added plot_orbit feature

plot multiple orbits in the same graph
Mechanics-of-Orbit · Mar 5, 2023 · f962857 · f962857
1 parent c4a4a91
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diff --git a/.idea/.gitignore b/.idea/.gitignore
diff --git a/.idea/MOPy.iml b/.idea/MOPy.iml
diff --git a/.idea/inspectionProfiles/profiles_settings.xml b/.idea/inspectionProfiles/profiles_settings.xml
diff --git a/.idea/misc.xml b/.idea/misc.xml
diff --git a/.idea/modules.xml b/.idea/modules.xml
diff --git a/.idea/vcs.xml b/.idea/vcs.xml
diff --git a/mopylib/constants/planetarydetails.py b/mopylib/constants/planetarydetails.py
@@ -163,9 +163,9 @@ def split_unit(input_unit):
         angle - radians, degrees, rad, deg
         SI Prefix = ['Y', 'Z', 'E', 'P', 'T', 'G', 'M', 'K', 'H', 'D', 'd', 'c', 'm', 'u', 'n', 'p', 'f', 'a', 'z']
         """
-        if unit[0][0] in SIV.SI_PREFIX:
+        if unit[0][0] in SI_PREFIX:
             if unit[1] > 0:
-                units_calculation.append(SIV.SI_PREFIX_VALUES[unit[0][0]])
+                units_calculation.append(SI_PREFIX_VALUES[unit[0][0]])
             elif unit[1] < 0:
                 pass
                 # units_calculation.append(1/(SIV.SI_PREFIX_VALUES[unit[0][0]]))

diff --git a/mopylib/orbitalparameters.py b/mopylib/orbitalparameters.py
@@ -2,150 +2,163 @@
 import constants.GlobalConstants as GCs
 import constants.planetarydetails as pandet
 
-class OrbitalValues():
+
+class OrbitalValues:
     """The initiate the variables and calculate all the rest of the values related to the orbit based on the input.
-    This take the given inputs and evaluates if the given information is enough to calculate the all the required orbital values. 
-    If not, it will return an error.
+    This take the given inputs and evaluates if the given information is enough to calculate the all the required
+    orbital values. If not, it will return an error.
     
     ### !!! Enter any of the two values only to avoid over constrained situation!!!
-    
-    If it does you can calculate other operations in this class.
+
     ------
     Example:
-    >>> `import mopylib.orbitalparameters as orbit_par
-    >>> `orbit_1 = orbit_par.OrbitalValues("Earth", semi_major_axis=20000, eccentricity=0.4)`
-    >>> `orbit_1_values = orbit_1.caculate_orbital_values()`
-    >>> `print(orbit_1_values)`
+    >>> import mopylib.orbitalparameters as orbit_par
+    >>> orbit_01 = orbit_par.OrbitalValues("Earth", semi_major_axis=20000, eccentricity=0.4)
+    >>> orbit_01_values = orbit_1.calculate_orbital_values()
+    >>> print(orbit_01_values)
     
     Output:
-    >>> `{'SemiMajorAxis': 20000, 'Eccentricity': 0.4, 'RadiusOfPerigee': 12000.0, 
+    >>> {'SemiMajorAxis': 20000, 'Eccentricity': 0.4, 'RadiusOfPerigee': 12000.0,
     'RadiusOfApogee': 28000.0, 'MeanMotion': 4480.043512802378, 'TimePeriod': 28148.943575165125, 
     'SpecificAngularMomentum': 81830.91404108841, 'SpecificMechanicalEnergy': -9.9647299, 'SemiLatusRectum': 16800.0}`
     
