(np.array([1e6,53e5,0.])) mySat2.setVel(np.array([5.60,-5.0,0.0])) mySat2.setDisturbance_b(np.array([10e-10,-4e-6,-3e-5])) mySat2.setControl_b(np.array([1e-5,1e-5,-8e-4])) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))) k1 = h*x_dot_BO(mySat2) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))+0.5*k1) k2 = h*x_dot_BO(mySat2) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))+0.5*(k2+k1)) k3 = h*x_dot_BO(mySat2) mySat2.setState(np.hstack((v_q_BO,v_w_BO_b))+k3+0.5*(k2+k1)) k4 = h*x_dot_BO(mySat2) error_state = np.hstack((v_q_BO,v_w_BO_b)) + (1./6.)*(k1 + 2.*k2 + 2.*k3 + k4) print(error_state) self.assertTrue(np.allclose(error_state,x1))
def test_magmeter(self,value): qBI = np.asarray(value[0]) v_B_i=np.asarray(value[1]) v_pos_i = np.array([1e6,-2.03,-3.0]) v_vel_i = np.array([2.0e3,2.8,-73.2]) qBO = frames.qBI2qBO(qBI,v_pos_i,v_vel_i) state = np.hstack((qBO,np.zeros(3))) mySat = satellite.Satellite(state,12.0) mySat.setMag_i(v_B_i) mySat.setPos(v_pos_i) mySat.setVel(v_vel_i) qOI = qnv.quatMultiplyNorm(qnv.quatInv(qBO),qBI) result = defblock.magnetometer(mySat) v_expected = value[2]; self.assertTrue(np.allclose(result,v_expected))
def test_ramp2(self):
t0 = 0.
mySat = satellite.Satellite(
np.array([0.5, 0.5, -0.5, -0.5, 1.6, -2.5, 0.3]), t0)
t = 10.
h = 0.1
for i in range(0, int(t / h)):
x1 = rk4(mySat, f_ramp, h)
mySat.setState(x1.copy())
mySat.setTime(t0 + (i + 1) * h)
self.assertTrue(
np.allclose([50.5, 50.5, 49.5, 49.5, 51.6, 47.5, 50.3],
mySat.getState()))
def test_tx(self):
t0 = 0.
mySat = satellite.Satellite(
np.array([0.5, 0.5, -0.5, -0.5, 1.6, -2.5, 0.3]), t0)
t = 3.
h = 0.001
for i in range(0, int(t / h)):
x1 = rk4(mySat, f_tx, h)
mySat.setState(x1.copy())
mySat.setTime(t0 + (i + 1) * h)
expected = np.exp(-t**2 / 2.) * np.array(
[0.5, 0.5, -0.5, -0.5, 1.6, -2.5, 0.3])
self.assertTrue(np.allclose(expected, mySat.getState()))
def test_sunsensor(self): qBO = np.array([.0,0.,0.,1.]) v_w_BI_b = np.array([-3.9999, 4.8575, 0]) v_w_BO_b = v_w_BI_b + qnv.quatRotate(qBO,v_w_IO_o) state = np.hstack((qBO,v_w_BO_b)) sat = satellite.Satellite(state,12.05) v_pos_i = np.array([1e6,-2.03,-3.0]) v_vel_i = np.array([2.0e3,2.8,-73.2]) sat.setPos(v_pos_i) sat.setVel(v_vel_i) qOI = np.array([-0.70697614, -0.01353643, 0.70697824, 0.01353791]) Suni = qnv.quatRotate(qnv.quatInv(qOI),np.array((3,4,5))) sat.setSun_i(Suni) result = sensor.sunsensor(sat) expected = np.array((3/(50**(0.5)),4/(50**(0.5)),5/(50**(0.5)))) self.assertTrue(np.allclose(result,expected))
def test_zero_torque_ideal_q(
self
): #zero torque, random initial angular velocity, aligned frames
qBO = np.array([1.0, 0., 0., 0.])
pos = np.array([1e6, 53e5, 0.])
vel = np.array([5.60, -5.0, 0.0])
state = np.hstack((qBO, np.array([-0.1, 0.39159385, -0.7])))
mySat = satellite.Satellite(state, 12.05)
mySat.setPos(pos)
mySat.setVel(vel)
mySat.setDisturbance_b(np.array([0., 0., 0.]))
mySat.setControl_b(np.array([0., 0., 0.]))
result = x_dot_BO(mySat, 12.06, mySat.getState())
self.assertTrue(
np.allclose(result, [
0., -0.05, 0.1957969257, -0.35, 0.00490396, -0.00185206,
-0.00173161
]))
def test_dynamics(self):
t0 = 0.
h = 0.001
v_q_BO = np.array([0.4, 0.254, -0.508, 0.71931912])
v_q_BI = frames.qBO2qBI(v_q_BO, np.array([1e6, 53e5, 0.]),
np.array([5.60, -5.0, 0.0]))
mySat = satellite.Satellite(
np.hstack((v_q_BI, np.array([0.1, -0.05, -0.3]))), t0)
mySat.setPos(np.array([1e6, 53e5, 0.]))
mySat.setVel(np.array([5.60, -5.0, 0.0]))
mySat.setDisturbance_b(np.array([10e-10, -4e-6, -3e-5]))
mySat.setControl_b(np.array([1e-5, 1e-5, -8e-4]))
r = np.linalg.norm(mySat.getPos())
v_w_IO_o = np.array([
0., np.sqrt(G * M_EARTH / (r)**3), 0.
