This repository has been archived by the owner on Aug 13, 2020. It is now read-only.
-
Notifications
You must be signed in to change notification settings - Fork 70
Commit
This commit does not belong to any branch on this repository, and may belong to a fork outside of the repository.
Merge pull request #3 from AlexS12/cessna-aqreed
WIP: Cessna aqreed
- Loading branch information
Showing
7 changed files
with
166 additions
and
44 deletions.
There are no files selected for viewing
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
This file contains bidirectional Unicode text that may be interpreted or compiled differently than what appears below. To review, open the file in an editor that reveals hidden Unicode characters.
Learn more about bidirectional Unicode characters
| Original file line number | Diff line number | Diff line change |
|---|---|---|
| @@ -0,0 +1,125 @@ | ||
| # -*- coding: utf-8 -*- | ||
| """ | ||
| Python Flight Mechanics Engine (PyFME). | ||
| Copyright (c) AeroPython Development Team. | ||
| Distributed under the terms of the MIT License. | ||
| Example | ||
| ------- | ||
| Cessna 310, ISA1976 integrated with Flat Earth (euler angles). | ||
| Evolution of the aircraft after a lat-dir perturbation. | ||
| Trimmed in stationary, horizontal, symmetric, wings level flight. | ||
| """ | ||
|
|
||
| import numpy as np | ||
| import matplotlib.pyplot as plt | ||
| from mpl_toolkits.mplot3d import Axes3D | ||
|
|
||
| from pyfme.aircrafts import Cessna172 | ||
| from pyfme.environment.environment import Environment | ||
| from pyfme.environment.atmosphere import ISA1976 | ||
| from pyfme.environment.gravity import VerticalConstant | ||
| from pyfme.environment.wind import NoWind | ||
| from pyfme.models.systems import EulerFlatEarth | ||
| from pyfme.simulator import BatchSimulation | ||
| from pyfme.utils.trimmer import steady_state_flight_trimmer | ||
| from pyfme.utils.input_generator import doublet | ||
|
|
||
| aircraft = Cessna172() | ||
| atmosphere = ISA1976() | ||
| gravity = VerticalConstant() | ||
| wind = NoWind() | ||
| environment = Environment(atmosphere, gravity, wind) | ||
|
|
||
| # Initial conditions. | ||
| TAS = 45 # m/s | ||
| h0 = 8000 * 0.3048 # m | ||
| psi0 = 1 # rad | ||
| x0, y0 = 0, 0 # m | ||
| turn_rate = 0.0 # rad/s | ||
| gamma0 = 0.00 # rad | ||
|
|
||
| system = EulerFlatEarth(lat=0, lon=0, h=h0, psi=psi0, x_earth=x0, y_earth=y0) | ||
|
|
||
| not_trimmed_controls = {'delta_elevator': 0.05, | ||
| 'delta_aileron': 0.01 * np.sign(turn_rate), | ||
| 'delta_rudder': 0.01 * np.sign(turn_rate), | ||
| 'delta_t': 0.5} | ||
|
|
||
| controls2trim = ['delta_elevator', 'delta_aileron', 'delta_rudder', 'delta_t'] | ||
|
|
||
| trimmed_ac, trimmed_sys, trimmed_env, results = steady_state_flight_trimmer( | ||
| aircraft, system, environment, TAS=TAS, controls_0=not_trimmed_controls, | ||
| controls2trim=controls2trim, gamma=gamma0, turn_rate=turn_rate, verbose=2) | ||
|
|
||
| print(results) | ||
|
|
||
| my_simulation = BatchSimulation(trimmed_ac, trimmed_sys, trimmed_env) | ||
|
|
||
| tfin = 15 # seconds | ||
| N = tfin * 100 + 1 | ||
| time = np.linspace(0, tfin, N) | ||
| initial_controls = trimmed_ac.controls | ||
|
|
||
| controls = {} | ||
| for control_name, control_value in initial_controls.items(): | ||
| controls[control_name] = np.ones_like(time) * control_value | ||
|
|
||
| # Rudder doublet | ||
| amplitude = 0.10 | ||
| controls['delta_elevator'] = doublet(t_init=1, | ||
| T=1, | ||
| A=amplitude, | ||
| time=time, | ||
| offset=initial_controls['delta_rudder']) | ||
|
|
||
| # Rudder aileron | ||
| amplitude = 0.15 | ||
| controls['delta_elevator'] = doublet(t_init=1.5, | ||
| T=1, | ||
| A=amplitude, | ||
| time=time, | ||
| offset=initial_controls['delta_aileron']) | ||
|
|
||
| my_simulation.set_controls(time, controls) | ||
|
|
||
| par_list = ['x_earth', 'y_earth', 'height', | ||
| 'psi', 'theta', 'phi', | ||
| 'u', 'v', 'w', | ||
| 'v_north', 'v_east', 'v_down', | ||
| 'p', 'q', 'r', | ||
| 'alpha', 'beta', 'TAS', | ||
| 'F_xb', 'F_yb', 'F_zb', | ||
| 'M_xb', 'M_yb', 'M_zb'] | ||
|
|
||
| my_simulation.set_par_dict(par_list) | ||
| my_simulation.run_simulation() | ||
|
|
||
| # print(my_simulation.par_dict) | ||
|
|
||
| plt.style.use('ggplot') | ||
|
|
||
| for ii in range(len(par_list) // 3): | ||
| three_params = par_list[3*ii:3*ii+3] | ||
| fig, ax = plt.subplots(3, 1, sharex=True) | ||
| for jj, par in enumerate(three_params): | ||
| ax[jj].plot(time, my_simulation.par_dict[par]) | ||
| ax[jj].set_ylabel(par) | ||
| ax[jj].set_xlabel('time (s)') | ||
|
|
||
| fig = plt.figure() | ||
| ax = Axes3D(fig) | ||
| ax.plot(my_simulation.par_dict['x_earth'], | ||
| my_simulation.par_dict['y_earth'], | ||
| my_simulation.par_dict['height']) | ||
|
|
||
| ax.plot(my_simulation.par_dict['x_earth'], | ||
| my_simulation.par_dict['y_earth'], | ||
| my_simulation.par_dict['height'] * 0) | ||
| ax.set_xlabel('x_earth') | ||
| ax.set_ylabel('y_earth') | ||
| ax.set_zlabel('z_earth') | ||
|
|
||
| plt.show() |