diff options
Diffstat (limited to 'stage.py')
| -rw-r--r-- | stage.py | 18 |
1 files changed, 14 insertions, 4 deletions
diff --git a/stage.py b/stage.py index 0df1d52..b3140c8 100644 --- a/stage.py +++ b/stage.py @@ -1,8 +1,10 @@ +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, fuel_type: type[Fuel], fuel_mass: int, drag_coefficient: float, cross_sectional_area: float): + 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, drag_coefficient: float, cross_sectional_area: float): self.name = name self.stage_mass = stage_mass self.engine = engine @@ -12,17 +14,22 @@ class Stage(): self.drag_coefficient = drag_coefficient self.cross_sectional_area = cross_sectional_area + self.max_engine_gimbaling_angle = max_engine_gimbaling_angle + self.gimbal = 0 self.throttle = 100 self.engines_on = False def total_mass(self): return (self.stage_mass + self.fuel_mass) - def current_thrust(self, g: float): + def current_thrust(self, g: float) -> (float, float): if(self.engines_on and self.fuel_mass > 0): - return self.engine.thrust(self.throttle, g) * self.engine_number + total_thrust = self.engine.thrust(self.throttle, g) * self.engine_number + thrust_x = math.fabs(math.sin(math.radians(self.gimbal)) * total_thrust) + thrust_y = math.fabs(math.cos(math.radians(self.gimbal)) * total_thrust) + return (thrust_x, thrust_y) else: - return 0 + return (0, 0) def total_fuel_used(self, delta: int): if(self.engines_on): @@ -30,6 +37,9 @@ class Stage(): 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 |