Merge pull request #140 from NCSU-High-Powered-Rocketry-Club/legacy-c…

…onfig

Switch to Legacy Launch 1 configuration

.github/workflows/integration_tests.yml

@@ -30,7 +30,7 @@ jobs:
           python-version-file: "pyproject.toml"
 
       - name: Install the project
-        run: uv sync
+        run: uv sync --verbose --group dev
 
       - name: Run integration tests
         timeout-minutes: 3

.github/workflows/unit_tests.yml

@@ -30,7 +30,7 @@
             python-version-file: "pyproject.toml"
 
         - name: Install the project
-          run: uv sync
+          run: uv sync --verbose --group dev
 
         - name: Run tests with coverage
           run: |

airbrakes/constants.py

@@ -29,7 +29,7 @@ class ServoExtension(Enum):
     MIN_EXTENSION = -0.75
     MAX_EXTENSION = 0.055
     MIN_NO_BUZZ = -0.72
-    MAX_NO_BUZZ = 0.05
+    MAX_NO_BUZZ = 0.01
 
 
 # -------------------------------------------------------
@@ -166,7 +166,7 @@ class DisplayEndingType(StrEnum):
 motor has stopped burning if the current velocity is less than a percentage of the max velocity."""
 
 # ----------------- Coasting to Freefall -----------------
-TARGET_ALTITUDE_METERS = 1000
+TARGET_ALTITUDE_METERS = 1
 """The target altitude in meters that we want the rocket to reach. This is used with our bang-bang
 controller to determine when to extend and retract the airbrakes."""
 

airbrakes/simulation/sim_config.py

@@ -96,7 +96,7 @@ def __init__(
     motor="AeroTech_J500G",
     airbrake_retracted_cd=np.array([[0.05, 0.2, 0.3], [0.5, 0.445, 0.43]]),
     airbrake_extended_cd=np.array([[0.05, 0.2, 0.3], [0.65, 0.595, 0.58]]),
-    rocket_mass=np.float64(5.103),
+    rocket_mass=np.float64(5.76),
     reference_area=np.float64(0.008107),
     airbrakes_reference_area=np.float64(0.00487741),
     air_temperature=np.float64(10),

launch_data/README.md

@@ -10,7 +10,12 @@ This folder contains the launch data of actual previous flights. These are used
 3. `genesis_launch_1.csv`: This was our first attempt of a control launch with the Genesis subscale rocket. We tried to have it extend its airbrakes for most of coast and then retract them, but later analysis proved that airbrakes didn't deploy during coast. Additionally, the LandedState was incorrectly detected, so for convenience ~100 mb of useless data has been cropped out of this file.
 The timestamps of the LandedState packets were synced with the timestamps of the last packet in the file. See #91 for more details.
 4. `genesis_launch_2.csv`: This was our second attempt of a control launch with Genesis. For this one we told the airbrakes to deploy once at around the start of CoastState and did not tell them to retract at all. When we recovered the rocket, the fins were extended, by analysis of launch data shows that the airbrakes didn't deploy in CoastState, and most likely deployed sometime either in FreeFall or once the rocket hit the ground. LandedState was mostly correctly detected. See #91 for more details.
+5. `legacy_launch_1.csv`: This was the first time airbrakes physically deployed! The airbrakes were pre-programmed to stay deployed after apogee convergence. 
+6. `legacy_launch_2.csv`: This was the second time airbrakes physically deployed! This was a control launch where the we planned to hit a target apogee.
 
+## Videos
+
+There is a video of the launch from the rocket's perspective in the `videos` folder.
 
 ## Metadata
 

launch_data/metadata.json

@@ -111,5 +111,61 @@
             "apogee_meters": 463.62
         },
         "flight_description": "Second flight of apogee prediction code. This was very similar to first flight and airbrakes most likely failed to deploy at the intended time. See https://github.com/NCSU-High-Powered-Rocketry-Club/AirbrakesV2/issues/91 for more details."
+    },
+    "legacy_launch_1.csv": {
+        "date": "2025-01-25 12:11:35.000",
+        "launch_site": {
+            "air_temperature_celsius": 4.11,  
+            "air_pressure_mb": null,
+            "wind_speed_kmh": null,
+            "wind_speed_direction": null,
+            "launch_coordinates": {
+                "latitiude": 35.1758000,
+                "longitude": -76.8283400
+            },
+            "landed_coordinates:": {
+                "latitude": null,
+                "longitude": null
+            },
+            "launch_rod_angle": 5.0
+        },
+        "imu_details": {
+            "imu_model": "Parker-LORD 3DM-CX5-15",
+            "raw_packet_frequency": 1000.0,
+            "est_packet_frequency": 500.0
+        },
+        "flight_data": {
+            "log_buffer_index": 5000,
+            "apogee_meters": null
+        },
+        "flight_description": ""
+    },
+    "legacy_launch_2.csv": {
+        "date": "2025-01-25 15:11:35.000",
+        "launch_site": {
+            "air_temperature_celsius": 3.11,  
+            "air_pressure_mb": null,
+            "wind_speed_kmh": null,
+            "wind_speed_direction": null,
+            "launch_coordinates": {
+                "latitiude": 35.1758000,
+                "longitude": -76.8283400
+            },
+            "landed_coordinates:": {
+                "latitude": null,
+                "longitude": null
+            },
+            "launch_rod_angle": 5.0
+        },
+        "imu_details": {
+            "imu_model": "Parker-LORD 3DM-CX5-15",
+            "raw_packet_frequency": 1000.0,
+            "est_packet_frequency": 500.0
+        },
+        "flight_data": {
+            "log_buffer_index": 5000,
+            "apogee_meters": null
+        },
+        "flight_description": ""
     }
 }

pyproject.toml

@@ -2,7 +2,7 @@
 name = "AirbrakesV2"
 description = "Logic for airbrakes as a part of the NASA Student Launch Competition"
 requires-python = ">=3.13"
-version = "0.1.0"
+version = "1.1.0"
 readme = "README.md"
 dependencies = [
     "gpiozero",

tests/conftest.py

@@ -28,6 +28,8 @@
 LAUNCH_DATA = list(Path("launch_data").glob("*.csv"))
 # Remove the genesis_launch_1.csv file since it's almost the same as genesis_launch_2.csv:
 LAUNCH_DATA.remove(Path("launch_data/genesis_launch_1.csv"))
+# Remove the legacy_launch_2.csv file since it's almost the same as legacy_launch_1.csv:
+# LAUNCH_DATA.remove(Path("launch_data/legacy_launch_2.csv"))
 # Use the filenames as the ids for the fixtures:
 LAUNCH_DATA_IDS = [log.stem for log in LAUNCH_DATA]
 
@@ -132,6 +134,8 @@ def target_altitude(request):
         return 1800.0  # actual apogee was about 1854m
     if launch_name == "genesis_launch_2":
         return 413.0  # actual apogee was about 462m
+    # if launch_name == "legacy_launch_1":
+    #     return 600.0 # actual apogee was about 650m
     return 1000.0  # Default altitude