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202 lines (186 loc) · 9.49 KB
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from utils import Geometry, Integrator, Utility
from atmosphere import standardAtmosphere
from dataclasses import dataclass
from functools import partial
import numpy as np
import math
import sys
import time
@dataclass(frozen=False)
class LaunchSite:
altitude: float
@dataclass(frozen=False)
class Balloon:
mass: float
burst_diameter: float
drag_coefficient: float
gas: str
gas_volume: float
gas_moles: float = 0.0
def __post_init__(self):
self.gas_moles = self.gas_volume * 3.048 ** 3 / 22.413636 #ft^3 to L to mol
@dataclass(frozen=False)
class Payload:
mass: float
parachute_diameter: float
parachute_drag_coefficient: float
parachute_area: float = 0.0
def __post_init__(self):
self.parachute_area = self.parachute_diameter ** 2 * math.pi / 4
@dataclass(frozen=False)
class MissionProfile:
launch_site: LaunchSite
balloon: Balloon
payload: Payload
@dataclass(frozen=False)
class FlightProfile(MissionProfile):
times: list[float]
altitudes: list[float]
velocities: list[float]
accelerations: list[float]
forces: list[float]
pressures: list[float]
temperatures: list[float]
densities: list[float]
gravities: list[float]
burst_altitude: float
max_altitude: float
burst_time: float
flight_time: float
class Model:
helium_mm = 4.002602
atmosphere = standardAtmosphere()
def __init__(self, time_step, profiles, result):
self.time_step = time_step
self.profiles = profiles
self.result = result
def _ascent_acceleration(self, altitude, velocity, profile, mass):
net_force = self._ascent_net_force(altitude, velocity, profile, mass)
return net_force / mass
def _ascent_net_force(self, altitude, velocity, profile, mass):
pressure, temperature, density, gravity = self.atmosphere._Qualities(altitude)
volume = profile.balloon.gas_moles * (1.380622 * 6.022169) * temperature / pressure / 1000
buoyant_force = density * gravity * volume
weight_force = gravity * mass
drag_force = 0.5 * density * velocity ** 2 * profile.balloon.drag_coefficient * Geometry.sphere_cross_section(volume) * np.sign(velocity)
return buoyant_force - weight_force - drag_force
def _descent_acceleration(self, altitude, velocity, profile, mass):
net_force = self._descent_net_force(altitude, velocity, profile, mass)
return net_force / mass
def _descent_net_force(self, altitude, velocity, profile, mass):
_, _, density, gravity = self.atmosphere._Qualities(altitude)
buoyant_force = 0
weight_force = gravity * mass
drag_force = 0.5 * density * velocity ** 2 * profile.payload.parachute_drag_coefficient * profile.payload.parachute_area * np.sign(velocity)
return buoyant_force - weight_force - drag_force
def altitude_model(self, logging: bool = True, interval: int = 1):
start = time.perf_counter()
if logging:
padding = len(f" Modelling {len(self.profiles)} Profiles ...")
