# 3D Control of Quadcopter
# based on https://github.com/juanmed/quadrotor_sim/blob/master/3D_Quadrotor/3D_control_with_body_drag.py
# The dynamics is from pp. 17, Eq. (2.22). https://www.kth.se/polopoly_fs/1.588039.1550155544!/Thesis%20KTH%20-%20Francesco%20Sabatino.pdf
# The linearization is from Different Linearization Control Techniques for
# a Quadrotor System (many typos)

import dynamics
from dynamics import g, m, Ix, Iy, Iz
import numpy as np
import scipy
from scipy.integrate import odeint

def lqr(A, B, Q, R):
    """Solve the continuous time lqr controller.
    dx/dt = A x + B u
    cost = integral x.T*Q*x + u.T*R*u
    """
    # http://www.mwm.im/lqr-controllers-with-python/
    # ref Bertsekas, p.151

    # first, try to solve the ricatti equation
    X = np.matrix(scipy.linalg.solve_continuous_are(A, B, Q, R))

    # compute the LQR gain
    K = np.matrix(scipy.linalg.inv(R) * (B.T * X))

    eigVals, eigVecs = scipy.linalg.eig(A - B * K)

    return np.asarray(K), np.asarray(X), np.asarray(eigVals)

# The control can be done in a decentralized style
# The linearized system is divided into four decoupled subsystems

# X-subsystem
# The state variables are x, dot_x, pitch, dot_pitch
Ax = np.array(
    [[0.0, 1.0, 0.0, 0.0],
     [0.0, 0.0, g, 0.0],
     [0.0, 0.0, 0.0, 1.0],
     [0.0, 0.0, 0.0, 0.0]])
Bx = np.array(
    [[0.0],
     [0.0],
     [0.0],
     [1 / Ix]])

# Y-subsystem
# The state variables are y, dot_y, roll, dot_roll
Ay = np.array(
    [[0.0, 1.0, 0.0, 0.0],
     [0.0, 0.0, -g, 0.0],
     [0.0, 0.0, 0.0, 1.0],
     [0.0, 0.0, 0.0, 0.0]])
By = np.array(
    [[0.0],
     [0.0],
     [0.0],
     [1 / Iy]])

# Z-subsystem
# The state variables are z, dot_z
Az = np.array(
    [[0.0, 1.0],
     [0.0, 0.0]])
Bz = np.array(
    [[0.0],
     [1 / m]])

# Yaw-subsystem
# The state variables are yaw, dot_yaw
Ayaw = np.array(
    [[0.0, 1.0],
     [0.0, 0.0]])
Byaw = np.array(
    [[0.0],
     [1 / Iz]])

####################### solve LQR #######################
Ks = []  # feedback gain matrices K for each subsystem
for A, B in ((Ax, Bx), (Ay, By), (Az, Bz), (Ayaw, Byaw)):
    n = A.shape[0]
    m = B.shape[1]
    Q = np.eye(n)
    Q[0, 0] = 10.  # The first state variable is the one we care about.
    R = np.diag([1., ])
    K, _, _ = lqr(A, B, Q, R)
    Ks.append(K)

####################### The controller ######################
def u(x, goal):
    # the controller
    UX = Ks[0].dot(np.array([goal[0], 0, 0, 0]) - x[[0, 1, 8, 9]])[0]
    UY = Ks[1].dot(np.array([goal[1], 0, 0, 0]) - x[[2, 3, 6, 7]])[0]
    UZ = Ks[2].dot(np.array([goal[2], 0]) - x[[4, 5]])[0]
    UYaw = Ks[3].dot(np.array([0, 0]) - x[[10, 11]])[0]
    return np.array([UZ, UY, UX, UYaw])

######################## The closed_loop system #######################
def cl_nonlinear(x, t, goal):
    x = np.array(x)
    dot_x = dynamics.f(x, u(x, goal) + np.array([m * g, 0, 0, 0]))
    return dot_x

# simulate
def simulate(x, goal, dt):
    curr_position = np.array(x)[[0,2,4]]
    error = goal - curr_position
    distance = np.sqrt((error**2).sum())
    if distance > 1:
        goal = curr_position + error / distance
    return odeint(cl_nonlinear, x, [0, dt], args=(goal,))[-1]

# 3D Control of Quadcopter
# based on https://github.com/juanmed/quadrotor_sim/blob/master/3D_Quadrotor/3D_control_with_body_drag.py
# The dynamics is from pp. 17, Eq. (2.22). https://www.kth.se/polopoly_fs/1.588039.1550155544!/Thesis%20KTH%20-%20Francesco%20Sabatino.pdf
# The linearization is from Different Linearization Control Techniques for
# a Quadrotor System (many typos)

import dynamics
from dynamics import g, m, Ix, Iy, Iz
import numpy as np
import scipy
from scipy.integrate import odeint

def lqr(A, B, Q, R):
    """Solve the continuous time lqr controller.
    dx/dt = A x + B u
    cost = integral x.T*Q*x + u.T*R*u
    """
    # http://www.mwm.im/lqr-controllers-with-python/
    # ref Bertsekas, p.151

