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CopilotaZira371
Copilot
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aZira371
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docs: update multistage notebook payload setup
Agent-Logs-Url: https://github.com/aZira371/RocketPy/sessions/fbe5846f-e62e-4267-8d52-191ce170c08b Co-authored-by: aZira371 <99824864+aZira371@users.noreply.github.com>
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‎docs/multistage_example.ipynb‎

Lines changed: 143 additions & 100 deletions
Original file line numberDiff line numberDiff line change
@@ -30,22 +30,26 @@
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"outputs": [],
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"source": [
3232
"import datetime as dt\n",
33+
"from pathlib import Path\n",
3334
"\n",
35+
"import rocketpy as rp\n",
3436
"from rocketpy import (\n",
3537
" Attachment,\n",
3638
" Deployable,\n",
3739
" DeploymentEvent,\n",
3840
" Environment,\n",
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" FlightBody,\n",
3942
" IgnitionEvent,\n",
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" Mission,\n",
4144
" MissionExecutor,\n",
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" Parachute,\n",
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" Rocket,\n",
4347
" RocketAdapter,\n",
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" SolidMotor,\n",
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" Stage,\n",
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" StageSeparationEvent,\n",
4751
")\n",
48-
"from rocketpy.plots.compare import CompareFlights"
52+
"from rocketpy.plots.compare import CompareFlights\n"
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]
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},
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{
@@ -100,91 +104,143 @@
100104
"metadata": {},
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"outputs": [],
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"source": [
103-
"def build_pro75_m1670():\n",
104-
" return SolidMotor(\n",
105-
" thrust_source=\"data/motors/cesaroni/Cesaroni_M1670.eng\",\n",
106-
" burn_time=3.9,\n",
107-
" dry_mass=1.815,\n",
108-
" dry_inertia=(0.125, 0.125, 0.002),\n",
109-
" center_of_dry_mass_position=0.317,\n",
110-
" nozzle_position=0,\n",
111-
" grain_number=5,\n",
112-
" grain_density=1815,\n",
113-
" nozzle_radius=33 / 1000,\n",
114-
" throat_radius=11 / 1000,\n",
115-
" grain_separation=5 / 1000,\n",
116-
" grain_outer_radius=33 / 1000,\n",
117-
" grain_initial_height=120 / 1000,\n",
118-
" grains_center_of_mass_position=0.397,\n",
119-
" grain_initial_inner_radius=15 / 1000,\n",
120-
" interpolation_method=\"linear\",\n",
121-
" coordinate_system_orientation=\"nozzle_to_combustion_chamber\",\n",
122-
" )\n",
107+
"data_directory = Path(rp.__file__).resolve().parent.parent / \"data\"\n",
108+
"motor_file = data_directory / \"motors\" / \"cesaroni\" / \"Cesaroni_M1670.eng\"\n",
109+
"power_off_drag_file = (\n",
110+
" data_directory / \"rockets\" / \"calisto\" / \"powerOffDragCurve.csv\"\n",
111+
")\n",
112+
"power_on_drag_file = data_directory / \"rockets\" / \"calisto\" / \"powerOnDragCurve.csv\"\n",
123113
"\n",
114+
"first_stage_motor = SolidMotor(\n",
115+
" thrust_source=str(motor_file),\n",
116+
" burn_time=3.9,\n",
117+
" dry_mass=1.815,\n",
118+
" dry_inertia=(0.125, 0.125, 0.002),\n",
119+
" center_of_dry_mass_position=0.317,\n",
120+
" nozzle_position=0,\n",
121+
" grain_number=5,\n",
122+
" grain_density=1815,\n",
123+
" nozzle_radius=33 / 1000,\n",
124+
" throat_radius=11 / 1000,\n",
125+
" grain_separation=5 / 1000,\n",
126+
" grain_outer_radius=33 / 1000,\n",
127+
" grain_initial_height=120 / 1000,\n",
128+
" grains_center_of_mass_position=0.397,\n",
129+
