The bug I'm experiencing is I am trying to access the values of Flight.x, Flight.y and Flight.z. I checked the documentation and Flight.x and Flight.z are indexed differently to Flight.y. I want to be able to index the x,y, and z coordinates of the rocket at a certain point in time (17.1 seconds). This is because then the second stage will launch.

However, when I try to even use display(type(Flight_stage1.x)) or anything similar, I get the error message:

KeyError: 'x'
ValueError: array must not contain infs or NaNs

I tried writing a script to turn infs and NaNs to zero but it seems to be a decorator format which I am not used to. Here is the code I tried to run, which works up until display(type(Flight_stage1.y)): (You'll have to use a thrust curve file in your directory!)

import math
import datetime

Env1 = Environment(latitude=67.89325597913002, longitude=21.065756056273834, elevation=300) 
tomorrow = datetime.date.today() + datetime.timedelta(days=1)
Env1.set_date((tomorrow.year, tomorrow.month, tomorrow.day, 12))
Env1.set_atmospheric_model(type="Ensemble", file="GEFS")

Motor1 = SolidMotor(
    thrust_source=r"...Python Modelling\Thrust curves\Motor.eng",
    dry_mass=260, # kg (gross mass - propellant mass)
    dry_inertia=(261.89, 261.89, 10.98),
    nozzle_radius=0.23957143, # radius of the nozzle outlet in meteres
    grain_number=1,
    grain_density=1750,
    grain_outer_radius=0.2795,
    grain_initial_inner_radius=0.07985714,
    grain_initial_height=2.6072,
    grain_separation=0,
    grains_center_of_mass_position= 1.445, 
    center_of_dry_mass_position=0,
    nozzle_position=3.44,
    burn_time=13.1,
    throat_radius=0.07985714,
    coordinate_system_orientation="combustion_chamber_to_nozzle",
)

# Rocket

rocket_stage1 = Rocket(
    radius=0.483,
    mass=555.736, 
    inertia=(2688.81, 2688.81, 36.97), 
    power_off_drag=r"...\Python Modelling\Drag curves\Motor1PowerOffDragCurve.eng",
    power_on_drag=r"...\Python Modelling\Drag curves\Motor1PowerOnDragCurve.eng",
    center_of_mass_without_motor=3.88, # m
    coordinate_system_orientation="nose_to_tail",
)

rocket_stage1.add_motor(Motor1, position=4.893)

nose_cone = rocket_stage1.add_nose(length=2.49, kind="ogive", position=0)

fin_set_1 = rocket_stage1.add_trapezoidal_fins(
    n=4,
    root_chord=0.865,
    tip_chord=0.302,
    span=0.352,
    position=3.985,
    sweep_length = 0.707
)

# Defining triggers for parachutes
def drogueTrigger(p, y, x, z, already_triggered=False):
    if already_triggered:
        return False
    if y < 0:
        return True
    return False
    #return True if y < 0 else False  # Less than zero, so rocket is coming back down from apogee

def mainTrigger(p, y, x, z, already_triggered=False): # Extra arguments are given because trigger is passing a lot through
    if already_triggered:
        return False
    if y < 0 and y < 1000:
        return True
    return False
    #print(type(y))
    #print(y)
    #return True if y < 0 and y < 1000 else False # Parachute within 1km from ground

Main = rocket_stage1.add_parachute('Main',
                                   cd_s=10.0,
                                   trigger=mainTrigger, 
                                   sampling_rate=105,
                                   lag=1.5,
                                   noise=(0, 8.3, 0.5))

Drogue = rocket_stage1.add_parachute('Drogue',
                                   cd_s=1.0,
                                   trigger=drogueTrigger, 
                                   sampling_rate=105,
                                   lag=1.5,
                                   noise=(0, 8.3, 0.5))

                              # Parameters for first stage rocket flight
Flight_stage1 = Flight(rocket=rocket_stage1, environment=Env1, inclination=85, heading=0 ,verbose=True, rail_length=10)

ignition_delay = 4
tsecond_stage = RedKite.burn_duration + ignition_delay

display(type(Flight_stage1.y))

I would expect the type of Flight_stage1.y to be listed. I want to be able to call Flight.y(tsecond_stage) for example, to see what the y value is at the time t=tsecond_stage.

I feel like this should be a simple fix! Any support on this I can get would be much appreciated.