def __init__(self, x0, t0, config, ax):
FixedWingUAV.__init__(self, x0, t0, config)
Autopilot.__init__(self, self.attrs['autopilot'], 1./200.)
self.x0 = x0
self.viewer = UAVViewer(ax, x0, self.R_bv(x0[6:9]))
self.trimmed_state = None
self.trimmed_control = None
def __init__(self, x0, t0, config, ax):
super(AppFixedWingRollAttHolder, self).__init__(x0, t0, config)
self.vertices = np.matrix(np.zeros((16, 3), dtype = np.double))
self.vertices[0, :] = [self.fuse_l1, 0.0, 0.0]
self.vertices[1, :] = [self.fuse_l2, 0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[2, :] = [self.fuse_l2, -0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[3, :] = [self.fuse_l2, -0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[4, :] = [self.fuse_l2, 0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[5, :] = [-self.fuse_l3, 0., 0.]
self.vertices[6, :] = [0, 0.5 * self.wing_w, 0.0]
self.vertices[7, :] = [-self.wing_l, 0.5 * self.wing_w, 0.0]
self.vertices[8, :] = [-self.wing_l, -0.5 * self.wing_w, 0.0]
self.vertices[9, :] = [0, -0.5 * self.wing_w, 0.0]
self.vertices[10, :] = [-(self.fuse_l3 - self.tailwing_l), 0.5 * self.tailwing_w, 0.]
self.vertices[11, :] = [-self.fuse_l3, 0.5 * self.tailwing_w, 0.]
self.vertices[12, :] = [-self.fuse_l3, -0.5 * self.tailwing_w, 0.]
self.vertices[13, :] = [-(self.fuse_l3 - self.tailwing_l), -0.5 * self.tailwing_w, 0.]
self.vertices[14, :] = [-(self.fuse_l3 - self.tailwing_l), 0.0, 0.]
self.vertices[15, :] = [-self.fuse_l3, 0.0, -self.tail_h]
self.vertices = 0.3048 * self.vertices
self.nose = [[0, 1, 2], [0, 2, 3], [0, 3, 4], [0, 1, 4]]
self.fuselage = [[5, 3, 2], [5, 2, 1], [5, 3, 4], [5, 4, 1]]
self.wing = [[6, 7, 8, 9]]
self.tail_wing = [[10, 11, 12, 13]]
self.tail = [[5, 14, 15]]
self.faces = [self.nose, self.fuselage, self.wing, self.tail_wing, self.tail]
self.viewer = UAVViewer(ax, (self.rotate(x0[6:9]) + x0[0:3]), self.faces, ['r', 'g', 'g', 'g', 'y'])
self.autopilot = Autopilot([], 1./200.)
self.autopilot.delta_a_limit = 15. * np.pi/180.
self.autopilot.roll_hold_controller.limit = self.autopilot.delta_a_limit
class AppFixedWingRollAttHolder(FixedWingUAV):
fuse_l1 = 5.
fuse_l2 = 2.5
fuse_l3 = 10.
fuse_h = 3.
fuse_w = 3.
wing_w = 15.
wing_l = 3.
tail_h = 4.
tailwing_w = 7.5
tailwing_l = 1.5
def __init__(self, x0, t0, config, ax):
super(AppFixedWingRollAttHolder, self).__init__(x0, t0, config)
self.vertices = np.matrix(np.zeros((16, 3), dtype = np.double))
self.vertices[0, :] = [self.fuse_l1, 0.0, 0.0]
self.vertices[1, :] = [self.fuse_l2, 0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[2, :] = [self.fuse_l2, -0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[3, :] = [self.fuse_l2, -0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[4, :] = [self.fuse_l2, 0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[5, :] = [-self.fuse_l3, 0., 0.]
self.vertices[6, :] = [0, 0.5 * self.wing_w, 0.0]
self.vertices[7, :] = [-self.wing_l, 0.5 * self.wing_w, 0.0]
self.vertices[8, :] = [-self.wing_l, -0.5 * self.wing_w, 0.0]
self.vertices[9, :] = [0, -0.5 * self.wing_w, 0.0]
self.vertices[10, :] = [-(self.fuse_l3 - self.tailwing_l), 0.5 * self.tailwing_w, 0.]
