aerosandbox.dynamics.rigid_body.rigid_2D.body

Attributes

dyn

Classes

DynamicsRigidBody2DBody

Dynamics instance:

Module Contents

class aerosandbox.dynamics.rigid_body.rigid_2D.body.DynamicsRigidBody2DBody(mass_props=None, x_e=0, z_e=0, u_b=0, w_b=0, theta=0, q=0)

Bases: aerosandbox.dynamics.rigid_body.rigid_3D.body_euler.DynamicsRigidBody3DBodyEuler

Dynamics instance: * simulating a rigid body * in 2D * with velocity parameterized in body axes

State variables:

x_e: x-position, in Earth axes. [meters] z_e: z-position, in Earth axes. [meters] u_b: x-velocity, in body axes. [m/s] w_b: z-velocity, in body axes. [m/s] theta: pitch angle. [rad] q: y-angular-velocity, in body axes. [rad/sec]

Control variables:

Fx_b: Force along the body-x axis. [N] Fz_b: Force along the body-z axis. [N] My_b: Moment about the body-y axis. [Nm]

Parameters:

• mass_props (aerosandbox.weights.mass_properties.MassProperties) –

• x_e (Union[float, aerosandbox.numpy.ndarray]) –

• z_e (Union[float, aerosandbox.numpy.ndarray]) –

• u_b (Union[float, aerosandbox.numpy.ndarray]) –

• w_b (Union[float, aerosandbox.numpy.ndarray]) –

• theta (Union[float, aerosandbox.numpy.ndarray]) –

• q (Union[float, aerosandbox.numpy.ndarray]) –

mass_props

For each state variable, self.state_var = state_var

For each indirect control variable, self.indirect_control_var = indirect_control_var

For each control variable, self.control_var = 0

x_e = 0

y_e = 0

z_e = 0

u_b = 0

v_b = 0

w_b = 0

phi = 0

theta = 0

psi = 0

p = 0

q = 0

r = 0

Fx_b = 0

Fy_b = 0

Fz_b = 0

Mx_b = 0

My_b = 0

Mz_b = 0

hx_b = 0

hy_b = 0

hz_b = 0

property state

Returns the state variables of this Dynamics instance as a Dict.

Keys are strings that give the name of the variables. Values are the variables themselves.

This method should look something like:

>>> {
>>>     "x_e": self.x_e,
>>>     "u_e": self.u_e,
>>>     ...
>>> }

property control_variables

state_derivatives()

Computes the state derivatives (i.e. equations of motion) for a body in 3D space.

Based on Section 9.8.2 of Flight Vehicle Aerodynamics by Mark Drela.

Returns:

{

“xe” : d_xe, “ye” : d_ye, “ze” : d_ze, “u” : d_u, “v” : d_v, “w” : d_w, “phi” : d_phi, “theta”: d_theta, “psi” : d_psi, “p” : d_p, “q” : d_q, “r” : d_r,

}

Return type:

Time derivatives of each of the 12 state variables, given in a dictionary

aerosandbox.dynamics.rigid_body.rigid_2D.body.dyn