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import math
from engine import Engine
from fuel import Fuel
class Stage():
def __init__(self, name: str, stage_mass: int, engine: type[Engine], engine_number: int, max_engine_gimbaling_angle: int, fuel_type: type[Fuel], fuel_mass: int, x_drag_coefficient: float, x_cross_sectional_area: float, y_drag_coefficient: float, y_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.x_drag_coefficient = x_drag_coefficient
self.x_cross_sectional_area = x_cross_sectional_area
self.y_drag_coefficient = y_drag_coefficient
self.y_cross_sectional_area = y_cross_sectional_area
self.max_engine_gimbaling_angle = max_engine_gimbaling_angle
self.gimbal = 0 #one thing is gimbal another is rocket angle (TODO TOODODODODODODOD)
self.throttle = 100
self.engines_on = False
def total_mass(self):
return (self.stage_mass + self.fuel_mass)
def current_thrust(self, g: float, heading: int) -> (float, float):
if(self.engines_on and self.fuel_mass > 0):
total_thrust = self.engine.thrust(self.throttle, g) * self.engine_number
#gimbal and heading components
thrust_x = (math.sin(math.radians(self.gimbal + heading)) * total_thrust)
thrust_y = (math.cos(math.radians(self.gimbal + heading)) * total_thrust)
return (thrust_x, thrust_y)
else:
return (0, 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
def convert_y_component_to_total_with_gimbal(self, y_value):
return math.fabs(y_value / math.cos(math.radians(self.gimbal)))
#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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