198 lines
6 KiB
C++
198 lines
6 KiB
C++
/**********************************************************************
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FILENAME: uiuc_controlInput.cpp
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----------------------------------------------------------------------
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DESCRIPTION: sets control surface deflections for specified input
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modes
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----------------------------------------------------------------------
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STATUS: alpha version
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----------------------------------------------------------------------
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REFERENCES:
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----------------------------------------------------------------------
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HISTORY: 04/08/2000 initial release
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06/18/2001 (RD) Added aileron_input and rudder_input
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07/05/2001 (RD) Code added to allow the pilot to fly
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aircraft after the control surface input
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files have been used.
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----------------------------------------------------------------------
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AUTHOR(S): Jeff Scott <jscott@mail.com>
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Robert Deters <rdeters@uiuc.edu>
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VARIABLES:
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INPUTS: -Simtime
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-deflection times
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-deflection angles
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OUTPUTS: -elevator deflection
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----------------------------------------------------------------------
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CALLED BY: uiuc_coefficients.cpp
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----------------------------------------------------------------------
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CALLS TO: none
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----------------------------------------------------------------------
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COPYRIGHT: (C) 2000 by Michael Selig
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This program is free software; you can redistribute it and/or
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modify it under the terms of the GNU General Public License
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as published by the Free Software Foundation.
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This program is distributed in the hope that it will be useful,
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but WITHOUT ANY WARRANTY; without even the implied warranty of
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MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
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GNU General Public License for more details.
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You should have received a copy of the GNU General Public License
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along with this program; if not, write to the Free Software
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Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA 02111-1307,
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USA or view http://www.gnu.org/copyleft/gpl.html.
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**********************************************************************/
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#include <simgear/compiler.h>
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#include "uiuc_controlInput.h"
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#include STL_IOSTREAM
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void uiuc_controlInput()
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{
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// elevator step input
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if (elevator_step)
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{
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if (Simtime >= elevator_step_startTime)
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{
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elevator = elevator + elevator_step_angle;
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}
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}
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// elevator singlet input
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if (elevator_singlet)
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{
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if (Simtime >= elevator_singlet_startTime &&
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Simtime <= (elevator_singlet_startTime + elevator_singlet_duration))
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{
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elevator = elevator + elevator_singlet_angle;
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}
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}
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// elevator doublet input
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if (elevator_doublet)
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{
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if (Simtime >= elevator_doublet_startTime &&
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Simtime <= (elevator_doublet_startTime + elevator_doublet_duration/2))
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{
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elevator = elevator + elevator_doublet_angle;
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}
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else if (Simtime >= (elevator_doublet_startTime + elevator_doublet_duration/2) &&
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Simtime <= (elevator_doublet_startTime + elevator_doublet_duration))
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{
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elevator = elevator - elevator_doublet_angle;
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}
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}
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// elevator input
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if (elevator_input)
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{
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double elevator_input_endTime = elevator_input_timeArray[elevator_input_ntime];
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if (Simtime >= elevator_input_startTime &&
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Simtime <= (elevator_input_startTime + elevator_input_endTime))
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{
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double time = Simtime - elevator_input_startTime;
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if (pilot_elev_no_check)
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{
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elevator = 0 + elevator_tab;
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pilot_elev_no = true;
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}
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elevator = elevator +
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uiuc_1Dinterpolation(elevator_input_timeArray,
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elevator_input_deArray,
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elevator_input_ntime,
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time);
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}
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}
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// aileron input
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if (aileron_input)
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{
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double aileron_input_endTime = aileron_input_timeArray[aileron_input_ntime];
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if (Simtime >= aileron_input_startTime &&
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Simtime <= (aileron_input_startTime + aileron_input_endTime))
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{
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double time = Simtime - aileron_input_startTime;
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if (pilot_ail_no_check)
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{
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aileron = 0;
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if (Simtime==0) //7-25-01 (RD) Added because
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pilot_ail_no = false; //segmentation fault is given
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else //with FG 0.7.8
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pilot_ail_no = true;
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}
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aileron = aileron +
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uiuc_1Dinterpolation(aileron_input_timeArray,
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aileron_input_daArray,
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aileron_input_ntime,
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time);
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}
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}
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// rudder input
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if (rudder_input)
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{
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double rudder_input_endTime = rudder_input_timeArray[rudder_input_ntime];
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if (Simtime >= rudder_input_startTime &&
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Simtime <= (rudder_input_startTime + rudder_input_endTime))
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{
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double time = Simtime - rudder_input_startTime;
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if (pilot_rud_no_check)
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{
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rudder = 0;
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pilot_rud_no = true;
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}
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rudder = rudder +
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uiuc_1Dinterpolation(rudder_input_timeArray,
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rudder_input_drArray,
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rudder_input_ntime,
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time);
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}
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}
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if (flap_pos_input)
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{
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double flap_pos_input_endTime = flap_pos_input_timeArray[flap_pos_input_ntime];
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if (Simtime >= flap_pos_input_startTime &&
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Simtime <= (flap_pos_input_startTime + flap_pos_input_endTime))
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{
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double time = Simtime - flap_pos_input_startTime;
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flap_pos = uiuc_1Dinterpolation(flap_pos_input_timeArray,
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flap_pos_input_dfArray,
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flap_pos_input_ntime,
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time);
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}
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}
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return;
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}
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// end uiuc_controlInput.cpp
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