" grain_initial_inner_radius=15 / 1000,\n",
130+
" interpolation_method=\"linear\",\n",
131+
" coordinate_system_orientation=\"nozzle_to_combustion_chamber\",\n",
132+
")\n",
124133
"\n",
125-
"def build_stage_rocket(name, dry_mass, motor_position, fin_position, nose_position):\n",
126-
" rocket = Rocket(\n",
127-
" radius=0.0635,\n",
128-
" mass=dry_mass,\n",
129-
" inertia=(6.321, 6.321, 0.034),\n",
130-
" power_off_drag=\"data/rockets/calisto/powerOffDragCurve.csv\",\n",
131-
" power_on_drag=\"data/rockets/calisto/powerOnDragCurve.csv\",\n",
132-
" center_of_mass_without_motor=0,\n",
133-
" coordinate_system_orientation=\"tail_to_nose\",\n",
134-
" )\n",
135-
" rocket.name = name\n",
136-
" rocket.add_motor(build_pro75_m1670(), position=motor_position)\n",
137-
" rocket.set_rail_buttons(\n",
138-
" upper_button_position=0.0818,\n",
139-
" lower_button_position=-0.618,\n",
140-
" angular_position=45,\n",
141-
" )\n",
142-
" rocket.add_nose(length=0.55829, kind=\"von karman\", position=nose_position)\n",
143-
" rocket.add_trapezoidal_fins(\n",
144-
" n=4,\n",
145-
" root_chord=0.120,\n",
146-
" tip_chord=0.060,\n",
147-
" span=0.110,\n",
148-
" position=fin_position,\n",
149-
" cant_angle=0.5,\n",
150-
" )\n",
151-
" rocket.add_tail(\n",
152-
" top_radius=0.0635,\n",
153-
" bottom_radius=0.0435,\n",
154-
" length=0.060,\n",
155-
" position=-1.194656,\n",
156-
" )\n",
157-
" return rocket\n",
134+
"second_stage_motor = SolidMotor(\n",
135+
" thrust_source=str(motor_file),\n",
136+
" burn_time=3.9,\n",
137+
" dry_mass=1.815,\n",
138+
" dry_inertia=(0.125, 0.125, 0.002),\n",
139+
" center_of_dry_mass_position=0.317,\n",
140+
" nozzle_position=0,\n",
141+
" grain_number=5,\n",
142+
" grain_density=1815,\n",
143+
" nozzle_radius=33 / 1000,\n",
144+
" throat_radius=11 / 1000,\n",
145+
" grain_separation=5 / 1000,\n",
146+
" grain_outer_radius=33 / 1000,\n",
147+
" grain_initial_height=120 / 1000,\n",
148+
" grains_center_of_mass_position=0.397,\n",
149+
" grain_initial_inner_radius=15 / 1000,\n",
150+
" interpolation_method=\"linear\",\n",
151+
" coordinate_system_orientation=\"nozzle_to_combustion_chamber\",\n",
152+
")\n",
158153
"\n",
154+
"first_stage_rocket = Rocket(\n",
155+
" radius=0.0635,\n",
156+
" mass=14.426,\n",
157+
" inertia=(6.321, 6.321, 0.034),\n",
158+
" power_off_drag=str(power_off_drag_file),\n",
159+
" power_on_drag=str(power_on_drag_file),\n",
160+
" center_of_mass_without_motor=0,\n",
161+
" coordinate_system_orientation=\"tail_to_nose\",\n",
162+
")\n",
163+
"first_stage_rocket.name = \"First Stage\"\n",
164+
"first_stage_rocket.add_motor(first_stage_motor, position=-1.255)\n",
165+
"first_stage_rocket.set_rail_buttons(\n",
166+
" upper_button_position=0.0818,\n",
167+
" lower_button_position=-0.618,\n",
168+
" angular_position=45,\n",
169+
")\n",
170+
"first_stage_rocket.add_nose(length=0.55829, kind=\"von karman\", position=1.278)\n",
171+
"first_stage_rocket.add_trapezoidal_fins(\n",
172+
" n=4,\n",
173+
" root_chord=0.120,\n",
174+
" tip_chord=0.060,\n",
175+
" span=0.110,\n",
176+
" position=-1.04956,\n",
177+
" cant_angle=0.5,\n",
178+
")\n",
179+
"first_stage_rocket.add_tail(\n",
180+
" top_radius=0.0635,\n",
181+
" bottom_radius=0.0435,\n",
182+
" length=0.060,\n",
183+
" position=-1.194656,\n",
184+
")\n",
159185
"\n",
160-
"def build_payload_rocket(name):\n",
161-
" payload = Rocket(\n",
162-
" radius=0.055,\n",
163-
" mass=4.5,\n",
164-
" inertia=(0.25, 0.25, 0.03),\n",
165-
" power_off_drag=0.55,\n",
166-
" power_on_drag=0.55,\n",
167-
" center_of_mass_without_motor=0,\n",
168-
" coordinate_system_orientation=\"tail_to_nose\",\n",
169-
" )\n",
170-
" payload.name = name\n",
171-
" payload.add_parachute(\n",
172-
" \"Payload Drogue\",\n",
173-
" cd_s=0.35,\n",
174-
" trigger=\"apogee\",\n",
175-
" sampling_rate=105,\n",
176-