for i, profile in enumerate(self.profiles):
if logging:
sys.stdout.write(f"""\033[?25l{Utility.progress_bar(0, i, len(self.profiles), prefix=f" Modelling Profile {i + 1} ...".rjust(padding), suffix="Complete", bar_length=100)}
{Utility.progress_bar(0, 0, 1, prefix=f"Ascent ...".rjust(padding), suffix="Complete", bar_length=100)}
{Utility.progress_bar(0, 0, 1, prefix=f"Descent ...".rjust(padding), suffix="Complete", bar_length=100)}\x1b[2F\n""")
sys.stdout.flush()
times = [0]
logged_times = [0]
altitude = profile.launch_site.altitude
altitudes = [altitude]
velocity = 0
velocities = [velocity]
accelerations = [0]
forces = [0]
pressure, temperature, density, gravity = self.atmosphere._Qualities(altitudes[-1])
pressures = [pressure]
temperatures = [temperature]
densities = [density]
gravities = [gravity]
burst_volume = (4 / 3) * math.pi * (profile.balloon.burst_diameter / 2) ** 3
volume = profile.balloon.gas_moles * (1.380622 * 6.022169) * temperature / pressure / 1000
intial_volume = volume
ascent_mass = profile.payload.mass + profile.balloon.mass + (self.helium_mm * profile.balloon.gas_moles / 1000)
descent_mass = profile.payload.mass
while volume < burst_volume:
altitude, velocity, acceleration = Integrator.rk4_second_order(altitude, velocity, partial(self._ascent_acceleration, profile = profile, mass = ascent_mass), self.time_step)
if altitude <= altitudes[0]:
break
pressure, temperature, density, gravity = self.atmosphere._Qualities(altitude)
volume = profile.balloon.gas_moles * (1.380622 * 6.022169) * temperature / pressure / 1000
times.append(times[-1] + self.time_step)
if len(times) % interval == 0:
logged_times.append(logged_times[-1] + interval * self.time_step)
altitudes.append(altitude)
velocities.append(velocity)
accelerations.append(acceleration)
forces.append(self._ascent_net_force(altitude, velocity, profile, ascent_mass))
pressures.append(pressure)
temperatures.append(temperature)
densities.append(density)
gravities.append(gravity)
if logging:
sys.stdout.write(f"\x1b[K{Utility.progress_bar(intial_volume, volume, burst_volume, prefix=f"Ascent ...".rjust(padding), suffix="Complete", bar_length=100)}")
sys.stdout.flush()
if logging:
sys.stdout.write(f"{Utility.progress_bar(0, 1, 1, prefix=f"Ascent ...".rjust(padding), suffix="Complete", bar_length=100)}\x1b[E")
sys.stdout.flush()
if altitude <= altitudes[0]:
burst_altitude = float('nan')
burst_time = float('nan')
flight_time = times[-1]
self.result.append(FlightProfile(
profile.launch_site, profile.balloon, profile.payload,
logged_times, altitudes, velocities, accelerations, forces,
pressures, temperatures, densities, gravities,
burst_altitude, np.max(altitudes), burst_time, flight_time
))
if logging:
sys.stdout.write("\x1b[2F\x1b[J")
sys.stdout.flush()
continue
else:
burst_altitude = altitude
burst_time = times[-1]
if descent_mass == 0:
flight_time = times[-1]
self.result.append(FlightProfile(
profile.launch_site, profile.balloon, profile.payload,
logged_times, altitudes, velocities, accelerations, forces,
pressures, temperatures, densities, gravities,
burst_altitude, np.max(altitudes), burst_time, flight_time
))
if logging:
sys.stdout.write("\x1b[2F\x1b[J")
sys.stdout.flush()
continue
while altitude > altitudes[0]:
altitude, velocity, acceleration = Integrator.rk4_second_order(altitude, velocity, partial(self._descent_acceleration, profile = profile, mass = descent_mass), self.time_step)
pressure, temperature, density, gravity = self.atmosphere._Qualities(altitude)
times.append(times[-1] + self.time_step)
if len(times) % interval == 0:
logged_times.append(logged_times[-1] + interval * self.time_step)
accelerations.append(acceleration)
velocities.append(velocity)
altitudes.append(altitude)
forces.append(self._descent_net_force(altitude, velocity, profile, descent_mass))
pressures.append(pressure)
temperatures.append(temperature)
densities.append(density)
gravities.append(gravity)
if logging:
sys.stdout.write(f"\x1b[K{Utility.progress_bar(altitudes[0], altitude, burst_altitude, prefix=f"Descent ...".rjust(padding), suffix="Complete", ascending=False, bar_length=100)}")
sys.stdout.flush()
if logging:
sys.stdout.write("\x1b[2F\x1b[J\033[?25h")
sys.stdout.flush()
flight_time = times[-1]
self.result.append(FlightProfile(profile.launch_site, profile.balloon, profile.payload,
logged_times, altitudes, velocities, accelerations, forces,
pressures, temperatures, densities, gravities,
burst_altitude, np.max(altitudes), burst_time, flight_time))
end = time.perf_counter()
if logging:
sys.stdout.write(f"{Utility.progress_bar(0, 1, 1, prefix=f" Modelling {len(self.profiles)} Profiles ...".ljust(padding), suffix=f"Complete in {end - start:.2f} seconds\n", bar_length=100)}")
sys.stdout.flush()
else:
pass