def VGP():
Direction_Vector = np.array([1, 1, 1])
HPOP_Results = joblib.load('Result_data/data_6.pkl')
x = HPOP_Results[1, :]
y = HPOP_Results[2, :]
z = HPOP_Results[3, :]
time = HPOP_Results[0, :]
position = np.row_stack((x, y))
position = np.row_stack((position, z))
Step_Size = 100
Number_Of_Steps = 8000
year = 2008
month = 1
day = 1
hour = 12
minute = 0
second = 0
length = Number_Of_Steps # 设置步长
# 生成长度为60的数组,要打1.0因为数组数据类型要为float，输入1则默认类型为int
timeJD = np.arange(0, length, 1)
Visibility = np.arange(0, length, 1)
JD_Start = Julian_date(year, month, day, hour, minute, second)
for i in range(0, length): # 0~59,没有60
timeJD[i] = JD_Start + i * Step_Size / 86400
Visibility[i] = Visibility_for_celestial_body(Direction_Vector,
position[:,
i], timeJD[i])
# plt.plot(time, Visibility)
# # plt.show()
Visibility_Star = np.row_stack((time, Visibility))
joblib.dump(Visibility_Star, 'Result_data/Visibility_Star_6.pkl')
# 加载x
# x = joblib.load('x.pkl')
np.savetxt('Result_data/Visibility_Star_6.csv',
Visibility_Star,
delimiter=',')
def GSAT():
Longitude = 121.368
Latitude = 31.1094
MAX_ElevationAngle = 45
Altitude = 0
HPOP_Results = joblib.load('Result_data/data_6.pkl')
x = HPOP_Results[1, :]
y = HPOP_Results[2, :]
z = HPOP_Results[3, :]
time = HPOP_Results[0, :]
# Start_Time = joblib.load('Start_Time.pkl')
year = 2008
month = 1
day = 1
hour = 12
minute = 0
second = 0
t_start_jd = Julian_date(year, month, day, hour, minute, second)
MJD_UTC_Start = t_start_jd - 2400000.5
Visibility_GS_SAT = []
# np.arange(0, len(time), 1)
i = 0
for t in time:
Visibility_GS_SAT.append(
GSA(np.array([x[i], y[i], z[i]]), t, Latitude, Longitude, Altitude,
MAX_ElevationAngle, MJD_UTC_Start))
i = i + 1
Visibility_GS_SAT = np.row_stack((time, Visibility_GS_SAT))
joblib.dump(Visibility_GS_SAT, 'Result_data/Visibility_GS_SAT_6.pkl')
# 加载x
# x = joblib.load('x.pkl')
np.savetxt('Result_data/Visibility_GS_SAT_6.csv',
Visibility_GS_SAT,
delimiter=',')
def run_Ob(self):
Direction_Vector = self.value_get()
HPOP_Results = joblib.load('HPOP_Results.pkl')
x = HPOP_Results[1, :]
y = HPOP_Results[2, :]
z = HPOP_Results[3, :]
time = HPOP_Results[0, :]
position = np.row_stack((x, y))
position = np.row_stack((position, z))
Start_Time = joblib.load('Start_Time.pkl')
Step_Size = joblib.load('Step_Size.pkl')
Number_Of_Steps = joblib.load('Number_Of_Steps.pkl')
year = Start_Time[5]
month = Start_Time[4]
day = Start_Time[3]
hour = Start_Time[2]
minute = Start_Time[1]
second = Start_Time[0]
length = Number_Of_Steps # 设置步长
# 生成长度为60的数组,要打1.0因为数组数据类型要为float，输入1则默认类型为int
timeJD = np.arange(0, length, 1)
Visibility = np.arange(0, length, 1)
JD_Start = Julian_date(year, month, day, hour, minute, second)
for i in range(0, length): # 0~59,没有60
timeJD[i] = JD_Start + i * Step_Size / 86400
Visibility[i] = Visibility_for_celestial_body(
Direction_Vector, position[:, i], timeJD[i])
joblib.dump(time, 'time.pkl')
joblib.dump(Visibility, 'Visibility.pkl')
return
def run_Ob(self):
Longitude, Latitude, MAX_ElevationAngle, Altitude = self.value_get()
HPOP_Results = joblib.load('HPOP_Results.pkl')
x = HPOP_Results[1, :]
y = HPOP_Results[2, :]
z = HPOP_Results[3, :]
time = HPOP_Results[0, :]
Start_Time = joblib.load('Start_Time.pkl')
year = Start_Time[5]
month = Start_Time[4]
day = Start_Time[3]
hour = Start_Time[2]
minute = Start_Time[1]
second = Start_Time[0]
t_start_jd = Julian_date(year, month, day, hour, minute, second)
