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DOC: Add Defiance launch to flight examples graph.
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‎docs/examples/defiance_flight_sim.ipynb

Lines changed: 51 additions & 83 deletions
Original file line numberDiff line numberDiff line change
@@ -4,7 +4,7 @@
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"cell_type": "markdown",
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"metadata": {},
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"source": [
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"# Defiance Mk. IV\n",
7+
"# Defiance Mk. IV - University of Toronto Aerospace - 2024\n",
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"Launched in Launch Canada 2024. Defiance Mk. IV is the fourth rocket in the defiance series of hybrid rocket from University of Toronto Aerospace Team.\n",
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"\n",
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"Defiance Mk. IV set a new Canadian amateur rocketry record with a recorded apogee altitude of $9308.318 m$.\n",
@@ -106,18 +106,10 @@
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],
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"source": [
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"flight_date = datetime.date(2024, 8, 24)\n",
109-
"env = Environment(\n",
110-
" latitude = 47.966527,\n",
111-
" longitude = -81.87413,\n",
112-
" elevation = 1383.4\n",
113-
")\n",
109+
"env = Environment(latitude=47.966527, longitude=-81.87413, elevation=1383.4)\n",
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"\n",
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"env.set_date((flight_date.year, flight_date.month, flight_date.day, 0))\n",
116-
"env.set_atmospheric_model(\n",
117-
" type = \"custom_atmosphere\",\n",
118-
" wind_v = 1.0,\n",
119-
" wind_u = -2.9\n",
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")\n",
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"env.set_atmospheric_model(type=\"custom_atmosphere\", wind_v=1.0, wind_u=-2.9)\n",
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"\n",
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"env.info()"
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]
@@ -135,49 +127,52 @@
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"metadata": {},
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"outputs": [],
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"source": [
138-
"oxidizer_liq = Fluid(name = 'N2O_l', density = 960)\n",
139-
"oxidizer_gas = Fluid(name = 'N2O_g', density = 1.9277)\n",
130+
"oxidizer_liq = Fluid(name='N2O_l', density=960)\n",
131+
"oxidizer_gas = Fluid(name='N2O_g', density=1.9277)\n",
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"\n",
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"tank_shape = CylindricalTank(0.0665, 1.79)\n",
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"\n",
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"oxidizer_tank = MassFlowRateBasedTank(\n",
144-
" name = 'oxidizer_tank',\n",
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" geometry = tank_shape,\n",
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" flux_time = (6.5),\n",
147-
" liquid = oxidizer_liq,\n",
148-
" gas = oxidizer_gas,\n",
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" initial_liquid_mass = 17,\n",
150-
" initial_gas_mass = 0,\n",
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" liquid_mass_flow_rate_in = 0,\n",
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" liquid_mass_flow_rate_out = 17/6.5,\n",
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" gas_mass_flow_rate_in = 0,\n",
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" gas_mass_flow_rate_out = 0\n",
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" name='oxidizer_tank',\n",
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" geometry=tank_shape,\n",
138+
" flux_time=(6.5),\n",
139+
" liquid=oxidizer_liq,\n",
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" gas=oxidizer_gas,\n",
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" initial_liquid_mass=17,\n",
142+
" initial_gas_mass=0,\n",
143+
" liquid_mass_flow_rate_in=0,\n",
144+
" liquid_mass_flow_rate_out=17 / 6.5,\n",
145+
" gas_mass_flow_rate_in=0,\n",
146+
" gas_mass_flow_rate_out=0,\n",
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")\n",
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"\n",
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"''' Defining the thrust curve'''\n",
150+
"\n",
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"\n",
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"def thrust_fuction(t):\n",
159-
" return 5750 * 2**(-t / 200)\n",
153+
" return 5750 * 2 ** (-t / 200)\n",
154+
"\n",
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"\n",
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"hybrid_motor = HybridMotor(\n",
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" thrust_source = '../../data/rockets/defiance/Thrust_curve.csv',\n",
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" dry_mass = 13.832,\n",
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" dry_inertia = (1.801, 1.801, 0.0305),\n",
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" center_of_dry_mass_position = 780/1000,\n",
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" reshape_thrust_curve = False,\n",
167-
" grain_number = 1,\n",
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" grain_separation = 0,\n",
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" grain_outer_radius = 0.0665,\n",
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" grain_initial_inner_radius = 0.061,\n",
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" grain_initial_height = 1.25,\n",
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" grain_density = 920,\n",
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" nozzle_radius = 0.0447,\n",
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" throat_radius = 0.0234,\n",
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" interpolation_method = 'linear',\n",
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" grains_center_of_mass_position = 0.377,\n",
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" coordinate_system_orientation = 'nozzle_to_combustion_chamber',\n",
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" thrust_source='../../data/rockets/defiance/Thrust_curve.csv',\n",
158+
" dry_mass=13.832,\n",
159+
" dry_inertia=(1.801, 1.801, 0.0305),\n",
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" center_of_dry_mass_position=780 / 1000,\n",
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" reshape_thrust_curve=False,\n",
162+
" grain_number=1,\n",
