human
I am working on the file "SIE_552_HW3.ipynb".
The first task is:
SIE 552 HW #3
This is a space mission design assignment for interplantary travel.  The homework was to create a Type-1 trajectory from Earth to Mars.  Departure from earth is set to be March 22, 2021 with an anticipated arrival on Mars at October 8, 2021.  We're also given the following details about Earth and Mars:
When designing the transfer ellipse, the overall mission has to be considered first.  We know that we want to create an interplanetary travel mission between Earth and Mars.  In order to plan this, we have to know more about those planets:

Earth at Launch: (March 22, 2021)

Longitude = 181.44 deg 
Eccentricity = 0.0167
SMA =  149,598,020 Km
Inclination = 0 deg 
Longitude of the Perihelion = 102.958 deg 
Longitude of the Ascending Node = 0 deg 
Radius = 149,905,909.7 km 
Velocity = 29.89 km/sec
True Anomaly = 78.48 deg 
Flight Path Angle = 0.9348 deg 


Mars at Arrival: (October 8, 2021)

Longitude = 333.22 deg 
Eccentricity = 0.0934
SMA =  227,939,133 Km
Inclination = 1.849 deg 
Longitude of the Perihelion = 336.093 deg 
Longitude of the Ascending Node = 49.572 deg 
Radius = 206,671,197 km
Velocity = 26.94 km/sec
True Anomaly = 357.128 deg 
Flight Path Angle = - 0.2452 deg


We'll store these as PlanetaryObejct's in python to help us later.
Can you write Python program for it?

Can you provide a the Python program you requested?
assistant
#Here is the Python program you requested.

class PlanetaryObject():
    """
    A simple class used to store pertinant information about the plantary object
    """
    def __init__(self, date, L, e, SMA, i, peri, asc, r, v, anom, fp, mu):
        self.date = date   # Event Date
        self.L = L         # Longitude
        self.e = e         # Eccentricity
        self.SMA = SMA     # SMA
        self.i = i         # Inclination
        self.peri = peri   # Longitude of Perihelion
        self.asc = asc     # Longitude of Ascending Node
        self.r = r         # Radius
        self.v = v         # Velocity
        self.anom = anom   # True Anomaly
        self.fp = fp       # Flight Path Angle
        self.mu = mu       # Gravitation parameter

earth = PlanetaryObject(
    datetime.date(2021, 3, 22),
    181.44,     # Longitude
    0.0167,     # Eccentricity
    149598020,  # SMA
    0,          # Inclination
    102.958,    # Longitude of Perihelion
    0,          # Longitude of Ascending Node
    14905909.7, # Radius
    29.89,      # Velocity
    78.48,      # True Anomaly
    0.9348,     # Flight Path Angle
    398600.4    # Gravitation parameter
)
mars = PlanetaryObject(
    datetime.date(2021, 10, 8),
    333.22,     # Longitude
    0.0934,     # Eccentricity
    227939133,  # SMA
    1.849,      # Inclination
    336.093,    # Longitude of Perihelion
    49.572,     # Longitude of Ascending Node
    206671197,  # Radius
    26.94,      # Velocity
    357.128,    # True Anomaly
    -0.2452,    # Flight Path Angle
    42828.3     # Gravitation parameter
)