Stationaere_Lsg

class +AMrotorSIM.+Experiments.@Stationaere_Lsg.Stationaere_Lsg(rotorsystem, drehzahlvektor, time)

Bases: handle

Class for time integration with constant roation speed (Stationary solution)

See also AMrotorSIM.Graphs

rotorsystem = None

rpm steps

time = None

time steps e.g. 0:tStep:tEnd

result = None

results-struct: result.X, result.X_d, result.X_dd

Stationaere_Lsg(rotorsystem, drehzahlvektor, time)

Constructor

Parameters

  • rotorsystem (object) – Object of class Rotorsystem

  • drehzahlvektor (vector) – Rotation speed

  • time (vector) – Time range

Returns

Stationary solution object

+AMrotorSIM.+Experiments.@Stationaere_Lsg.clear_time_result(obj)

Clears result data in object

Returns

Empty result field in object

+AMrotorSIM.+Experiments.@Stationaere_Lsg.compute_euler_ss(obj)

Carries out an integration of type euler in state space (currently not working)

Returns

Integration results in results field of object

+AMrotorSIM.+Experiments.@Stationaere_Lsg.compute_newmark(obj, options)

Carries out an integration of type newmark

Parameters

options – Additional options like adaptivity, tolerances,… (check function)

Returns

Integration results in results field of object

+AMrotorSIM.+Experiments.@Stationaere_Lsg.compute_ode15s_ss(obj)

Carries out an integration of type ode15s

Returns

Integration results in results field of object

+AMrotorSIM.+Experiments.@Stationaere_Lsg.compute_sys_ss_variant(obj)

Carries out an integration in the state space (currently not working)

Returns

Integration results in results field of object

+AMrotorSIM.+Experiments.@Stationaere_Lsg.get_state_space_matrices(obj, omega)

Builds state space matrices of form A=[0, I;-M_inv*K, -M_inv*(C+G*omega)] and B=[0, 0;0, M_inv]

Parameters

omega (double) – Angular velocity

Returns

State space matrices A, B

+AMrotorSIM.+Experiments.@Stationaere_Lsg.newmark_integration_with_adaptive_step_size(obj, M, C, K, forceFunction, tspan, x0, dotx0, options)

Function for newmark with adaptive stepsize

Parameters

  • M (matrix) – Mass

  • C (matrix) – Damping with out gyro

  • K (matrix) – Stiffness

  • forceFunction (function) – Force for RHS of equation

  • t_span (double) – Time step

  • x0 (vector) – Start state vector (Z = [x; dotx];)

  • dotx0 (vector) – Start of derivative part of state vector Z = [x; dotx];

  • options – Additional options like adaptivity, tolerances,… (check function compute_newmark)

Returns

Derivatives of state vector parts (x,dotx,ddotx) and the time vector (t)

+AMrotorSIM.+Experiments.@Stationaere_Lsg.newmark_integration_without_adaptive_step_size(obj, M, C, K, forceFunction, t, x0, dotx0)

Function for newmark without adaptive stepsize

Parameters

  • M (matrix) – Mass

  • C (matrix) – Damping without gyro

  • K (matrix) – Stiffness

  • forceFunction (function) – Force for RHS of equation

  • t (double) – Time step

  • x0 (vector) – Start state vector (Z = [x; dotx];)

  • dotx0 (vector) – Start of derivative part of state vector Z = [x; dotx];

Returns

Derivatives of state vector parts, the time vector and error values [t,x,dotx,ddotx,localError,globalError]

+AMrotorSIM.+Experiments.@Stationaere_Lsg.show(obj)

Displays the object name in the Command Window

Parameters

obj (object) – Object of type Stationaere_Lsg

Returns

Notification of object name

+AMrotorSIM.+Experiments.@Stationaere_Lsg.private.get_force_newmark(obj, t, x, dotx)

Extracts the force from load-objects and from controller-objects

Parameters

  • t (double) – Time step

  • x (vector) – State vector (Z = [x; dotx];)

  • dotx (vector) – Derivative part of state vector Z = [x; dotx];

Returns

Force vector f

+AMrotorSIM.+Experiments.@Stationaere_Lsg.private.integrate_function(t, Z, Omega, rotorsystem, mat)

Provides integration function

Parameters

  • t (double) – Time step

  • Z (vector) – State vector

  • Omega –

  • rotorsystem (object) – Object of type Rotorsystem

  • mat (struct) – State space matrices A,B in form mat.A, mat.B

Returns

Derivative of state vector (dZ) for integration (check Matlab’s odefun)

+AMrotorSIM.+Experiments.@Stationaere_Lsg.private.odeOutputFcnController(t, y, flag, varargin)

Provides output function of integration and displays progress in Command Window

Parameters

  • t (vector (double)) – Time steps of integration

  • y (function) – Output function

  • flag (char) – Imports status of integration (check MATLAB odeset)

  • varargin – Variable input argument (check function)

Returns

Printing and plotting of the integration status