Create Satellite_Orbits_3rd_Projects.py

Satellite_Orbits_3rd_Projects.py

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+import numpy as np
+import matplotlib.pyplot as plt
+from mpl_toolkits.mplot3d import Axes3D
+from mpl_toolkits.mplot3d.art3d import Poly3DCollection
+from matplotlib.animation import FuncAnimation
+
+# Earth parameters
+earth_radius = 6371  # Earth radius in kilometers
+rotation_period = 24  # Earth rotation period in hours
+
+# Satellite orbit data
+satellites = [
+    {"semi_major_axis": 800, "eccentricity": 0.1, "inclination": 45, "argument_of_periapsis": 0, "ascending_node": 0},
+    {"semi_major_axis": 1000, "eccentricity": 0.2, "inclination": 60, "argument_of_periapsis": 0, "ascending_node": 120},
+    {"semi_major_axis": 1200, "eccentricity": 0.3, "inclination": 75, "argument_of_periapsis": 0, "ascending_node": 240},
+    {"semi_major_axis": 1400, "eccentricity": 0.15, "inclination": 30, "argument_of_periapsis": 0, "ascending_node": 60},
+    {"semi_major_axis": 1600, "eccentricity": 0.25, "inclination": 50, "argument_of_periapsis": 0, "ascending_node": 180},
+]
+
+# Time array
+num_frames = 100
+time = np.linspace(0, 2 * np.pi, num_frames)
+
+# Initialize the plot
+fig = plt.figure()
+ax = fig.add_subplot(111, projection='3d')
+
+# Earth surface coordinates
+u = np.linspace(0, 2 * np.pi, 100)
+v = np.linspace(0, np.pi, 50)
+x_earth = earth_radius * np.outer(np.cos(u), np.sin(v))
+y_earth = earth_radius * np.outer(np.sin(u), np.sin(v))
+z_earth = earth_radius * np.outer(np.ones(np.size(u)), np.cos(v))
+
+# Plot Earth surface
+earth = ax.plot_surface(x_earth, y_earth, z_earth, color='lightblue', alpha=0.8)
+
+# Initialize satellite lines
+satellite_lines = []
+
+# Plotting the satellite orbits
+for satellite in satellites:
+    semi_major_axis = satellite["semi_major_axis"]
+    eccentricity = satellite["eccentricity"]
+    inclination = satellite["inclination"]
+    argument_of_periapsis = satellite["argument_of_periapsis"]
+    ascending_node = satellite["ascending_node"]
+
+    # Parametric equations for satellite orbit
+    r = semi_major_axis * (1 - eccentricity**2) / (1 + eccentricity * np.cos(time))
+    x_satellite = r * (np.cos(ascending_node) * np.cos(argument_of_periapsis + time) - np.sin(ascending_node) * np.sin(argument_of_periapsis + time) * np.cos(inclination))
+    y_satellite = r * (np.sin(ascending_node) * np.cos(argument_of_periapsis + time) + np.cos(ascending_node) * np.sin(argument_of_periapsis + time) * np.cos(inclination))
+    z_satellite = r * (np.sin(argument_of_periapsis + time) * np.sin(inclination))
+
+    # Plot the satellite orbit
+    satellite_line, = ax.plot(x_satellite, y_satellite, z_satellite, color='red', linewidth=1)
+    satellite_lines.append(satellite_line)
+
+# Animation update function
+def update(frame):
+    # Rotate Earth around the Z-axis
+    angle = (360 / rotation_period) * frame / num_frames
+    x_earth_rotated = x_earth * np.cos(np.radians(angle)) - y_earth * np.sin(np.radians(angle))
+    y_earth_rotated = x_earth * np.sin(np.radians(angle)) + y_earth * np.cos(np.radians(angle))
+    z_earth_rotated = z_earth
+
+    # Update Earth surface plot
+    earth._verts3d = x_earth_rotated, y_earth_rotated, z_earth_rotated
+
+    # Update satellite orbits
+    for i, satellite_line in enumerate(satellite_lines):
+        satellite_line.set_data(x_satellite[:frame+1], y_satellite[:frame+1])
+        satellite_line.set_3d_properties(z_satellite[:frame+1])
+
+    return earth, satellite_lines
+
+# Set plot labels and limits
+ax.set_xlabel('X (km)')
+ax.set_ylabel('Y (km)')
+ax.set_zlabel('Z (km)')
+ax.set_title('Satellite Orbits')
+
+# Set plot aspect ratio to be equal
+ax.set_box_aspect([1, 1, 1])
+
+# Create animation
+animation = FuncAnimation(fig, update, frames=num_frames, interval=100)
+
+plt.show()