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from engine import Engine
from fuel import Fuel
class Stage():
def __init__(self, name: str, stage_mass: int, engine: type[Engine], engine_number: int, fuel_type: type[Fuel], fuel_mass: int, drag_coefficient: float, cross_sectional_area: float):
self.name = name
self.stage_mass = stage_mass
self.engine = engine
self.engine_number = engine_number
self.fuel_type = fuel_type
self.fuel_mass = fuel_mass
self.drag_coefficient = drag_coefficient
self.cross_sectional_area = cross_sectional_area
self.throttle = 100
self.engines_on = False
def total_mass(self):
return (self.stage_mass + self.fuel_mass)
def current_thrust(self):
if(self.engines_on and self.fuel_mass > 0):
return self.engine.thrust(self.throttle) * self.engine_number
else:
return 0
def total_fuel_used(self, delta: int):
if(self.engines_on):
return self.engine.flow_rate(self.throttle) * self.engine_number * delta
else:
return 0
#total drag coefficient is just the upper stage
#engines on is just the lower stage
#thrust is just the lower stage
#fuel used is just lower stage
#when stage separation lower stage jetissoned
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