# -*- coding: utf-8 -*-
"""
Template for the main solution code in Part 7 of the project.

The objective of the template files is to give you an idea of
the most important functions that you have to implement, what
input they will need and what output they should produce.

To make things work in practice you will have to add more
functionalities than the ones outlined, and you might have
to adapt the interfaces to fit your specific approach.

You are of course free (and encouraged) to structure the code
in any way you want!
"""
import ast2000tools.constants as const
import ast2000tools.utils as utils
from ast2000tools.space_mission import SpaceMission
import part_6


def compute_drag_force(system,
                       planet_idx,
                       mean_molecular_mass,
                       lander_position,
                       lander_velocity,
                       cross_sectional_area):
    """
    Here you can implement the drag force function for challenge A
    of Part 7 of the project.
    """

    # Insert awesome code here...

    # You will need the following method:
    # part_6.compute_atmospheric_profiles

    # You will probably also need these quantities:
    # const.pi
    # const.day
    # system.radii
    # system.rotational_periods

    return drag_force


def run_landing_planning_simulation(mission,
                                    planet_idx,
                                    mean_molecular_mass,
                                    initial_time,
                                    initial_position,
                                    initial_velocity,
                                    duration,
                                    time_of_lander_launch,
                                    lander_launch_delta_v,
                                    parachute_area,
                                    parachute_deployment_height,
                                    thruster_force,
                                    thruster_activation_height):
    """
    Here you can implement the landing planning simulation for challenge B
    of Part 7 of the project.
    """

    # Insert awesome code here...

    # You will probably also need these quantities:
    # const.G
    # const.m_sun
    # system.masses
    # system.radii
    # mission.spacecraft_mass
    # mission.spacecraft_area
    # mission.lander_mass
    # mission.lander_area

    # You might want to generate some plots to inspect the results.


def land_spacecraft(landing_sequence,
                    duration,
                    time_of_lander_launch,
                    lander_launch_delta_v,
                    parachute_area,
                    parachute_deployment_height,
                    thruster_force,
                    thruster_activation_height):
    """
    Here you can implement the commanding of the spacecraft for
    challenge C of Part 7 of the project.
    """

    # Insert awesome code here...

    # You might want to generate some cool videos and pictures
    # to view in MCAst.


# Prevent the following code from executing when calling `import part_7`
if __name__ == '__main__':

    # Print a message if a newer version of ast2000tools is available
    utils.check_for_newer_version()

    # Load the mission instance saved after completing Part 6
    mission = SpaceMission.load('mission_after_part_6.pickle')

    # Obtain the ongoing landing sequence
    landing_sequence = mission.ongoing_landing_sequence

    # Obtain the initial conditions for the landing simulation
    initial_time, initial_position, initial_velocity = landing_sequence.orient()

    # Run planning simulations to determine landing parameters here...

    # Land the lander safely on the surface of the planet
    land_spacecraft(landing_sequence,
                    duration,
                    time_of_lander_launch,
                    lander_launch_delta_v,
                    parachute_area,
                    parachute_deployment_height,
                    thruster_force,
                    thruster_activation_height)