self.vertices[11, :] = [-self.fuse_l3, 0.5 * self.tailwing_w, 0.]
self.vertices[12, :] = [-self.fuse_l3, -0.5 * self.tailwing_w, 0.]
self.vertices[13, :] = [-(self.fuse_l3 - self.tailwing_l), -0.5 * self.tailwing_w, 0.]
self.vertices[14, :] = [-(self.fuse_l3 - self.tailwing_l), 0.0, 0.]
self.vertices[15, :] = [-self.fuse_l3, 0.0, -self.tail_h]
self.vertices = 0.3048 * self.vertices
self.nose = [[0, 1, 2], [0, 2, 3], [0, 3, 4], [0, 1, 4]]
self.fuselage = [[5, 3, 2], [5, 2, 1], [5, 3, 4], [5, 4, 1]]
self.wing = [[6, 7, 8, 9]]
self.tail_wing = [[10, 11, 12, 13]]
self.tail = [[5, 14, 15]]
self.faces = [self.nose, self.fuselage, self.wing, self.tail_wing, self.tail]
self.viewer = UAVViewer(ax, (self.rotate(x0[6:9]) + x0[0:3]), self.faces, ['r', 'g', 'g', 'g', 'y'])
self.autopilot = Autopilot([], 1./200.)
self.autopilot.delta_a_limit = 15. * np.pi/180.
self.autopilot.roll_hold_controller.limit = self.autopilot.delta_a_limit
def update_view(self):
vertices = self.rotate(self.dynamics.x[6:9]) + self.dynamics.x[0:3]
self.viewer.update(vertices)
def trim(self, Va, gamma, radius, max_iters):
trimmed_state, trimmed_control_inputs = self.dynamics.trim(Va, gamma, radius, epsilon=1e-8, kappa=1e-6, max_iters=max_iters)
#self.set_state(trimmed_state, 0.)
self.set_control_inputs(trimmed_control_inputs)
#TODO: move ki, tau, zeta to config if required
def set_roll(self, roll_c, ki, tau, zeta):
Va = np.linalg.norm(self.dynamics.x[3:6])
S = self.attrs['params']['S']
b = self.attrs['params']['b']
rho = self.attrs['params']['rho']
Jx = self.attrs['params']['Jx']
Jz = self.attrs['params']['Jz']
Jxz = self.attrs['params']['Jxz']
gamma_0 = Jx * Jz - Jxz**2
gamma_3 = Jz/gamma_0
gamma_4 = Jxz/gamma_0
Clateral_coeffs = self.attrs['lateral_coeffs']
Cl_p = Clateral_coeffs['Cl_p']
Cl_delta_a = Clateral_coeffs['Cl_delta_a']
Cn_delta_a = Clateral_coeffs['Cn_delta_a']
Cn_p = Clateral_coeffs['Cn_p']
Cp_delta_a = gamma_3 * Cl_delta_a + gamma_4 * Cn_delta_a
Cp_p = gamma_3 * Cl_p + gamma_4 * Cn_p
aphi_1 = -0.5 * rho * Va * S * b * Cp_p * 0.5 * b
aphi_2 = 0.5 * rho * Va**2 * S * b * Cp_delta_a
self.autopilot.roll_hold_controller.kp = self.attrs['autopilot']['delta_a_max_deg']/self.attrs['autopilot']['error_phi_max_deg'] * np.sign(aphi_2)
self.autopilot.roll_hold_controller.ki = ki
omega_phi = np.sqrt(np.abs(aphi_2) * self.attrs['autopilot']['delta_a_max_deg']/self.attrs['autopilot']['error_phi_max_deg'])
self.autopilot.roll_hold_controller.kd = (2 * zeta * omega_phi - aphi_1)/aphi_2
self.autopilot.roll_hold_controller.tau = tau
control_inputs = self.get_control_inputs()
#-0.018949908534872429
control_inputs[1] = self.autopilot.compute_delta_a(roll_c, self.dynamics.x[6])
self.set_control_inputs(control_inputs)
class AppFixedWingPitchAttHolder(FixedWingUAV):
fuse_l1 = 5.
fuse_l2 = 2.5
fuse_l3 = 10.
fuse_h = 3.
fuse_w = 3.
wing_w = 15.
wing_l = 3.
tail_h = 4.