     ------
     Args:
         major_body (String): Name of the Major Body of the Orbit
-        radiusOfApogee (float, optional): Radius of Apogee of the Orbit. Defaults to None.
-        radiusOfPerigee (float, optional): Radius of Perigee of the Orbit. Defaults to None.
+        radius_of_apogee (float, optional): Radius of Apogee of the Orbit. Defaults to None.
+        radius_of_perigee (float, optional): Radius of Perigee of the Orbit. Defaults to None.
         semi_major_axis (float, optional): Semi Major Axis of the Orbit. Defaults to None.
         eccentricity (Float, optional): Eccentricity of the Orbit. Defaults to None.
     """
-    def __init__(self, major_body, 
-                 radius_of_apogee=None, 
-                 radius_of_perigee=None, 
-                 semi_major_axis=None, 
+
+    def __init__(self, major_body,
+                 radius_of_apogee=None,
+                 radius_of_perigee=None,
+                 semi_major_axis=None,
                  eccentricity=None):
+        self.specific_mechanical_energy = None
+        self.mean_motion = None
+        self.orbital_time_period = None
+        self.specific_angular_momentum = None
+        self.semi_latus_rectum = None
+        self.gravitational_constant = None
         self.major_body = major_body
         self.major_body_mass = pandet.value(major_body, 'mass')
         self.radius_of_apogee = radius_of_apogee
         self.radius_of_perigee = radius_of_perigee
         self.semi_major_axis = semi_major_axis
         self.eccentricity = eccentricity
-        OrbitalValues.calculate_rest(self)        
-    
+        self.calculate_rest()
+
     def calculate_orbital_constants(self):
         self.gravitational_constant = GCs.NEWTON_GRAVITATIONAL_CONSTANT * self.major_body_mass
-        self.semi_latus_rectum = self.semi_major_axis*(1-self.eccentricity**2)
-        self.specific_angular_momentum = (self.radius_of_perigee*(1+self.eccentricity)*self.gravitational_constant)**0.5
-        self.orbital_time_period = np.sqrt(((4*np.pi**2)/self.gravitational_constant)*self.semi_major_axis**3)
-        self.mean_motion = self.orbital_time_period/(2*np.pi)
-        self.specific_mechanical_energy = -self.gravitational_constant/(2* self.semi_major_axis)
-        return self.mean_motion, self.orbital_time_period, self.specific_angular_momentum, self.specific_mechanical_energy, self.semi_latus_rectum
-
+        self.semi_latus_rectum = self.semi_major_axis * (1 - self.eccentricity ** 2)
+        self.specific_angular_momentum = (self.radius_of_perigee * (
+                    1 + self.eccentricity) * self.gravitational_constant) ** 0.5
+        self.orbital_time_period = np.sqrt(((4 * np.pi ** 2) / self.gravitational_constant) * self.semi_major_axis ** 3)
+        self.mean_motion = self.orbital_time_period / (2 * np.pi)
+        self.specific_mechanical_energy = -self.gravitational_constant / (2 * self.semi_major_axis)
+        return self.mean_motion, self.orbital_time_period, self.specific_angular_momentum, \
+            self.specific_mechanical_energy, self.semi_latus_rectum
+
     def calculate_rest(self):
-        if self.radius_of_apogee and self.radius_of_perigee != None:
-            self.semi_major_axis = (self.radius_of_perigee + self.radius_of_apogee)/2
-            self.eccentricity = (self.radius_of_apogee - self.radius_of_perigee)/ \
+        if self.radius_of_apogee and self.radius_of_perigee is not None:
+            self.semi_major_axis = (self.radius_of_perigee + self.radius_of_apogee) / 2
+            self.eccentricity = (self.radius_of_apogee - self.radius_of_perigee) / \
                                 (self.radius_of_apogee + self.radius_of_perigee)
-        elif self.semi_major_axis and self.eccentricity != None:
+        elif self.semi_major_axis and self.eccentricity is not None:
             self.radius_of_perigee = self.semi_major_axis * (1 - self.eccentricity)
