def problem_1():
# Problem 1
print("Problem 1:")
dep_early = datetime.datetime(2005, 6, 6, 0, 0, 0) # Earth departure earliest date (June 6th 2005)
dep_late = datetime.datetime(2005, 11, 7, 0, 0, 0) # Earth departure latest date (November 7th 2005)
arr_early = datetime.datetime(2005, 12, 1, 0, 0, 0) # Mars arrival earliest date (December 1st 2005)
arr_late = datetime.datetime(2007, 2, 24, 0, 0, 0) # Mars arrival latest date (February 24th 2007)
_, _, _ = util.porkchop(p_d.Earth(), dep_early, dep_late,
p_d.Mars(), arr_early, arr_late, 5)
# Project 2
# AERO 452
# Ryo Takatori
import numpy as np
from scipy.integrate import solve_ivp
import time
from orbit_tools import classical_orbital_elements as coe, lambert
from orbit_tools import equation_of_motion as eom
from orbit_tools import perturbations
from orbit_tools import planet_data as p_d
from orbit_tools import plotter
from orbit_tools import utility as util
earth = p_d.Earth()
mue = earth.mu
re = earth.radius
c_d = 2.2
c_r = 1.2
t_span_type = [[0, 30*24*60*60], [0, 365*24*60*60]]
t_span_type = [[0, 30*24*60*60]]
def main():
sat_dict = {
"LEMUR-2 JOEL":{
"name": "LEMUR-2 JOEL.txt",
"planets": ["Sun", "Moon"],
"spacecraft": {
"area": 0.1*0.1*3,
"mass": 4
},