mirror of
https://github.com/ArduPilot/ardupilot
synced 2025-01-08 08:58:29 -04:00
8f17f95cbc
updated motor setup test to be sequencial pulses of the motors in CW order. Fixed Mission scripting logic fixed Free yaw error in neutral throttle fixed D term issue with Baro hold - was too high incremented firmware revision, removed frame var removed setup show from startup removed unused EEPROM functions fixed broken demo mission fixed non working loiter with delay git-svn-id: https://arducopter.googlecode.com/svn/trunk@2275 f9c3cf11-9bcb-44bc-f272-b75c42450872
144 lines
3.5 KiB
Plaintext
144 lines
3.5 KiB
Plaintext
/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
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#define ARM_DELAY 10
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#define DISARM_DELAY 10
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void arm_motors()
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{
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static byte arming_counter;
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// Arm motor output : Throttle down and full yaw right for more than 2 seconds
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if (g.rc_3.control_in == 0){
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// full right
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if (g.rc_4.control_in > 4000) {
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if (arming_counter >= ARM_DELAY) {
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motor_armed = true;
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arming_counter = ARM_DELAY;
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// Remember Orientation
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// ---------------------------
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init_simple_bearing();
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} else{
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arming_counter++;
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}
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// full left
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}else if (g.rc_4.control_in < -4000) {
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if (arming_counter >= DISARM_DELAY){
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motor_armed = false;
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arming_counter = DISARM_DELAY;
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}else{
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arming_counter++;
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}
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// centered
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}else{
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arming_counter = 0;
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}
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}else{
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arming_counter = 0;
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}
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}
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/*****************************************
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* Set the flight control servos based on the current calculated values
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*****************************************/
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void
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set_servos_4()
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{
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if (motor_armed == true && motor_auto_armed == true) {
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// creates the radio_out and pwm_out values
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output_motors_armed();
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} else{
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output_motors_disarmed();
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}
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}
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/*****************************************
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* Set the flight control servos based on the current calculated values
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*****************************************/
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//if (num++ > 25){
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// num = 0;
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//Serial.print("kP: ");
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//Serial.println(g.pid_stabilize_roll.kP(),3);
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//*/
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/*
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Serial.printf("yaw: %d, lat_e: %ld, lng_e: %ld, \tnlat: %ld, nlng: %ld,\tnrll: %ld, nptc: %ld, \tcx: %.2f, sy: %.2f, \ttber: %ld, \tnber: %ld\n",
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(int)(dcm.yaw_sensor / 100),
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lat_error,
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long_error,
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nav_lat,
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nav_lon,
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nav_roll,
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nav_pitch,
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cos_yaw_x,
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sin_yaw_y,
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target_bearing,
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nav_bearing);
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//*/
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/*
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gcs_simple.write_byte(control_mode);
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//gcs_simple.write_int(motor_out[CH_1]);
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//gcs_simple.write_int(motor_out[CH_2]);
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//gcs_simple.write_int(motor_out[CH_3]);
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//gcs_simple.write_int(motor_out[CH_4]);
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gcs_simple.write_int(g.rc_3.servo_out);
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gcs_simple.write_int((int)(dcm.yaw_sensor / 100));
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gcs_simple.write_int((int)nav_lat);
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gcs_simple.write_int((int)nav_lon);
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gcs_simple.write_int((int)nav_roll);
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gcs_simple.write_int((int)nav_pitch);
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//gcs_simple.write_int((int)(cos_yaw_x * 100));
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//gcs_simple.write_int((int)(sin_yaw_y * 100));
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gcs_simple.write_long(current_loc.lat); //28
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gcs_simple.write_long(current_loc.lng); //32
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gcs_simple.write_int((int)current_loc.alt); //34
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gcs_simple.write_long(next_WP.lat);
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gcs_simple.write_long(next_WP.lng);
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gcs_simple.write_int((int)next_WP.alt); //44
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gcs_simple.write_int((int)(target_bearing / 100));
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gcs_simple.write_int((int)(nav_bearing / 100));
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gcs_simple.write_int((int)(nav_yaw / 100));
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if(altitude_sensor == BARO){
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gcs_simple.write_int((int)g.pid_baro_throttle.get_integrator());
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}else{
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gcs_simple.write_int((int)g.pid_sonar_throttle.get_integrator());
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}
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gcs_simple.write_int(g.throttle_cruise);
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gcs_simple.write_int(g.throttle_cruise);
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//24
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gcs_simple.flush(10); // Message ID
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//*/
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//Serial.printf("\n tb %d\n", (int)(target_bearing / 100));
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//Serial.printf("\n nb %d\n", (int)(nav_bearing / 100));
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//Serial.printf("\n dcm %d\n", (int)(dcm.yaw_sensor / 100));
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/*Serial.printf("a %ld, e %ld, i %d, t %d, b %4.2f\n",
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current_loc.alt,
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altitude_error,
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(int)g.pid_baro_throttle.get_integrator(),
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nav_throttle,
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angle_boost());
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*/
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//} |