MJD_UTC_Start = t_start_jd - 2400000.5
Visibility_GS_SAT = []
# np.arange(0, len(time), 1)
i = 0
for t in time:
Visibility_GS_SAT.append(
GSA(np.array([x[i], y[i], z[i]]), t, Latitude, Longitude,
Altitude, MAX_ElevationAngle, MJD_UTC_Start))
i = i + 1
joblib.dump(time, 'time.pkl')
joblib.dump(Visibility_GS_SAT, 'Visibility_GS_SAT.pkl')
return
def HPOP(Start_Time, Number_of_Steps, Step_Size, Initial_Orbit_Elements):
#Load basic data
# Start_time, Number_of_Steps, Step, Initial_Orbit_Elements
year = Start_Time[5]
month = Start_Time[4]
day = Start_Time[3]
hour = Start_Time[2]
minute = Start_Time[1]
second = Start_Time[0]
t_start_jd = Julian_date(year, month, day, hour, minute, second)
orbit_element = Initial_Orbit_Elements #输入角度单位为度°
r0, v0 = orbit_element_to_rv(orbit_element)
Y0 = np.array([
r0[0] * 1e3, r0[1] * 1e3, r0[2] * 1e3, v0[0] * 1e3, v0[1] * 1e3,
v0[2] * 1e3
]) #Y0单位为m,m/s
Mjd_UTC = t_start_jd - 2400000.5
Global_parameters.AuxParam['Mjd_UTC'] = Mjd_UTC
Global_parameters.AuxParam['n'] = 10
Global_parameters.AuxParam['m'] = 10
Global_parameters.AuxParam['sun'] = 0
Global_parameters.AuxParam['moon'] = 0
Global_parameters.AuxParam['planets'] = 0
Global_parameters.AuxParam['sRad'] = 0
Global_parameters.AuxParam['drag'] = 0
Global_parameters.AuxParam['SolidEarthTides'] = 0
Global_parameters.AuxParam['OceanTides'] = 0
Global_parameters.AuxParam['Relativity'] = 0
Global_parameters.AuxParam['Cr'] = 1.0
Global_parameters.AuxParam['Cd'] = 4
Global_parameters.AuxParam['mass'] = 8000
Global_parameters.AuxParam['area_drag'] = 62.5
Global_parameters.AuxParam['area_solar'] = 110.5
Mjd0 = Mjd_UTC
Step = Step_Size #[s]
N_Step = Number_of_Steps #26.47hours
#shorten PC, eopdata, swdata, Cnm, and Snm
num = int(N_Step * Step / 86400) + 2
JD = t_start_jd
i = np.nonzero((Global_parameters.PC[:, 0] <= JD))
j = np.nonzero((Global_parameters.PC[:, 1] >= JD))
i = i[-1]
i = i[-1]
Global_parameters.PC = Global_parameters.PC[i:i + num + 1, :]
mjd = floor(Mjd_UTC)
i = np.nonzero(mjd == Global_parameters.eopdata[3, :])
i = i[-1]
i = i[-1]
Global_parameters.eopdata = Global_parameters.eopdata[:, i:i + num + 1]
i = np.nonzero(year == Global_parameters.swdata[0, :])
i = i[0]
j = np.nonzero(month == Global_parameters.swdata[1, :])
j = j[0]
k = np.nonzero(day == Global_parameters.swdata[2, :])
k = k[0]
i = i.tolist()
j = j.tolist()
k = k.tolist()
A = [x for x in i if x in j]
B = [y for y in A if y in k]
i = B[0]
Global_parameters.swdata = Global_parameters.swdata[:,
(i - 3):(i + num + 1)]
Global_parameters.Cnm = Global_parameters.Cnm[
0:Global_parameters.AuxParam['n'] + 1,
0:Global_parameters.AuxParam['n'] + 1]
Global_parameters.Snm = Global_parameters.Snm[
0:Global_parameters.AuxParam['n'] + 1,
0:Global_parameters.AuxParam['n'] + 1]
#% Ephemeris computation using variable-order Radau IIA integrator with step-size control
# options = rdpset('RelTol', 1e-13, 'AbsTol', 1e-16);
# [t, yout] = radau( @ Accel, (0:Step:N_Step * Step), Y0, options);
# Eph(:, 1) = t;
# Eph(:, 2: 7) = yout;
ol = solve_ivp(Accel, [0, N_Step * Step],
Y0,
method='Radau',
t_eval=np.arange(0, N_Step * Step, Step),
rtol=1e-3,
atol=1e-3)
a = ol.y