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" grain_separation=0,\n",
164+
" grain_outer_radius=0.0665,\n",
165+
" grain_initial_inner_radius=0.061,\n",
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" grain_initial_height=1.25,\n",
167+
" grain_density=920,\n",
168+
" nozzle_radius=0.0447,\n",
169+
" throat_radius=0.0234,\n",
170+
" interpolation_method='linear',\n",
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" grains_center_of_mass_position=0.377,\n",
172+
" coordinate_system_orientation='nozzle_to_combustion_chamber',\n",
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")\n",
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"\n",
180-
"hybrid_motor.add_tank(tank = oxidizer_tank, position = 2.2)"
175+
"hybrid_motor.add_tank(tank=oxidizer_tank, position=2.2)"
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]
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},
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{
@@ -205,53 +200,30 @@
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],
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"source": [
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"defiance = Rocket(\n",
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" radius = 0.07,\n",
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" mass = 37.211,\n",
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" radius=0.07,\n",
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" mass=37.211,\n",
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" # inertia = (180.142, 180.142, 0.262),\n",
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" inertia = (94.14, 94.14, 0.09),\n",
212-
" center_of_mass_without_motor = 3.29,\n",
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" power_off_drag = '../../data/rockets/defiance/DragCurve.csv',\n",
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" power_on_drag = '../../data/rockets/defiance/DragCurve.csv',\n",
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" coordinate_system_orientation = 'tail_to_nose'\n",
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" inertia=(94.14, 94.14, 0.09),\n",
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" center_of_mass_without_motor=3.29,\n",
208+
" power_off_drag='../../data/rockets/defiance/DragCurve.csv',\n",
209+
" power_on_drag='../../data/rockets/defiance/DragCurve.csv',\n",
210+
" coordinate_system_orientation='tail_to_nose',\n",
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")\n",
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"\n",
218-
"defiance.add_motor(hybrid_motor, position = 0.2)\n",
213+
"defiance.add_motor(hybrid_motor, position=0.2)\n",
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"\n",
220-
"defiance.add_nose(\n",
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" length = 0.563,\n",
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" kind = \"vonKarman\",\n",
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" position = 4.947\n",
224-
")\n",
215+
"defiance.add_nose(length=0.563, kind=\"vonKarman\", position=4.947)\n",
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"\n",
226217
"defiance.add_trapezoidal_fins(\n",
227-
" n = 3,\n",
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" span = 0.115,\n",
229-
" root_chord = 0.4,\n",
230-
" tip_chord = 0.2,\n",
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" position = 0.175\n",
218+
" n=3, span=0.115, root_chord=0.4, tip_chord=0.2, position=0.175\n",
232219
")\n",
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"\n",
234-
"defiance.add_tail(\n",
235-
" top_radius = 0.07,\n",
236-
" bottom_radius = 0.064,\n",
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" length = 0.0597,\n",
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" position = 0.1\n",
239-
")\n",
221+
"defiance.add_tail(top_radius=0.07, bottom_radius=0.064, length=0.0597, position=0.1)\n",
240222
"\n",
241-
"defiance.add_parachute(\n",
242-
" name = 'main',\n",
243-
" cd_s = 2.2,\n",
244-
" trigger = 305,\n",
245-
" sampling_rate = 100,\n",
246-
" lag = 0\n",
247-
")\n",
223+
"defiance.add_parachute(name='main', cd_s=2.2, trigger=305, sampling_rate=100, lag=0)\n",
248224
"\n",
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"defiance.add_parachute(\n",
250-
" name ='drogue',\n",
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" cd_s = 1.55,\n",
252-
" trigger = 'apogee',\n",
253-
" sampling_rate = 100,\n",
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" lag = 0\n",
226+
" name='drogue', cd_s=1.55, trigger='apogee', sampling_rate=100, lag=0\n",
255227
")"
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]
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},
@@ -296,11 +268,7 @@
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],
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"source": [
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"test_flight = Flight(\n",
299-
" rocket = defiance,\n",
300-
" environment = env,\n",
301-
" inclination = 85,\n",
302-
" heading = 90,\n",
303-
" rail_length = 10\n",
271+
" rocket=defiance, environment=env, inclination=85, heading=90, rail_length=10\n",
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")\n",
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"\n",
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"test_flight.prints.apogee_conditions()\n",

‎docs/examples/index.rst

Lines changed: 4 additions & 2 deletions
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@@ -25,10 +25,11 @@ apogee of some rockets.
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"Genesis (2023)": (3076.45, 2916),
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"Camoes (2023)": (3003.28, 3015),
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"Juno III (2023)": (3026.05, 3213),
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"Halcyon (2023)": (3212.775, 3450),
28+
"Halcyon (2023)": (3212.78, 3450),
29+
"Defiance Mk.IV (2024)": (9238.01, 9308.32),
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}
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31-
max_apogee = 4500
32+
max_apogee = 10000
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3334
# Extract data
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simulated = [sim for sim, meas in results.values()]
@@ -80,4 +81,5 @@ In the next sections you will find the simulations of the rockets listed above.
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cavour_flight_sim.ipynb
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genesis_flight_sim.ipynb
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camoes_flight_sim.ipynb
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defiance_flight_sim.ipynb
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