trajectory

class trajectory.Trajectory(n_segments_vnrs)[source]

Bases: object

The trajectory module contains the methods to compute the take-off trajectory used by pyNA.

__init__(n_segments_vnrs)[source]

Initialize self. See help(type(self)) for accurate signature.

static check_convergence(settings: pyNA.src.settings.Settings, filename: str) → bool[source]

Checks convergence of case using optimizer output file.

Parameters

  • settings (Settings) – pyna settings

  • filename (str) – file name of IPOPT output

Returns

converged

Return type

bool

compute(problem: openmdao.core.problem.Problem, settings: pyNA.src.settings.Settings, ac: pyNA.src.aircraft.Aircraft, run_driver: bool, init_trajectory: openmdao.core.problem.Problem, control_optimization: bool, objective: str) → None[source]

Run trajectory initial guess with minimal time to climb.

Parameters

  • problem (om.Problem) – openmdao problem

  • settings (Settings) – pyna settings

  • ac (Aircraft) – aircraft parameters

  • run_driver (bool) – flag to enable run_driver setting for dymos run_model function

  • init_trajectory (om.Problem) – initialization trajectory

  • control_optimization (bool) – flag to enable trajectory control_optimization

  • objective (str) – objective for the trajectory control optimization

Returns

None

static compute_minimum_TS(settings: pyNA.src.settings.Settings, ac: pyNA.src.aircraft.Aircraft, engine: pyNA.src.engine.Engine) → numpy.float64[source]

Compute minimum cutback thrust-setting meeting the 4%CG and one-engine-inoperative (OEI) airworthiness requirements.

Parameters

  • settings (Settings) – pyNA settings

  • ac (Aircraft) – aircraft parameters

  • engine – engine parameters

  • engine – Engine

Returns

TS_max

Return type

np.float64

compute_size_output_mux()[source]

Compute vector size of the muxed trajectory.

Parameters

size_inputs (np.ndarray) –

static get_engine_variables(settings: pyNA.src.settings.Settings, engine_mode: str) → list[source]

Get the engine parameters to compute during the trajectory computations.

Parameters

  • settings (Settings) – pyna settings

  • engine_mode (str) – mode for engine model in trajectory calculations: “trajectory” / “noise”

Returns

(engine_var, engine_var_units)

Return type

(list, list)

load_operating_point(settings: pyNA.src.settings.Settings, time_step: int) → None[source]

Loads predefined trajectory timeseries.

Parameters

  • settings (Settings) – pyna settings

  • time_step (int) – time step of the operating point in the trajectory time series

Returns

None

load_time_series(settings: pyNA.src.settings.Settings) → None[source]

Loads predefined trajectory timeseries.

Parameters

settings (Settings) – pyna settings

Returns

None

setup(problem: openmdao.core.problem.Problem, settings: pyNA.src.settings.Settings, ac: pyNA.src.aircraft.Aircraft, engine: pyNA.src.engine.Engine, engine_mode: str, control_optimization: bool) → None[source]

Setup take-off trajectory module using the following phases:

  • Ground roll: acceleration from V=0 to V=kVstall;

  • Rotation: rotate at dalpha/dt = cnst until Fnet_up=0N;

  • Climb: climb until obstacle is cleared (35ft).

  • VNRS: any VNRS can be applied in this phase, e.g. PTCB or PHLD

  • cutback: a pilot-initiated thrust cut-back to a constant thrust-setting is applied

Parameters

  • problem (om.Problem) – openmdao problem

  • settings (Settings) – pyna settings

  • ac (Aircraft) – aircraft parameters

  • engine – engine parameters

  • engine – Engine

  • engine_mode (str) – mode for engine model in trajectory calculations: “trajectory” / “noise”

Returns

None