" lag=1.0,\n",
177-
" noise=(0, 4.0, 0.2),\n",
178-
" )\n",
179-
" payload.add_parachute(\n",
180-
" \"Payload Main\",\n",
181-
" cd_s=3.5,\n",
182-
" trigger=700,\n",
183-
" sampling_rate=105,\n",
184-
" lag=1.0,\n",
185-
" noise=(0, 4.0, 0.2),\n",
186-
" )\n",
187-
" return payload"
186+
"second_stage_rocket = Rocket(\n",
187+
" radius=0.0635,\n",
188+
" mass=9.500,\n",
189+
" inertia=(6.321, 6.321, 0.034),\n",
190+
" power_off_drag=str(power_off_drag_file),\n",
191+
" power_on_drag=str(power_on_drag_file),\n",
192+
" center_of_mass_without_motor=0,\n",
193+
" coordinate_system_orientation=\"tail_to_nose\",\n",
194+
")\n",
195+
"second_stage_rocket.name = \"Second Stage\"\n",
196+
"second_stage_rocket.add_motor(second_stage_motor, position=-1.000)\n",
197+
"second_stage_rocket.set_rail_buttons(\n",
198+
" upper_button_position=0.0818,\n",
199+
" lower_button_position=-0.618,\n",
200+
" angular_position=45,\n",
201+
")\n",
202+
"second_stage_rocket.add_nose(length=0.55829, kind=\"von karman\", position=1.050)\n",
203+
"second_stage_rocket.add_trapezoidal_fins(\n",
204+
" n=4,\n",
205+
" root_chord=0.120,\n",
206+
" tip_chord=0.060,\n",
207+
" span=0.110,\n",
208+
" position=-0.920,\n",
209+
" cant_angle=0.5,\n",
210+
")\n",
211+
"second_stage_rocket.add_tail(\n",
212+
" top_radius=0.0635,\n",
213+
" bottom_radius=0.0435,\n",
214+
" length=0.060,\n",
215+
" position=-1.194656,\n",
216+
")\n",
217+
"\n",
218+
"payload_body = FlightBody(\n",
219+
" name=\"Payload\",\n",
220+
" geometry=0.055,\n",
221+
" mass_model=lambda t: 4.5,\n",
222+
" inertia_model=lambda t: (0.25, 0.25, 0.03, 0.0, 0.0, 0.0),\n",
223+
" center_of_mass_model=lambda t: 0.0,\n",
224+
" recovery_systems=[\n",
225+
" Parachute(\n",
226+
" name=\"Payload Drogue\",\n",
227+
" cd_s=0.35,\n",
228+
" trigger=\"apogee\",\n",
229+
" sampling_rate=105,\n",
230+
" lag=1.0,\n",
231+
" noise=(0, 4.0, 0.2),\n",
232+
" ),\n",
233+
" Parachute(\n",
234+
" name=\"Payload Main\",\n",
235+
" cd_s=3.5,\n",
236+
" trigger=700,\n",
237+
" sampling_rate=105,\n",
238+
" lag=1.0,\n",
239+
" noise=(0, 4.0, 0.2),\n",
240+
" ),\n",
241+
" ],\n",
242+
" coordinate_system_orientation=\"tail_to_nose\",\n",
243+
")\n"
188244
]
189245
},
190246
{
@@ -202,21 +258,6 @@
202258
"metadata": {},
203259
"outputs": [],
204260
"source": [
205-
"first_stage_rocket = build_stage_rocket(\n",
206-
" name=\"First Stage\",\n",
207-
" dry_mass=14.426,\n",
208-
" motor_position=-1.255,\n",
209-
" fin_position=-1.04956,\n",
210-
" nose_position=1.278,\n",
211-
")\n",
212-
"\n",
213-
"second_stage_rocket = build_stage_rocket(\n",
214-
" name=\"Second Stage\",\n",
215-
" dry_mass=9.500,\n",
216-
" motor_position=-1.000,\n",
217-
" fin_position=-0.920,\n",
218-
" nose_position=1.050,\n",
219-
")\n",
220261
"second_stage_rocket.add_parachute(\n",
221262
" \"Second Stage Main\",\n",
222263
" cd_s=5.0,\n",
@@ -226,7 +267,9 @@
226267
" noise=(0, 6.0, 0.25),\n",
227268
")\n",
228269
"\n",
229-
"payload_rocket = build_payload_rocket(name=\"Payload\")"
270+
"print(f\"Using motor file: {motor_file}\")\n",
271+
"print(f\"Using drag curve files: {power_off_drag_file.name}, {power_on_drag_file.name}\")\n",
272+
"print(f\"Payload body type: {type(payload_body).__name__}\")\n"
230273
]
231274
},
232275
{
@@ -296,14 +339,14 @@
296339
"\n",
297340
"payload = Deployable(\n",
298341
" name=\"payload\",\n",
299-
" body=RocketAdapter(payload_rocket),\n",
342+
" body=payload_body,\n",
300343
" attachment=payload_attachment,\n",
301344
" deployment_event=payload_deploy_event,\n",
302345
")\n",
303346
"\n",
304347
"mission.add_stage(first_stage)\n",
305348
"mission.add_stage(second_stage)\n",
306-
"mission.add_deployable(payload)"
349+
"mission.add_deployable(payload)\n"
307350
]
308351
},
309352
{

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