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from stage import Stage
class Rocket():
def __init__(self, name: str, stages: [type[Stage]], payload_mass: int):
self.name = name
self.stages = stages
self.stages_spent = 0
self.payload_mass = payload_mass
def current_stage(self) -> type[Stage]:
return self.stages[0]
def top_stage(self) -> type[Stage]:
return self.stages[len(self.stages) - 1] #TODO: drag coef and cross sectional area of top stage
def perform_stage_separation(self, engines_on: bool):
if len(self.stages) > 1:
self.stages.pop(0)
self.stages_spent += 1
self.current_stage().engines_on = engines_on
def total_mass(self):
total_mass = self.payload_mass
for stage in self.stages:
total_mass += stage.total_mass()
return total_mass
def total_fuel(self):
fuel_mass = 0
for stage in self.stages:
fuel_mass += stage.fuel_mass
return fuel_mass
def s_cross_sectional_area(self):
return self.top_stage().cross_sectional_area
def s_drag_coefficient(self):
return self.top_stage().drag_coefficient
#TODO: IMPLEMENT rocket_x_drag_coefficient() that adds the x drag coefficient of all stages, same with cross sectional area
def __str__(self):
return "eue"
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