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Update floating point calculations to use floats instead of doubles. 

- Allows use of hardware floating point on the Cortex-M4.
- Added "f" suffix to floating point literals.
- Call floating point versions of stdlib math functions.
This commit is contained in:
James Bielman 2013-01-10 10:42:24 -08:00 committed by Andrew Tridgell
parent d00b06d449
commit 5631f865b2
74 changed files with 538 additions and 538 deletions
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2
APMrover2/Attitude.pde
View File

@ -23,7 +23,7 @@ static void throttle_slew_limit(int16_t last_throttle)
// if slew limit rate is set to zero then do not slew limit
if (g.throttle_slewrate) {
// limit throttle change by the given percentage per second
float temp = g.throttle_slewrate * G_Dt * 0.01 * fabs(g.channel_throttle.radio_max - g.channel_throttle.radio_min);
float temp = g.throttle_slewrate * G_Dt * 0.01f * fabsf(g.channel_throttle.radio_max - g.channel_throttle.radio_min);
// allow a minimum change of 1 PWM per cycle
if (temp < 1) {
temp = 1;

42
APMrover2/GCS_Mavlink.pde
View File

@ -1361,9 +1361,9 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
case MAV_FRAME_MISSION:
case MAV_FRAME_GLOBAL:
{
tell_command.lat = 1.0e7*packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7*packet.y; // in as DD converted to * t7
tell_command.alt = packet.z*1.0e2; // in as m converted to cm
tell_command.lat = 1.0e7f*packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7f*packet.y; // in as DD converted to * t7
tell_command.alt = packet.z*1.0e2f; // in as m converted to cm
tell_command.options = 0; // absolute altitude
break;
}
@ -1371,10 +1371,10 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
#ifdef MAV_FRAME_LOCAL_NED
case MAV_FRAME_LOCAL_NED: // local (relative to home position)
{
tell_command.lat = 1.0e7*ToDeg(packet.x/
(radius_of_earth*cos(ToRad(home.lat/1.0e7)))) + home.lat;
tell_command.lng = 1.0e7*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = -packet.z*1.0e2;
tell_command.lat = 1.0e7f*ToDeg(packet.x/
(radius_of_earth*cosf(ToRad(home.lat/1.0e7f)))) + home.lat;
tell_command.lng = 1.0e7f*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = -packet.z*1.0e2f;
tell_command.options = MASK_OPTIONS_RELATIVE_ALT;
break;
}
@ -1383,10 +1383,10 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
#ifdef MAV_FRAME_LOCAL
case MAV_FRAME_LOCAL: // local (relative to home position)
{
tell_command.lat = 1.0e7*ToDeg(packet.x/
(radius_of_earth*cos(ToRad(home.lat/1.0e7)))) + home.lat;
tell_command.lng = 1.0e7*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = packet.z*1.0e2;
tell_command.lat = 1.0e7f*ToDeg(packet.x/
(radius_of_earth*cosf(ToRad(home.lat/1.0e7f)))) + home.lat;
tell_command.lng = 1.0e7f*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = packet.z*1.0e2f;
tell_command.options = MASK_OPTIONS_RELATIVE_ALT;
break;
}
@ -1394,9 +1394,9 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
case MAV_FRAME_GLOBAL_RELATIVE_ALT: // absolute lat/lng, relative altitude
{
tell_command.lat = 1.0e7 * packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7 * packet.y; // in as DD converted to * t7
tell_command.alt = packet.z * 1.0e2;
tell_command.lat = 1.0e7f * packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7f * packet.y; // in as DD converted to * t7
tell_command.alt = packet.z * 1.0e2f;
tell_command.options = MASK_OPTIONS_RELATIVE_ALT; // store altitude relative!! Always!!
break;
}
@ -1557,7 +1557,7 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
} else if (var_type == AP_PARAM_INT32) {
if (packet.param_value < 0) rounding_addition = -rounding_addition;
float v = packet.param_value+rounding_addition;
v = constrain(v, -2147483648.0, 2147483647.0);
v = constrain(v, -2147483648.0f, 2147483647.0f);
((AP_Int32 *)vp)->set_and_save(v);
} else if (var_type == AP_PARAM_INT16) {
if (packet.param_value < 0) rounding_addition = -rounding_addition;
@ -1634,12 +1634,12 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
mavlink_msg_hil_state_decode(msg, &packet);
float vel = pythagorous2(packet.vx, packet.vy);
float cog = wrap_360_cd(ToDeg(atan2(packet.vy, packet.vx)) * 100);
float cog = wrap_360_cd(ToDeg(atan2f(packet.vy, packet.vx)) * 100);
// set gps hil sensor
g_gps->setHIL(packet.time_usec/1000,
packet.lat*1.0e-7, packet.lon*1.0e-7, packet.alt*1.0e-3,
vel*1.0e-2, cog*1.0e-2, 0, 10);
packet.lat*1.0e-7f, packet.lon*1.0e-7f, packet.alt*1.0e-3f,
vel*1.0e-2f, cog*1.0e-2f, 0, 10);
// rad/sec
Vector3f gyros;
@ -1649,9 +1649,9 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
// m/s/s
Vector3f accels;
accels.x = packet.xacc * (GRAVITY_MSS/1000.0);
accels.y = packet.yacc * (GRAVITY_MSS/1000.0);
accels.z = packet.zacc * (GRAVITY_MSS/1000.0);
accels.x = packet.xacc * (GRAVITY_MSS/1000.0f);
accels.y = packet.yacc * (GRAVITY_MSS/1000.0f);
accels.z = packet.zacc * (GRAVITY_MSS/1000.0f);
ins.set_gyro(gyros);

