1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
|
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 = self.body.radius #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))
g = self.body.g(G=self.universe.G, height=self.rocket_altitude())
print("g: " + str(g))
force_x = 0
force_y = 0
if fuel_used > 0:
total_thrust = current_stage.current_thrust(g, 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
gravitational_force_y = g * self.rocket.total_mass()
print("Gravity Y: " + str(gravitational_force_y))
#Remove gravity from force
force_y -= gravitational_force_y
curr_atmospheric_density = self.body.atmosphere.density_at_height(self.rocket_altitude(), g)
print("Atmosphere density: " + str(curr_atmospheric_density))
#TODO: cross sectional area and drag coef for x should b different
drag_force_x = (1/2) * curr_atmospheric_density * (self.speed_x ** 2) * self.rocket.rocket_x_drag_coefficient() * self.rocket.rocket_x_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) * curr_atmospheric_density * (self.speed_y ** 2) * self.rocket.rocket_y_drag_coefficient() * self.rocket.rocket_y_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)
#update position based on velocity and delta
self.x += self.speed_x * delta
self.y += self.speed_y * delta
if self.rocket_altitude() < 0:
#undo positional changes
self.x -= self.speed_x * delta
self.y -= self.speed_y * delta
self.speed_x = 0
self.speed_y = 0
print("Speed x: " + str(self.speed_x))
print("Speed y: " + str(self.speed_y))
print("X: " + str(self.x))
print("Y: " + str(self.y))
ref_vec = (0, 1)
acc_vec = (self.speed_x, self.speed_y)
dot = (acc_vec[0] * ref_vec[0]) + (acc_vec[1] * ref_vec[1])
det = (acc_vec[0] * ref_vec[1]) - (acc_vec[1] * ref_vec[0])
self.heading = math.degrees(math.atan2(det, dot))
print("Heading: " + str(self.heading))
print("Total Simulation Time: " + str(self.time))
print("")
self.ticks += 1
self.time += delta
def rocket_altitude(self):
#take into account body and allow for 360 height
altitude = math.sqrt(self.x**2 + self.y**2)
altitude -= self.body.radius
return altitude
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)
|