-            self.radius_of_apogee  = self.semi_major_axis * (1 + self.eccentricity)
-            
-        elif self.semi_major_axis and self.radius_of_apogee != None:
-            self.radius_of_perigee = 2*self.semi_major_axis - self.radius_of_apogee
-            self.eccentricity = (self.radius_of_apogee - self.radius_of_perigee)/ \
+            self.radius_of_apogee = self.semi_major_axis * (1 + self.eccentricity)
+
+        elif self.semi_major_axis and self.radius_of_apogee is not None:
+            self.radius_of_perigee = 2 * self.semi_major_axis - self.radius_of_apogee
+            self.eccentricity = (self.radius_of_apogee - self.radius_of_perigee) / \
                                 (self.radius_of_apogee + self.radius_of_perigee)
-        elif self.semi_major_axis and self.radius_of_perigee != None:
-            self.radius_of_apogee = 2*self.semi_major_axis - self.radius_of_perigee
-            self.eccentricity = (self.radius_of_apogee - self.radius_of_perigee)/ \
+        elif self.semi_major_axis and self.radius_of_perigee is not None:
+            self.radius_of_apogee = 2 * self.semi_major_axis - self.radius_of_perigee
+            self.eccentricity = (self.radius_of_apogee - self.radius_of_perigee) / \
                                 (self.radius_of_apogee + self.radius_of_perigee)
-        elif self.eccentricity and self.radius_of_apogee != None:
-            self.radius_of_perigee = self.radius_of_apogee * ((1 - self.eccentricity)/(1 + self.eccentricity))
-            self.semi_major_axis = (self.radius_of_perigee + self.radius_of_apogee)/2
-        elif self.eccentricity and self.radius_of_perigee != None:
-            self.radius_of_apogee = self.radius_of_perigee * ((1 + self.eccentricity)/(1 - self.eccentricity))
-            self.semi_major_axis = (self.radius_of_perigee + self.radius_of_apogee)/2        
-                          
-        OrbitalValues.calculate_orbital_constants(self)
-        
-    def caculate_orbital_values(self, return_style='dict'):
+        elif self.eccentricity and self.radius_of_apogee is not None:
+            self.radius_of_perigee = self.radius_of_apogee * ((1 - self.eccentricity) / (1 + self.eccentricity))
+            self.semi_major_axis = (self.radius_of_perigee + self.radius_of_apogee) / 2
+        elif self.eccentricity and self.radius_of_perigee is not None:
+            self.radius_of_apogee = self.radius_of_perigee * ((1 + self.eccentricity) / (1 - self.eccentricity))
+            self.semi_major_axis = (self.radius_of_perigee + self.radius_of_apogee) / 2
+
+        self.calculate_orbital_constants()
+
+    def calculate_orbital_values(self, return_style='dict'):
         # possible values dict(default), variables
         if return_style == 'dict':
             orbital_values = {
-                        "SemiMajorAxis": self.semi_major_axis, "Eccentricity": self.eccentricity,
-                        "RadiusOfPerigee": self.radius_of_perigee, "RadiusOfApogee": self.radius_of_apogee,
-                        "MeanMotion": self.mean_motion, "TimePeriod": self.orbital_time_period, 
-                        "SpecificAngularMomentum": self.specific_angular_momentum, "SpecificMechanicalEnergy":self.specific_mechanical_energy, 
-                        "SemiLatusRectum": self.semi_latus_rectum
-                        }
+                "SemiMajorAxis": self.semi_major_axis, "Eccentricity": self.eccentricity,
+                "RadiusOfPerigee": self.radius_of_perigee, "RadiusOfApogee": self.radius_of_apogee,
+                "MeanMotion": self.mean_motion, "TimePeriod": self.orbital_time_period,
+                "SpecificAngularMomentum": self.specific_angular_momentum,
+                "SpecificMechanicalEnergy": self.specific_mechanical_energy,
+                "SemiLatusRectum": self.semi_latus_rectum
+            }
             return orbital_values
 
