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physics_sim.py
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physics_sim.py
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import numpy as np
import csv
def C(x):
return np.cos(x)
def S(x):
return np.sin(x)
def earth_to_body_frame(ii, jj, kk):
# C^b_n
R = [[C(kk) * C(jj), C(kk) * S(jj) * S(ii) - S(kk) * C(ii), C(kk) * S(jj) * C(ii) + S(kk) * S(ii)],
[S(kk) * C(jj), S(kk) * S(jj) * S(ii) + C(kk) * C(ii), S(kk) * S(jj) * C(ii) - C(kk) * S(ii)],
[-S(jj), C(jj) * S(ii), C(jj) * C(ii)]]
return np.array(R)
def body_to_earth_frame(ii, jj, kk):
# C^n_b
return np.transpose(earth_to_body_frame(ii, jj, kk))
class PhysicsSim():
def __init__(self, init_pose=None, init_velocities=None, init_angle_velocities=None, runtime=5.):
self.init_pose = init_pose
self.init_velocities = init_velocities
self.init_angle_velocities = init_angle_velocities
self.runtime = runtime
self.gravity = -9.81 # m/s
self.rho = 1.2
self.mass = 0.958 # 300 g
self.dt = 1 / 50.0 # Timestep
self.C_d = 0.3
self.l_to_rotor = 0.4
self.propeller_size = 0.1
width, length, height = .51, .51, .235
self.dims = np.array([width, length, height]) # x, y, z dimensions of quadcopter
self.areas = np.array([length * height, width * height, width * length])
I_x = 1 / 12. * self.mass * (height**2 + width**2)
I_y = 1 / 12. * self.mass * (height**2 + length**2) # 0.0112 was a measured value
I_z = 1 / 12. * self.mass * (width**2 + length**2)
self.moments_of_inertia = np.array([I_x, I_y, I_z]) # moments of inertia
env_bounds = 300.0 # 300 m / 300 m / 300 m
self.lower_bounds = np.array([-env_bounds / 2, -env_bounds / 2, 0])
self.upper_bounds = np.array([env_bounds / 2, env_bounds / 2, env_bounds])
self.reset()
def reset(self):
self.time = 0.0
self.pose = np.array([0.0, 0.0, 10.0, 0.0, 0.0, 0.0]) if self.init_pose is None else np.copy(self.init_pose)
self.v = np.array([0.0, 0.0, 0.0]) if self.init_velocities is None else np.copy(self.init_velocities)
self.angular_v = np.array([0.0, 0.0, 0.0]) if self.init_angle_velocities is None else np.copy(self.init_angle_velocities)
self.linear_accel = np.array([0.0, 0.0, 0.0])
self.angular_accels = np.array([0.0, 0.0, 0.0])
self.prop_wind_speed = np.array([0., 0., 0., 0.])
self.done = False
def find_body_velocity(self):
body_velocity = np.matmul(earth_to_body_frame(*list(self.pose[3:])), self.v)
return body_velocity
def get_linear_drag(self):
linear_drag = 0.5 * self.rho * self.find_body_velocity()**2 * self.areas * self.C_d
return linear_drag
def get_linear_forces(self, thrusts):
# Gravity
gravity_force = self.mass * self.gravity * np.array([0, 0, 1])
# Thrust
thrust_body_force = np.array([0, 0, sum(thrusts)])
# Drag
drag_body_force = -self.get_linear_drag()
body_forces = thrust_body_force + drag_body_force
linear_forces = np.matmul(body_to_earth_frame(*list(self.pose[3:])), body_forces)
linear_forces += gravity_force
return linear_forces
def get_moments(self, thrusts):
thrust_moment = np.array([(thrusts[3] - thrusts[2]) * self.l_to_rotor,
(thrusts[1] - thrusts[0]) * self.l_to_rotor,
0])# (thrusts[2] + thrusts[3] - thrusts[0] - thrusts[1]) * self.T_q]) # Moment from thrust
drag_moment = self.C_d * 0.5 * self.rho * self.angular_v * np.absolute(self.angular_v) * self.areas * self.dims * self.dims
moments = thrust_moment - drag_moment # + motor_inertia_moment
return moments
def calc_prop_wind_speed(self):
body_velocity = self.find_body_velocity()
phi_dot, theta_dot = self.angular_v[0], self.angular_v[1]
s_0 = np.array([0., 0., theta_dot * self.l_to_rotor])
s_1 = -s_0
s_2 = np.array([0., 0., phi_dot * self.l_to_rotor])
s_3 = -s_2
speeds = [s_0, s_1, s_2, s_3]
for num in range(4):
perpendicular_speed = speeds[num] + body_velocity
self.prop_wind_speed[num] = perpendicular_speed[2]
def get_propeler_thrust(self, rotor_speeds):
'''calculates net thrust (thrust - drag) based on velocity
of propeller and incoming power'''
thrusts = []
for prop_number in range(4):
V = self.prop_wind_speed[prop_number]
D = self.propeller_size
n = rotor_speeds[prop_number]
J = V / n * D
# From http://m-selig.ae.illinois.edu/pubs/BrandtSelig-2011-AIAA-2011-1255-LRN-Propellers.pdf
C_T = max(.12 - .07*max(0, J)-.1*max(0, J)**2, 0)
thrusts.append(C_T * self.rho * n**2 * D**4)
return thrusts
def next_timestep(self, rotor_speeds):
self.calc_prop_wind_speed()
thrusts = self.get_propeler_thrust(rotor_speeds)
self.linear_accel = self.get_linear_forces(thrusts) / self.mass
position = self.pose[:3] + self.v * self.dt + 0.5 * self.linear_accel * self.dt**2
self.v += self.linear_accel * self.dt
moments = self.get_moments(thrusts)
self.angular_accels = moments / self.moments_of_inertia
angles = self.pose[3:] + self.angular_v * self.dt + 0.5 * self.angular_accels * self.angular_accels * self.dt ** 2
angles = (angles + 2 * np.pi) % (2 * np.pi)
self.angular_v = self.angular_v + self.angular_accels * self.dt
new_positions = []
for ii in range(3):
if position[ii] <= self.lower_bounds[ii] :
new_positions.append(self.lower_bounds[ii])
self.done = True
elif position[ii] > self.upper_bounds[ii]:
new_positions.append(self.upper_bounds[ii])
self.done = True
else:
new_positions.append(position[ii])
self.pose = np.array(new_positions + list(angles))
self.time += self.dt
if self.time > self.runtime:
self.done = True
return self.done