for the dynamics xdot = f(x, u), returns f(x, u)

Adds a group of measurements in vector form vector_name (string): name given the vector through the *define_input_vector*

Defines an input vector so measurements can be added in groups vector_name (string): name of the vector input_vector (list o

Converts euler angles to 3-2-1 rotation matrix (R_b^i **b2i = transpose of the book**)

Return value of sensors on MAV: gyros, accels, absolute_pressure, dynamic_pressure, GPS

square wave function

for the dynamics xdot = f(x, u), returns f(x, u)

return the forces on the UAV based on the state, wind, and control surfaces :param delta: np.matrix(delta_a, delta_e, delta_r, delta_

Integrate the differential equations defining dynamics, update sensors delta = (delta_a, delta_e, delta_r, delta_t) are the c

converts a quaternion attitude to an euler angle attitude :param quaternion: the quaternion to be converted to euler angles in a np.matrix

Return value of sensors on MAV: gyros, accels, absolute_pressure, dynamic_pressure, GPS

square wave function

polynomial transition wave function

Converts a quaternion attitude to an euler angle attitude Args: quaternion: `size == 4` quaternion vector Returns: tupl

Rotate points by the rotation matrix R

Integrate the differential equations defining dynamics, update sensors delta = (delta_a, delta_e, delta_r, delta_t) are the c

PASS if check matches either candidate solution.

for the dynamics xdot = f(x, u), returns f(x, u)

for the dynamics xdot = f(x, u), returns f(x, u)

Converts euler angles to rotation matrix (R_b^i)

Add multiple plotboxes, configured according to the structure of *plotbox_arg_list* Arguments: plotbox_arg_list (list of Plotbox

converts a quaternion attitude to a 3-2-1 rotation matrix (R_b^i **b2i = transpose of the book**)

Update the plots (according to plotting frequency defined in init)

Converts an euler angle attitude to a quaternian attitude :param euler: Euler angle attitude in a np.matrix(phi, theta, psi) :return: Qua

converts a quaternion attitude to a rotation matrix

return the forces on the UAV based on the state, wind, and control surfaces :param delta: np.matrix(delta_a, delta_e, delta_r, delta_

Force np.random.normal(...) to return its mean (loc).

Rotate points by the rotation matrix R

Adds a state and the necessary plot, curves, and data lists curve_names: name(s) of the state(s) to be plotted in the same plot window

Converts an euler angle attitude to a quaternian attitude Args: param euler: Euler angle attitude in three floats, phi, theta, psi