AirframeParametersConf.java example

Explorer
jop-master
/* $Id$
 * 
 * This file is a part of jPapaBench providing a Java implementation 
 * of PapaBench project.
 * Copyright (C) 2010  Michal Malohlava <michal.malohlava_at_d3s.mff.cuni.cz>
 *
 * This program is free software; you can redistribute it and/or
 * modify it under the terms of the GNU General Public License
 * as published by the Free Software Foundation; either version 2
 * of the License, or (at your option) any later version.
 *
 * This program is distributed in the hope that it will be useful,
 * but WITHOUT ANY WARRANTY; without even the implied warranty of
 * MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
 * GNU General Public License for more details.
 *
 * You should have received a copy of the GNU General Public License
 * along with this program; if not, write to the Free Software
 * Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA  02110-1301, USA.
 * 
 */
package papabench.core.commons.conf;

/**
 * Airframe parameters.
 * 
 * TODO this should be generated according to airplane configuration
 * 
 * @author Michal Malohlava
 * 
 */
public interface AirframeParametersConf {
	
	public static final float ALTITUDE_PGAIN = -0.025f;

	public static final float MAX_PITCH = 0.35f;
	public static final float MIN_PITCH = -0.35f;

	public static final float ROLL_PGAIN = 10000.0f;
//	public static final float MAX_ROLL = 0.35f; // FIXME
	public static final float MAX_ROLL = 0.85f;
	
	public static final float CLIMB_PITCH_PGAIN = -0.1f;
	public static final float CLIMB_PITCH_IGAIN = 0.025f;

	public static final float CLIMB_MAX = 1.0f;
	
	public static final float CLIMB_PGAIN = -0.03f;
	public static final float CLIMB_IGAIN = 0.1f;

	public static final float CLIMB_LEVEL_GAZ = 0.31f;
	public static final float CLIMB_PITCH_OF_VZ_PGAIN = 0.05f;
	public static final float CLIMB_GAZ_OF_CLIMB = 0.2f;
	
	public static final float COURSE_PGAIN = -0.2f;

	public static final float PITCH_OF_ROLL = 0.0f;
	public static final float PITCH_PGAIN = 15000.0f;

	public static final float NAV_PITCH = 0.f;
	
	public static final float NOMINAL_AIRSPEED = 10.0f;
	public static final float MAXIMUM_AIRSPEED = NOMINAL_AIRSPEED * 1.5f;

	public static final float AUTO_THROTTLE_NOMINAL_CRUISE_THROTTLE = 0.35f;
	public static final float CRUISE_THROTTLE = AUTO_THROTTLE_NOMINAL_CRUISE_THROTTLE;
		
	public static final float WEIGHT = 1.3f;
	public static final float MAXIMUM_POWER = 5 * MAXIMUM_AIRSPEED * WEIGHT;
	
	public static final float G = 9.806f;
	
	public static final float CARROT = 5.f;
	
	public static final float ROLL_RESPONSE_FACTOR = 15f;
	public static final float YAW_RESPONSE_FACTOR = 1f;

}