tailwing_w = 7.5
tailwing_l = 1.5
def __init__(self, x0, t0, config, ax):
super(AppFixedWingPitchAttHolder, self).__init__(x0, t0, config)
self.vertices = np.matrix(np.zeros((16, 3), dtype = np.double))
self.vertices[0, :] = [self.fuse_l1, 0.0, 0.0]
self.vertices[1, :] = [self.fuse_l2, 0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[2, :] = [self.fuse_l2, -0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[3, :] = [self.fuse_l2, -0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[4, :] = [self.fuse_l2, 0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[5, :] = [-self.fuse_l3, 0., 0.]
self.vertices[6, :] = [0, 0.5 * self.wing_w, 0.0]
self.vertices[7, :] = [-self.wing_l, 0.5 * self.wing_w, 0.0]
self.vertices[8, :] = [-self.wing_l, -0.5 * self.wing_w, 0.0]
self.vertices[9, :] = [0, -0.5 * self.wing_w, 0.0]
self.vertices[10, :] = [-(self.fuse_l3 - self.tailwing_l), 0.5 * self.tailwing_w, 0.]
self.vertices[11, :] = [-self.fuse_l3, 0.5 * self.tailwing_w, 0.]
self.vertices[12, :] = [-self.fuse_l3, -0.5 * self.tailwing_w, 0.]
self.vertices[13, :] = [-(self.fuse_l3 - self.tailwing_l), -0.5 * self.tailwing_w, 0.]
self.vertices[14, :] = [-(self.fuse_l3 - self.tailwing_l), 0.0, 0.]
self.vertices[15, :] = [-self.fuse_l3, 0.0, -self.tail_h]
self.vertices = 0.3048 * self.vertices
self.nose = [[0, 1, 2], [0, 2, 3], [0, 3, 4], [0, 1, 4]]
self.fuselage = [[5, 3, 2], [5, 2, 1], [5, 3, 4], [5, 4, 1]]
self.wing = [[6, 7, 8, 9]]
self.tail_wing = [[10, 11, 12, 13]]
self.tail = [[5, 14, 15]]
self.faces = [self.nose, self.fuselage, self.wing, self.tail_wing, self.tail]
self.viewer = UAVViewer(ax, (self.rotate(x0[6:9]) + x0[0:3]), self.faces, ['r', 'g', 'g', 'g', 'y'])
self.autopilot = Autopilot([], 1./200.)
self.autopilot.delta_e_limit = self.attrs['autopilot']['delta_e_max_deg'] * np.pi/180
self.autopilot.pitch_hold_controller.limit = self.autopilot.delta_e_limit
def update_view(self):
vertices = self.rotate(self.dynamics.x[6:9]) + self.dynamics.x[0:3]
self.viewer.update(vertices)
def trim(self, Va, gamma, radius, max_iters):
trimmed_state, trimmed_control_inputs = self.dynamics.trim(Va, gamma, radius, epsilon=1e-8, kappa=1e-6, max_iters=max_iters)
#self.set_state(trimmed_state, 0.)
self.set_control_inputs(trimmed_control_inputs)
#TODO: move ki, tau, zeta to config if required
def set_pitch(self, pitch_c, ki, tau, zeta):
Va = np.linalg.norm(self.dynamics.x[3:6])
S = self.attrs['params']['S']
#b = self.attrs['params']['b']
c = self.attrs['params']['c']
rho = self.attrs['params']['rho']
Jy = self.attrs['params']['Jy']
Clong_coeffs = self.attrs['longitudinal_coeffs']
Cm_q = Clong_coeffs['Cm_q']
Cm_alpha = Clong_coeffs['Cm_q']
Cm_delta_e = Clong_coeffs['Cm_delta_e']
atheta_1 = -rho * Va * c * S * Cm_q * 0.5 * c
atheta_2 = -rho * Va**2 * c *S * Cm_alpha * 0.5/Jy
atheta_3 = rho * Va**2 * c *S * Cm_delta_e * 0.5/Jy
self.autopilot.pitch_hold_controller.kp = self.attrs['autopilot']['delta_e_max_deg']/self.attrs['autopilot']['error_theta_max_deg'] * np.sign(atheta_3)
self.autopilot.pitch_hold_controller.ki = ki
omega_theta = np.sqrt(atheta_2 + self.attrs['autopilot']['delta_e_max_deg']/self.attrs['autopilot']['error_theta_max_deg'] * np.abs(atheta_3))
self.autopilot.pitch_hold_controller.kd = (2 * zeta * omega_theta - atheta_1)/atheta_3
self.autopilot.pitch_hold_controller.tau = tau
control_inputs = self.get_control_inputs()
#-0.018949908534872429
q = self.dynamics.x[10]
control_inputs[0] = self.autopilot.compute_delta_e(pitch_c, self.dynamics.x[7], -q)
self.set_control_inputs(control_inputs)
class AppFixedWingAirspeedHolder(FixedWingUAV):
fuse_l1 = 5.