# # Make data
# u = np.linspace(0, 2 * np.pi, 100)
# v = np.linspace(0, np.pi, 100)
# x = 5000000 * np.outer(np.cos(u), np.sin(v))
# y = 5000000 * np.outer(np.sin(u), np.sin(v))
# z = 5000000 * np.outer(np.ones(np.size(u)), np.cos(v))
#
# # Plot the surface
# plt.axis('off')
# ax.plot_surface(x, y, z, rstride=1, # row 行步长
# cstride=2, color='w')
# z = a[2,:]
# y = a[1,:]
# x = a[0,:]
# vx=a[3,:]
# vy=a[4,:]
# vz=a[5,:]
position = a[0:3, :]
velocity = a[3:6, :]
time = ol.t
# if 0 :
#
# mpl.rcParams['legend.fontsize'] = 10
#
# fig = plt.figure()
#
# ax = fig.gca(projection='3d')
# ax.plot(x/1000, y/1000, z/1000, label='parametric curve')
# ax.legend()
#
# ax.set_xlim(-6000, 6000) # 设置横轴范围，会覆盖上面的横坐标,plt.xlim
# ax.set_ylim(-6000, 6000) #
# ax.set_zlim(-6000, 6000)
# ax.set_xlabel('x') # 设置x轴名称,plt.xlabel
# ax.set_ylabel('y')
# ax.set_zlabel('z')
# ax.patch.set_alpha(1)
# ax.grid(True)
# plt.show()
# if 1:
# length=len(x)
#
# orbit_element_data = np.zeros([6,length])
#
# for i in range(1,length+1):
#
# temp=rv_to_orbit_element(np.array([x[i-1],y[i-1],z[i-1]]),
# np.array([vx[i-1],vy[i-1],vz[i-1]]),398600.4418e9)
#
# orbit_element_data[0,i-1]=temp[0]
# orbit_element_data[1, i - 1] =temp[1]
# orbit_element_data[2, i - 1] =temp[2]
# orbit_element_data[3, i - 1] =temp[3]
# orbit_element_data[4, i - 1] =temp[4]
# orbit_element_data[5, i - 1] =temp[5]
#
#
# X=ol.t
#
# pl.figure(1)
# pl.subplot(231)
# pl.plot(X, orbit_element_data[0,:])
# temp=np.array([orbit_element[0]*1e3]*len(X))
# pl.plot(X, temp)
# plt.xlabel('t/s') # 设置x轴名称,plt.xlabel
# plt.ylabel('a/m')
#
# pl.subplot(232)
# pl.plot(X, orbit_element_data[1,:])
# temp = np.array([orbit_element[1]] * len(X))
# pl.plot(X, temp)
# plt.xlabel('t/s') # 设置x轴名称,plt.xlabel
# plt.ylabel('e')
#
# pl.subplot(233)
# pl.plot(X, orbit_element_data[2,:])
# temp = np.array([radians(orbit_element[2])] * len(X))
# pl.plot(X, temp)
# plt.xlabel('t/s') # 设置x轴名称,plt.xlabel
# plt.ylabel('i/rad')
#
#
# pl.subplot(234)
# pl.plot(X, orbit_element_data[3,:])
# temp = np.array([radians(orbit_element[3])] * len(X))
# pl.plot(X, temp)
# plt.xlabel('t/s') # 设置x轴名称,plt.xlabel
# plt.ylabel('RAAN/rad')
#
# pl.subplot(235)
# pl.plot(X, orbit_element_data[4,:])
# temp = np.array([radians(orbit_element[4])] * len(X))
# pl.plot(X, temp)
# plt.xlabel('t/s') # 设置x轴名称,plt.xlabel
# plt.ylabel('Perigee/rad')
#
# pl.subplot(236)
# pl.plot(X, orbit_element_data[5,:]% (2 * pi))
# temp = np.array([radians(orbit_element[5])] * len(X))
# pl.plot(X, temp)
# plt.xlabel('t/s') # 设置x轴名称,plt.xlabel
# plt.ylabel('True_anomaly/rad')
#
#
# pl.show()
#
#
# # plt.plot(X, orbit_element_data[0,:])
# # plt.plot(X, orbit_element_data[1,:])
# # plt.plot(X, orbit_element_data[2, :])
# # plt.plot(X, orbit_element_data[3, :])
# # plt.plot(X, orbit_element_data[4, :])
# # plt.plot(X, orbit_element_data[5, :]% (2 * pi))
# # 在ipython的交互环境中需要这句话才能显示出来
#
# plt.show()
HPOP_Results = np.row_stack((time, a))
joblib.dump(HPOP_Results, 'HPOP_Results.pkl')
return
#from 2019年1月15日9：00到12:00
month = 3
day = 15
year = 2017
hour = 9
minute = 0
second = 0
length=60#设置步长
time=np.arange(0,length,1.0)#生成长度为60的数组,要打1.0因为数组数据类型要为float，输入1则默认类型为int
Visibility=np.arange(0,length,1)
r = array([3e6, 4e6, 4e6])
direction_vector = array([-1.0, 0.0, 0.0])
for i in range(0,length): #0~59,没有60
minute=i+1
time[i] = Julian_date(year,month,day,hour,minute,second)
Visibility[i] = Visibility_for_celestial_body(direction_vector, r, time[i])
#xlim(time[0,1], time[0,10])
#设置y轴范围
#ylim(0, 2)
#Visibility=[1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1,1]
plt.plot(time, Visibility)
plt.show()