         elif return_style == 'variables':
             return self.semi_major_axis, self.eccentricity, self.radius_of_perigee, self.radius_of_apogee, \
-                    self.mean_motion, self.orbital_time_period, self.specific_angular_momentum, self.specific_mechanical_energy, \
-                    self.semi_latus_rectum
-    
+                self.mean_motion, self.orbital_time_period, self.specific_angular_momentum, self.specific_mechanical_energy, \
+                self.semi_latus_rectum
+
     def calculate_velocities_at_these_angles(self, *angles):
         velocities = []
         for angle in angles:
             velocities.append(OrbitalValues.calculate_velocity_at_point(self, angle=angle))
         return velocities
-    
+
     def calculate_velocities_at_these_points(self, *radii):
         velocities = []
         for radius in radii:
             velocities.append(OrbitalValues.calculate_velocity_at_point(self, radius=radius))
         return velocities
-
-    def calculate_velocity_at_point(self, radius=None,angle=None):
-        if angle != None:
-            radius = ((self.specific_angular_momentum**2/self.gravitational_constant)/(1+(self.eccentricity)*np.cos(angle)))
 
-        velocity = np.sqrt((2*self.gravitational_constant/radius)-(self.gravitational_constant/self.semi_major_axis))
+    def calculate_velocity_at_point(self, radius=None, angle=None):
+        if angle is not None:
+            radius = ((self.specific_angular_momentum ** 2 / self.gravitational_constant) / (
+                    1 + self.eccentricity * np.cos(angle)))
+
+        velocity = np.sqrt(
+            (2 * self.gravitational_constant / radius) - (self.gravitational_constant / self.semi_major_axis))
 
         return velocity
 
+
 if __name__ == '__main__':
     import pandas as pd
+
+    sma = np.linspace(7000, 100000, num=15)
+    e = np.linspace(0, 1, num=15, endpoint=False)
     # test = OrbitalValues("Earth", radiusOfApogee = 20000, radiusOfPerigee = 10000)
     # orbit_1 = OrbitalValues("Earth", semi_major_axis=20000, eccentricity=0)
-    orbit_1 = OrbitalValues("Earth", semi_major_axis=20000, eccentricity=0.4)
-    orbit_2 = OrbitalValues("Earth", semi_major_axis=20000, radius_of_apogee=28000)
-    orbit_3 = OrbitalValues("Earth", semi_major_axis=20000, radius_of_perigee=12000)
-    orbit_4 = OrbitalValues("Earth", eccentricity=0.4, radius_of_apogee=28000)
-    orbit_5 = OrbitalValues("Earth", eccentricity=0.4, radius_of_perigee=12000)
-    orbit_6 = OrbitalValues("Earth", radius_of_perigee=12000, radius_of_apogee=28000)
-    orbital_values = [
-                orbit_1.caculate_orbital_values(), 
-                orbit_2.caculate_orbital_values(), 
-                orbit_3.caculate_orbital_values(), 
-                orbit_4.caculate_orbital_values(), 
-                orbit_5.caculate_orbital_values(), 
-                orbit_6.caculate_orbital_values()
-                ]
-
-    # orbital_values = [orbit_1.caculate_orbital_values()]
-    orbital_values_df = pd.DataFrame.from_dict(orbital_values)
-    # pd.set_option('display.max_columns', None)
-    # orbital_values_df.head()    
-    print(orbital_values_df.T)
-    print(orbital_values[0])
-
-
-
-
-
-    print(orbit_1.calculate_velocities_at_these_angles(0,np.pi/2,np.pi))
-
-
-
+    # orbit_1 = OrbitalValues("Earth", semi_major_axis=20000, eccentricity=0.4)
+    # orbit_2 = OrbitalValues("Earth", semi_major_axis=20000, radius_of_apogee=28000)
+    # orbit_3 = OrbitalValues("Earth", semi_major_axis=20000, radius_of_perigee=12000)
+    # orbit_4 = OrbitalValues("Earth", eccentricity=0.4, radius_of_apogee=28000)
+    # orbit_5 = OrbitalValues("Earth", eccentricity=0.4, radius_of_perigee=12000)
+    # orbit_6 = OrbitalValues("Earth", radius_of_perigee=12000, radius_of_apogee=28000)
+    for i, j in zip(sma, e):
+        orbit_1 = OrbitalValues("Earth", semi_major_axis=i, eccentricity=j)
+        print(f'{orbit_1.calculate_orbital_values()} \n')
+
+    # orbital_values = [
+    #             orbit_1.calculate_orbital_values(),
+    #             # orbit_2.calculate_orbital_values(),
+    #             # orbit_3.calculate_orbital_values(),
+    #             # orbit_4.calculate_orbital_values(),
+    #             # orbit_5.calculate_orbital_values(),
+    #             # orbit_6.calculate_orbital_values()
+    #             ]
+
+    # orbital_values = [orbit_1.calculate_orbital_values()]
+    # orbital_values_df = pd.DataFrame.from_dict(orbital_values)
+    # # pd.set_option('display.max_columns', None)
+    # # orbital_values_df.head()    
+    # print(orbital_values_df.T)
+    # print(orbital_values[0])
+
+    print(orbit_1.calculate_velocities_at_these_angles(0, np.pi / 2, np.pi))