fuse_l2 = 2.5
fuse_l3 = 10.
fuse_h = 3.
fuse_w = 3.
wing_w = 15.
wing_l = 3.
tail_h = 4.
tailwing_w = 7.5
tailwing_l = 1.5
def __init__(self, x0, t0, config, ax):
super(AppFixedWingAirspeedHolder, self).__init__(x0, t0, config)
self.vertices = np.matrix(np.zeros((16, 3), dtype = np.double))
self.vertices[0, :] = [self.fuse_l1, 0.0, 0.0]
self.vertices[1, :] = [self.fuse_l2, 0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[2, :] = [self.fuse_l2, -0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[3, :] = [self.fuse_l2, -0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[4, :] = [self.fuse_l2, 0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[5, :] = [-self.fuse_l3, 0., 0.]
self.vertices[6, :] = [0, 0.5 * self.wing_w, 0.0]
self.vertices[7, :] = [-self.wing_l, 0.5 * self.wing_w, 0.0]
self.vertices[8, :] = [-self.wing_l, -0.5 * self.wing_w, 0.0]
self.vertices[9, :] = [0, -0.5 * self.wing_w, 0.0]
self.vertices[10, :] = [-(self.fuse_l3 - self.tailwing_l), 0.5 * self.tailwing_w, 0.]
self.vertices[11, :] = [-self.fuse_l3, 0.5 * self.tailwing_w, 0.]
self.vertices[12, :] = [-self.fuse_l3, -0.5 * self.tailwing_w, 0.]
self.vertices[13, :] = [-(self.fuse_l3 - self.tailwing_l), -0.5 * self.tailwing_w, 0.]
self.vertices[14, :] = [-(self.fuse_l3 - self.tailwing_l), 0.0, 0.]
self.vertices[15, :] = [-self.fuse_l3, 0.0, -self.tail_h]
self.vertices = 0.3048 * self.vertices
self.nose = [[0, 1, 2], [0, 2, 3], [0, 3, 4], [0, 1, 4]]
self.fuselage = [[5, 3, 2], [5, 2, 1], [5, 3, 4], [5, 4, 1]]
self.wing = [[6, 7, 8, 9]]
self.tail_wing = [[10, 11, 12, 13]]
self.tail = [[5, 14, 15]]
self.faces = [self.nose, self.fuselage, self.wing, self.tail_wing, self.tail]
self.viewer = UAVViewer(ax, (self.rotate(x0[6:9]) + x0[0:3]), self.faces, ['r', 'g', 'g', 'g', 'y'])
self.autopilot = Autopilot([], 1./200.)
self.autopilot.delta_a_limit = 15. * np.pi/180.
self.autopilot.roll_hold_controller.limit = self.autopilot.delta_a_limit
def update_view(self):
vertices = self.rotate(self.dynamics.x[6:9]) + self.dynamics.x[0:3]
self.viewer.update(vertices)
def trim(self, Va, gamma, radius, max_iters):
trimmed_state, trimmed_control_inputs = self.dynamics.trim(Va, gamma, radius, epsilon=1e-8, kappa=1e-6, max_iters=max_iters)
#self.set_state(trimmed_state, 0.)