]) #angular velocity of orbit frame wrt inertial frame in orbit frame
v_w_BO_b = frames.wBIb2wBOb(np.array([0.1, -0.05, -0.3]), v_q_BO,
v_w_IO_o)
x1 = rk4Quaternion(mySat, x_dot_BO, h)
mySat.setState(x1.copy())
mySat.setTime(t0 + h)
k1 = h * x_dot_BO(mySat, t0 + 0.5 * h, np.hstack((v_q_BO, v_w_BO_b)))
k2 = h * x_dot_BO(mySat, t0 + 0.5 * h,
np.hstack((v_q_BO, v_w_BO_b)) + 0.5 * k1)
k3 = h * x_dot_BO(mySat, t0 + 0.5 * h,
np.hstack((v_q_BO, v_w_BO_b)) + 0.5 * k2)
k4 = h * x_dot_BO(mySat, t0 + h, np.hstack((v_q_BO, v_w_BO_b)) + k3)
error_state = np.hstack(
(v_q_BO, v_w_BO_b)) + (1. / 6.) * (k1 + 2. * k2 + 2. * k3 + k4)
expected = np.hstack((frames.qBO2qBI(error_state[0:4],
np.array([1e6, 53e5, 0.]),
np.array([5.60, -5.0, 0.0])),
frames.wBOb2wBIb(error_state[4:7],
error_state[0:4], v_w_IO_o)))
self.assertTrue(np.allclose(expected, mySat.getState()))
def test_kinematics_explicitly(self):
qBO = np.array(
[0.4, 0.254, -0.508,
np.sqrt(1 - 0.4**2 - 0.254**2 - 0.508**2)])
pos = np.array([1e6, 53e5, 0.])
vel = np.array([5.60, -5.0, 0.0])
state = np.hstack((qBO, np.array([0.10050588, -0.05026119,
-0.3014887])))
mySat = satellite.Satellite(state, 128.05)
mySat.setPos(pos)
mySat.setVel(vel)
mySat.setDisturbance_b(np.array([10e-10, -4e-6, -3e-5]))
mySat.setControl_b(np.array([1e-5, 1e-5, -8e-4]))
result = x_dot_BO(mySat, 128.08, mySat.getState())
print(result)
self.assertTrue(
np.allclose(result, [
0.08290271, 0.11475622, 0.06438473, -0.04115242, 0.00627683,
0.00299226, -0.56264081
]))
def test_zero_torque_rates_ideal_q(self): #zero torque, zero initial wBIB, aligned frames ''' For this test case set (from sixth model of Advitiy) and ALTITUDE = 700 km Ixx = 0.00152529 Iyy = 0.00145111 Izz = 0.001476 Ixy = 0.00000437 Iyz = - 0.00000408 Ixz = 0.00000118 ''' qBO = np.array([0.0,0.,0.0,1.]) vel = np.array([5.0,5.0,0.0]) v_w_BI_b = np.array([0.,0.,0.]) v_w_BO_b = frames.wBIb2wBOb(v_w_BI_b,qBO,v_w_IO_o) state = np.hstack((qBO,v_w_BO_b)) mySat = satellite.Satellite(state,12.0) mySat.setVel(vel) mySat.setDisturbance_b(np.array([0.,0.,0.])) mySat.setControl_b(np.array([0.,0.,0.])) result = x_dot_BO(mySat) self.assertTrue(np.allclose(result,[0.,0.00053089,0.,0.,0.,0.,0.]))
def save(self):
# capture every entry made by the user
name = self.nameBox.get()
upFreq = self.upFreqBox.get()
downFreq = self.downFreqBox.get()
owner = self.boxOwner.get()
modulation = self.boxModulation.get()
#verify if all the information is here
if name == "" or upFreq == 0 or downFreq == 0 or owner == "" or modulation == "":
self.errortext.set("all fields must be filled!")
else:
try:
if float(upFreq) > 500 or float(upFreq) < 100 or float(
downFreq) > 500 or float(downFreq) < 100:
self.errortext.set("Frequencies not in range")
else:
#saves the satellite in the database
sat = satellite.Satellite(name=name,
upFreq=upFreq,
downFreq=downFreq,
upBand="UHF",
downBand="VHF",
owner=owner,
modulation=modulation)
sat.saveInDB()
#save the TLE in predict TLE
TLEDB = open("/home/simon/.predict/predict.tle", 'a')
newTLE = '\n' + name + "\n" + self.boxTLE.get(
) + "\n" + self.boxTLE2.get()
TLEDB.write(newTLE)
# quit the window without closing the program
self.master.destroy()
except ValueError:
self.errortext.set("frequencies should be numbers")