    # first, try to solve the ricatti equation
    X = np.matrix(scipy.linalg.solve_continuous_are(A, B, Q, R))

    # compute the LQR gain
    K = np.matrix(scipy.linalg.inv(R) * (B.T * X))

    eigVals, eigVecs = scipy.linalg.eig(A - B * K)

    return np.asarray(K), np.asarray(X), np.asarray(eigVals)

# The control can be done in a decentralized style
# The linearized system is divided into four decoupled subsystems

# X-subsystem
# The state variables are x, dot_x, pitch, dot_pitch
Ax = np.array(
    [[0.0, 1.0, 0.0, 0.0],
     [0.0, 0.0, g, 0.0],
     [0.0, 0.0, 0.0, 1.0],
     [0.0, 0.0, 0.0, 0.0]])
Bx = np.array(
    [[0.0],
     [0.0],
     [0.0],
     [1 / Ix]])

# Y-subsystem
# The state variables are y, dot_y, roll, dot_roll
Ay = np.array(
    [[0.0, 1.0, 0.0, 0.0],
     [0.0, 0.0, -g, 0.0],
     [0.0, 0.0, 0.0, 1.0],
     [0.0, 0.0, 0.0, 0.0]])
By = np.array(
    [[0.0],
     [0.0],
     [0.0],
     [1 / Iy]])

# Z-subsystem
# The state variables are z, dot_z
Az = np.array(
    [[0.0, 1.0],
     [0.0, 0.0]])
Bz = np.array(
    [[0.0],
     [1 / m]])

# Yaw-subsystem
# The state variables are yaw, dot_yaw
Ayaw = np.array(
    [[0.0, 1.0],
     [0.0, 0.0]])
Byaw = np.array(
    [[0.0],
     [1 / Iz]])

####################### solve LQR #######################
Ks = []  # feedback gain matrices K for each subsystem
for A, B in ((Ax, Bx), (Ay, By), (Az, Bz), (Ayaw, Byaw)):
    n = A.shape[0]
    m = B.shape[1]
    Q = np.eye(n)
    Q[0, 0] = 10.  # The first state variable is the one we care about.
    R = np.diag([1., ])
    K, _, _ = lqr(A, B, Q, R)
    Ks.append(K)

####################### The controller ######################
def u(x, goal):
    # the controller
    UX = Ks[0].dot(np.array([goal[0], 0, 0, 0]) - x[[0, 1, 8, 9]])[0]
    UY = Ks[1].dot(np.array([goal[1], 0, 0, 0]) - x[[2, 3, 6, 7]])[0]
    UZ = Ks[2].dot(np.array([goal[2], 0]) - x[[4, 5]])[0]
    UYaw = Ks[3].dot(np.array([0, 0]) - x[[10, 11]])[0]
    return np.array([UZ, UY, UX, UYaw])

######################## The closed_loop system #######################
def cl_nonlinear(x, t, goal):
    x = np.array(x)
    dot_x = dynamics.f(x, u(x, goal) + np.array([m * g, 0, 0, 0]))
    return dot_x

# simulate
def simulate(x, goal, dt):
    curr_position = np.array(x)[[0,2,4]]
    error = goal - curr_position
    distance = np.sqrt((error**2).sum())
    if distance > 1:
        goal = curr_position + error / distance
    return odeint(cl_nonlinear, x, [0, dt], args=(goal,))[-1]

# 3D Control of Quadcopter # based on https://github.com/juanmed/quadrotor_sim/blob/master/3D_Quadrotor/3D_control_with_body_drag.py # The dynamics is from pp. 17, Eq. (2.22). https://www.kth.se/polopoly_fs/1.588039.1550155544!/Thesis%20KTH%20-%20Francesco%20Sabatino.pdf # The linearization is from Different Linearization Control Techniques for # a Quadrotor System (many typos) Solve the continuous time lqr controller.     dx/dt = A x + B u     cost = integral x.T*Q*x + u.T*R*u # http://www.mwm.im/lqr-controllers-with-python/ # ref Bertsekas, p.151 # first, try to solve the ricatti equation # compute the LQR gain # The control can be done in a decentralized style # The linearized system is divided into four decoupled subsystems # X-subsystem # The state variables are x, dot_x, pitch, dot_pitch # Y-subsystem # The state variables are y, dot_y, roll, dot_roll # Z-subsystem # The state variables are z, dot_z # Yaw-subsystem # The state variables are yaw, dot_yaw ####################### solve LQR ####################### # feedback gain matrices K for each subsystem # The first state variable is the one we care about. ####################### The controller ###################### # the controller ######################## The closed_loop system ####################### # simulate