#print trimmed_control_inputs
self.set_control_inputs(trimmed_control_inputs)
#TODO: vg = va (no wind is assumed. Add wind models and change appropriately later!)
def set_airspeed(self, Va_c, zeta, Va_trim, delta_e_trim, alpha_trim):
Va = np.linalg.norm(self.dynamics.x[3:6])
S = self.attrs['params']['S']
#b = self.attrs['params']['b']
c = self.attrs['params']['c']
rho = self.attrs['params']['rho']
Jy = self.attrs['params']['Jy']
Clong_coeffs = self.attrs['longitudinal_coeffs']
CD0 = Clong_coeffs['CD0']
CD_alpha = Clong_coeffs['CD_alpha']
CD_delta_e = Clong_coeffs['CD_delta_e']
C_prop = Clong_coeffs['C_prop']
S_prop = self.attrs['params']['S_prop']
mass = self.attrs['params']['mass']
aV_1 = rho * Va_trim * S * (CD0 + CD_alpha * alpha_trim + CD_delta_e * delta_e_trim)/mass + rho * S_prop * C_prop * Va_trim/mass
Cm_alpha = Clong_coeffs['Cm_q']
Cm_delta_e = Clong_coeffs['Cm_delta_e']
atheta_2 = -rho * Va**2 * c *S * Cm_alpha * 0.5/Jy
atheta_3 = rho * Va**2 * c *S * Cm_delta_e * 0.5/Jy
omega_v2 = 0.5
kp_theta = self.attrs['autopilot']['delta_e_max_deg']/self.attrs['autopilot']['error_theta_max_deg'] * np.sign(atheta_3)
K_theta_dc = (kp_theta * atheta_3)/(atheta_2 + kp_theta * atheta_3)
self.autopilot.airspeed_hold_with_pitch_controller.kp = (aV_1 - 2.0*zeta*omega_v2)/(K_theta_dc * 9.81)
self.autopilot.airspeed_hold_with_pitch_controller.ki = -omega_v2**2 /(K_theta_dc * 9.81)
pitch_c = self.autopilot.compute_pitch_for_airspeed(Va_c, Va)
return pitch_c
#TODO: move ki, tau, zeta to config if required
def set_pitch(self, pitch_c, ki, tau, zeta):
Va = np.linalg.norm(self.dynamics.x[3:6])
S = self.attrs['params']['S']
#b = self.attrs['params']['b']
c = self.attrs['params']['c']
rho = self.attrs['params']['rho']
Jy = self.attrs['params']['Jy']
Clong_coeffs = self.attrs['longitudinal_coeffs']
Cm_q = Clong_coeffs['Cm_q']
Cm_alpha = Clong_coeffs['Cm_q']
Cm_delta_e = Clong_coeffs['Cm_delta_e']
atheta_1 = -rho * Va * c * S * Cm_q * 0.5 * c
atheta_2 = -rho * Va**2 * c *S * Cm_alpha * 0.5/Jy
atheta_3 = rho * Va**2 * c *S * Cm_delta_e * 0.5/Jy
self.autopilot.pitch_hold_controller.kp = self.attrs['autopilot']['delta_e_max_deg']/self.attrs['autopilot']['error_theta_max_deg'] * np.sign(atheta_3)
self.autopilot.pitch_hold_controller.ki = ki
omega_theta = np.sqrt(atheta_2 + self.attrs['autopilot']['delta_e_max_deg']/self.attrs['autopilot']['error_theta_max_deg'] * np.abs(atheta_3))
print 'omega_theta: ', omega_theta
self.autopilot.pitch_hold_controller.kd = (2 * zeta * omega_theta - atheta_1)/atheta_3
self.autopilot.pitch_hold_controller.tau = tau
control_inputs = self.get_control_inputs()
#-0.018949908534872429
q = self.dynamics.x[10]
control_inputs[0] = self.autopilot.compute_delta_e(pitch_c, self.dynamics.x[7])
self.set_control_inputs(control_inputs)
class AppFixedWingAirspeedHolder(FixedWingUAV):
fuse_l1 = 5.
fuse_l2 = 2.5
fuse_l3 = 10.
fuse_h = 3.
fuse_w = 3.
wing_w = 15.
wing_l = 3.
tail_h = 4.
tailwing_w = 7.5
tailwing_l = 1.5
def __init__(self, x0, t0, config, ax):
super(AppFixedWingAirspeedHolder, self).__init__(x0, t0, config)
self.vertices = np.matrix(np.zeros((16, 3), dtype = np.double))
self.vertices[0, :] = [self.fuse_l1, 0.0, 0.0]
self.vertices[1, :] = [self.fuse_l2, 0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[2, :] = [self.fuse_l2, -0.5*self.fuse_w, 0.5*self.fuse_h]
self.vertices[3, :] = [self.fuse_l2, -0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[4, :] = [self.fuse_l2, 0.5*self.fuse_w, -0.5*self.fuse_h]
self.vertices[5, :] = [-self.fuse_l3, 0., 0.]
