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import math
from dataclasses import dataclass
from universe import Universe
from body import Body
from rocket import Rocket
@dataclass
class Simulation_Snapshot:
universe: type[Universe]
body: type[Body]
rocket: type[Rocket]
class Simulation():
def __init__(self, universe: type[Universe], body: type[Body], rocket: type[Rocket]):
self.ticks = 0
self.time = 0
self.universe = universe
self.body = body
self.rocket = rocket
self.x = 0#TODO
self.y = 0 #TODO: we need to make it so there is height() to calc height based on x and y
self.speed_x = 0
self.speed_y = 0
self.acceleration_x = 0
self.acceleration_y = 0
self.heading = 0
#simulation logic
def tick(self, delta: int) -> None:
current_stage = self.rocket.current_stage()
#calculate upwards force by fuel
fuel_used = current_stage.total_fuel_used(delta)
if current_stage.fuel_mass < fuel_used:
fuel_used = current_stage.fuel_mass
current_stage.fuel_mass -= fuel_used
print("Fuel remaining: " + str(current_stage.fuel_mass))
force_x = 0
force_y = 0
if fuel_used > 0:
total_thrust = current_stage.current_thrust(self.body.g(self.universe.G, self.y), self.heading)
force_x = total_thrust[0]
force_y = total_thrust[1]
print("Thrust X: " + str(force_x))
print("Thrust Y: " + str(force_y))
print("BODY MASS: " + str(self.body.mass()))
print("ROCKET TOTAL MASS: " + str(self.rocket.total_mass()))
#calculate downwards force by drag and gravity
print("g: " + str(self.body.g(G=self.universe.G, height=self.y)))
gravitational_force = self.body.g(G=self.universe.G, height=self.y) * self.rocket.total_mass()
print("Gravity: " + str(gravitational_force))
#Remove gravity from force
force_y -= gravitational_force
print("Atmosphere density: " + str(self.body.atmosphere.density_at_height(self.y, self.body.g(G=self.universe.G, height=self.y))))
#TODO: cross sectional area and drag coef for x should b different
drag_force_x = (1/2) * self.body.atmosphere.density_at_height(self.y, self.body.g(G=self.universe.G, height=self.y)) * (self.speed_x ** 2) * self.rocket.s_drag_coefficient() * self.rocket.s_cross_sectional_area()
#drag goes against speed
if force_x < 0:
drag_force_x *= -1
print("Drag X: " + str(drag_force_x))
#https://www.grc.nasa.gov/www/k-12/airplane/drageq.html
drag_force_y = (1/2) * self.body.atmosphere.density_at_height(self.y, self.body.g(G=self.universe.G, height=self.y)) * (self.speed_y ** 2) * self.rocket.s_drag_coefficient() * self.rocket.s_cross_sectional_area()
#drag goes against speed
if force_y < 0:
drag_force_y *= -1
print("Drag Y: " + str(drag_force_y))
#remove drag
force_x -= drag_force_x
force_y -= drag_force_y
print("Total Force X: " + str(force_x))
print("Total Force Y: " + str(force_y))
self.acceleration_x = force_x / self.rocket.total_mass()
self.acceleration_y = force_y / self.rocket.total_mass()
print("Acceleration x: " + str(self.acceleration_x))
print("Acceleration y: " + str(self.acceleration_y))
self.speed_x = self.speed_x + (self.acceleration_x * delta)
self.speed_y = self.speed_y + (self.acceleration_y * delta)
print("Speed x: " + str(self.speed_x))
print("Speed y: " + str(self.speed_y))
#TODO: HEADING behaves a bit weird, just a bit and it goes forever and hard to cancel. WELL CALCULATED OR IMPLEMENTED?
#speedx / speedy
#1 = 45
#-1 = -45
#0 = 90
self.heading = math.degrees(self.speed_x / self.speed_y) #TODO? con speed, y luego heading influences thrust (gimbal), so pass as a parameter to func
print("Heading: " + str(self.heading))
#update position based on velocity and delta
self.x += self.speed_x * delta
#in future u should be able to go negative y (y and height are different)
self.y += self.speed_y * delta
if self.y < 0:
self.y = 0
self.speed_y = 0
print("X: " + str(self.x))
print("Y: " + str(self.y))
print("Total Simulation Time: " + str(self.time))
print("")
self.ticks += 1
self.time += delta
def snapshot(self) -> Simulation_Snapshot:
return Simulation_Snapshot(self.universe, self.body, self.rocket)
def str_snapshot(self) -> str:
return str(self.universe) + "\n" + \
str(self.body) + "\n" + \
str(self.rocket)
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