From c0c11da2fdd3e1baf7bca164cd4fe5a4341711b4 Mon Sep 17 00:00:00 2001
From: Lucas <69172945+lucasfourier@users.noreply.github.com>
Date: Mon, 12 Feb 2024 21:45:04 -0300
Subject: [PATCH] Acceptance test for Juno was born. Also, removed unnecessary
 imports in the acceptance of the NDRT flight.

---
 tests/acceptance/test_Juno3.py            | 103 ++++++++++++++++++++++
 tests/acceptance/test_ndrt_2020_rocket.py |   7 --
 2 files changed, 103 insertions(+), 7 deletions(-)
 create mode 100644 tests/acceptance/test_Juno3.py

diff --git a/tests/acceptance/test_Juno3.py b/tests/acceptance/test_Juno3.py
new file mode 100644
index 000000000..a588fbcf6
--- /dev/null
+++ b/tests/acceptance/test_Juno3.py
@@ -0,0 +1,103 @@
+import numpy as np
+import pandas as pd
+from scipy.signal import savgol_filter
+
+from rocketpy import Environment, Flight, Function, Rocket, SolidMotor
+
+
+def test_ndrt_2020_rocket_data_asserts_acceptance():
+    # Juno III flight (2023, by Projeto Jupiter)
+    # Launched at Spaceport America Cup 2023 edition
+    # Date: June 23rd, 2023. around 17hrs local time
+    # (Team Number 138)
+    # Permission to use flight data given by 
+    
+    # IMPORTANT RESULTS
+    # Last simulated apogee before flight: 3026.054 m
+    # Official recorded apogee: 3213 m
+    # Relative error of 8.08 %
+
+    # Defining all parameters
+
+    parameters = {
+        # Mass Details
+        "rocket_mass": (24.05, 0.010),
+        # Propulsion details
+        "impulse": (8800, 0.033 * 8800),
+        "burn_time": (5.8, 0.1),
+        "nozzle_radius": (0.0335, 0.001),
+        "throat_radius": (0.0114, 0.001),
+        "grain_separation": (0.006, 0.001),
+        "grain_density": (1748.9, 30),
+        "grain_outer_radius": (0.0465, 0.001),
+        "grain_initial_inner_radius": (0.016, 0.002),
+        "grain_initial_height": (0.156, 0.001),
+        # Aerodynamics
+        "drag_coefficient": (, ),
+        "inertia_i": (, ),
+        "inertia_z": (, ),
+        "radius": (0.0655, 0.001),
+        "distance_rocket_nozzle": (, ),
+        "distance_rocket_propellant": (, ),
+        "power_off_drag": (, ),
+        "power_on_drag": (, ),
+        "nose_length": (0.565, 0.001),
+        "nose_distance_to_cm": (, ),
+        "fin_span": (0.130, 0.001),
+        "fin_root_chord": (0.20, 0.001),
+        "fin_tip_chord": (0.12, 0.0001),
+        "fin_distance_to_cm": (, ),
+        "transition_top_radius": (, ),
+        "transition_bottom_radius": (,),
+        "transition_length": (, ),
+        "transition_distance_to_cm": (, ),
+        # Launch and environment details
+        "wind_direction": (, ),
+        "wind_speed": (, ),
+        "inclination": (85, 1),
+        "heading": (105, 3),
+        "rail_length": (5.2, 0.001),
+        # Parachute details
+        "cd_s_drogue": (0.885, ),
+        "cd_s_main": (, ),
+        "lag_rec": (0.5, 0.5 / 2),
+    }
+
+    # Environment conditions
+    env = Environment(
+        gravity=9.81,
+        latitude=32.939377,
+        longitude=-106.911986,
+        date=(2023, 6, 23, 17),
+        elevation=1480,
+    )
+
+    env.set_atmospheric_model(
+        type="Reanalysis",
+        file="tests/fixtures/acceptance/Juno3/spaceport_america_pressure_levels_2023_hourly.nc",
+        dictionary="ECMWF",
+    )
+
+    env.max_expected_height = 6000
+
+    # motor information
+    # add mandioca to fixtures.
+    L1395 = SolidMotor(
+        thrust_source="tests/fixtures/acceptance/NDRT_2020/ndrt_2020_motor_Cesaroni_4895L1395-P.eng",
+        burn_time=parameters.get("burn_time")[0],
+        dry_mass=1,
+        dry_inertia=(0, 0, 0),
+        center_of_dry_mass_position=0,
+        grains_center_of_mass_position=parameters.get("distance_rocket_propellant")[0],
+        grain_number=5,
+        grain_separation=parameters.get("grain_separation")[0],
+        grain_density=parameters.get("grain_density")[0],
+        grain_outer_radius=parameters.get("grain_outer_radius")[0],
+        grain_initial_inner_radius=parameters.get("grain_initial_inner_radius")[0],
+        grain_initial_height=parameters.get("grain_initial_height")[0],
+        nozzle_radius=parameters.get("nozzle_radius")[0],
+        throat_radius=parameters.get("throat_radius")[0],
+        interpolation_method="linear",
+        nozzle_position=parameters.get("distance_rocket_nozzle")[0],
+    )
+
diff --git a/tests/acceptance/test_ndrt_2020_rocket.py b/tests/acceptance/test_ndrt_2020_rocket.py
index a0b812f10..f0c19cd91 100644
--- a/tests/acceptance/test_ndrt_2020_rocket.py
+++ b/tests/acceptance/test_ndrt_2020_rocket.py
@@ -16,13 +16,6 @@ def test_ndrt_2020_rocket_data_asserts_acceptance():
     # Measured Altitude 4,320 ft or 1316.736 m
     # Drift: 2275 ft
 
-    # Importing libraries
-    import numpy as np
-    import pandas as pd
-    from scipy.signal import savgol_filter
-
-    from rocketpy import Environment, Flight, Function, Rocket, SolidMotor
-
     # Defining all parameters
     parameters = {
         # Mass Details