self.vertices[6, :] = [0, 0.5 * self.wing_w, 0.0]
self.vertices[7, :] = [-self.wing_l, 0.5 * self.wing_w, 0.0]
self.vertices[8, :] = [-self.wing_l, -0.5 * self.wing_w, 0.0]
self.vertices[9, :] = [0, -0.5 * self.wing_w, 0.0]
self.vertices[10, :] = [-(self.fuse_l3 - self.tailwing_l), 0.5 * self.tailwing_w, 0.]
self.vertices[11, :] = [-self.fuse_l3, 0.5 * self.tailwing_w, 0.]
self.vertices[12, :] = [-self.fuse_l3, -0.5 * self.tailwing_w, 0.]
self.vertices[13, :] = [-(self.fuse_l3 - self.tailwing_l), -0.5 * self.tailwing_w, 0.]
self.vertices[14, :] = [-(self.fuse_l3 - self.tailwing_l), 0.0, 0.]
self.vertices[15, :] = [-self.fuse_l3, 0.0, -self.tail_h]
self.vertices = 0.3048 * self.vertices
self.nose = [[0, 1, 2], [0, 2, 3], [0, 3, 4], [0, 1, 4]]
self.fuselage = [[5, 3, 2], [5, 2, 1], [5, 3, 4], [5, 4, 1]]
self.wing = [[6, 7, 8, 9]]
self.tail_wing = [[10, 11, 12, 13]]
self.tail = [[5, 14, 15]]
self.faces = [self.nose, self.fuselage, self.wing, self.tail_wing, self.tail]
self.viewer = UAVViewer(ax, (self.rotate(x0[6:9]) + x0[0:3]), self.faces, ['r', 'g', 'g', 'g', 'y'])
self.autopilot = Autopilot([], 1./200.)
def update_view(self):
vertices = self.rotate(self.dynamics.x[6:9]) + self.dynamics.x[0:3]
self.viewer.update(vertices)
def trim(self, Va, gamma, radius, max_iters):
trimmed_state, trimmed_control_inputs = self.dynamics.trim(Va, gamma, radius, epsilon=1e-8, kappa=1e-6, max_iters=max_iters)
#self.set_state(trimmed_state, 0.)
#print trimmed_control_inputs
self.set_control_inputs(trimmed_control_inputs)
#TODO: vg = va (no wind is assumed. Add wind models and change appropriately later!)
def set_airspeed(self, Va_c, zeta, Va_trim, delta_e_trim, alpha_trim, delta_t_trim):
Va = np.linalg.norm(self.dynamics.x[3:6])
S = self.attrs['params']['S']
rho = self.attrs['params']['rho']
Clong_coeffs = self.attrs['longitudinal_coeffs']
CD0 = Clong_coeffs['CD0']
CD_alpha = Clong_coeffs['CD_alpha']
CD_delta_e = Clong_coeffs['CD_delta_e']
C_prop = Clong_coeffs['C_prop']
S_prop = self.attrs['params']['S_prop']
mass = self.attrs['params']['mass']
k_motor = self.attrs['params']['k_motor']
av_1 = rho * Va_trim * S * (CD0 + CD_alpha * alpha_trim + CD_delta_e * delta_e_trim)/mass + rho * S_prop * C_prop * Va_trim/mass
av_2 = rho * S_prop * C_prop * k_motor**2 * delta_t_trim/mass
omega_v = 1.0
kp_v = (2.0 * zeta * omega_v - av_1) /av_2
ki_v = omega_v**2/av_2
self.autopilot.airspeed_hold_with_throttle_controller.kp = kp_v
self.autopilot.airspeed_hold_with_pitch_controller.ki = ki_v
delta_delta_t = self.autopilot.compute_throttle_for_airspeed(Va_c, Va)
control_inputs = self.get_control_inputs()
control_inputs[3] = delta_delta_t + control_inputs[3]
self.set_control_inputs(control_inputs)