2
APMrover2/navigation.pde
View File

@ -71,7 +71,7 @@ static void update_crosstrack(void)
// Crosstrack Error
// ----------------
if (abs(wrap_180(target_bearing - crosstrack_bearing)) < 4500) { // If we are too far off or too close we don't do track following
crosstrack_error = sin(radians((target_bearing - crosstrack_bearing) / (float)100)) * (float)wp_distance; // Meters we are off track line
crosstrack_error = sinf(radians((target_bearing - crosstrack_bearing) / (float)100)) * (float)wp_distance; // Meters we are off track line
nav_bearing += constrain(crosstrack_error * g.crosstrack_gain, -g.crosstrack_entry_angle.get(), g.crosstrack_entry_angle.get());
nav_bearing = wrap_360(nav_bearing);
}

8
ArduCopter/ArduCopter.pde
View File

@ -630,7 +630,7 @@ static int8_t CH7_wp_index;
// Battery Sensors
////////////////////////////////////////////////////////////////////////////////
// Battery Voltage of battery, initialized above threshold for filter
static float battery_voltage1 = LOW_VOLTAGE * 1.05;
static float battery_voltage1 = LOW_VOLTAGE * 1.05f;
// refers to the instant amp draw – based on an Attopilot Current sensor
static float current_amps1;
// refers to the total amps drawn – based on an Attopilot Current sensor
@ -1741,11 +1741,11 @@ void update_simple_mode(void)
if (simple_counter == 1) {
// roll
simple_cos_x = sin(radians(90 - delta));
simple_cos_x = sinf(radians(90 - delta));
}else if (simple_counter > 2) {
// pitch
simple_sin_y = cos(radians(90 - delta));
simple_sin_y = cosf(radians(90 - delta));
simple_counter = 0;
}
@ -2132,7 +2132,7 @@ static void update_altitude_est()
}
static void tuning(){
tuning_value = (float)g.rc_6.control_in / 1000.0;
tuning_value = (float)g.rc_6.control_in / 1000.0f;
g.rc_6.set_range(g.radio_tuning_low,g.radio_tuning_high); // 0 to 1
switch(g.radio_tuning) {

10
ArduCopter/Attitude.pde
View File

@ -708,7 +708,7 @@ static void update_throttle_cruise(int16_t throttle)
}
// calc average throttle if we are in a level hover
if (throttle > g.throttle_min && abs(climb_rate) < 60 && labs(ahrs.roll_sensor) < 500 && labs(ahrs.pitch_sensor) < 500) {
throttle_avg = throttle_avg * .99 + (float)throttle * .01;
throttle_avg = throttle_avg * 0.99f + (float)throttle * 0.01f;
g.throttle_cruise = throttle_avg;
}
}
@ -802,7 +802,7 @@ get_throttle_accel(int16_t z_target_accel)
z_accel_error = 0;
} else {
// calculate accel error and Filter with fc = 2 Hz
z_accel_error = z_accel_error + 0.11164 * (constrain(z_target_accel - z_accel_meas, -32000, 32000) - z_accel_error);
z_accel_error = z_accel_error + 0.11164f * (constrain(z_target_accel - z_accel_meas, -32000, 32000) - z_accel_error);
}
last_call_ms = now;
@ -937,7 +937,7 @@ get_throttle_rate(int16_t z_target_speed)
z_rate_error = 0;
} else {
// calculate rate error and filter with cut off frequency of 2 Hz
z_rate_error = z_rate_error + 0.20085 * ((z_target_speed - climb_rate) - z_rate_error);
z_rate_error = z_rate_error + 0.20085f * ((z_target_speed - climb_rate) - z_rate_error);
}
last_call_ms = now;
@ -1039,7 +1039,7 @@ get_throttle_althold_with_slew(int16_t target_alt, int16_t min_climb_rate, int16
static void
get_throttle_rate_stabilized(int16_t target_rate)
{
controller_desired_alt += target_rate * 0.02;
controller_desired_alt += target_rate * 0.02f;
// do not let target altitude get too far from current altitude
controller_desired_alt = constrain(controller_desired_alt,current_loc.alt-750,current_loc.alt+750);
@ -1098,7 +1098,7 @@ get_throttle_surface_tracking(int16_t target_rate)
}
last_call_ms = now;
target_sonar_alt += target_rate * 0.02;
target_sonar_alt += target_rate * 0.02f;
distance_error = (target_sonar_alt-sonar_alt);
sonar_induced_slew_rate = constrain(fabs(THR_SURFACE_TRACKING_P * distance_error),0,THR_SURFACE_TRACKING_VELZ_MAX);

60
ArduCopter/GCS_Mavlink.pde
View File

@ -198,7 +198,7 @@ static NOINLINE void send_extended_status1(mavlink_channel_t chan, uint16_t pack
uint8_t battery_remaining = -1;
if (current_total1 != 0 && g.pack_capacity != 0) {
battery_remaining = (100.0 * (g.pack_capacity - current_total1) / g.pack_capacity);
battery_remaining = (100.0f * (g.pack_capacity - current_total1) / g.pack_capacity);
}
if (current_total1 != 0) {
battery_current = current_amps1 * 100;
@ -264,12 +264,12 @@ static void NOINLINE send_nav_controller_output(mavlink_channel_t chan)
{
mavlink_msg_nav_controller_output_send(
chan,
nav_roll / 1.0e2,
nav_pitch / 1.0e2,
wp_bearing / 1.0e2,
wp_bearing / 1.0e2,
wp_distance / 1.0e2,
altitude_error / 1.0e2,
nav_roll / 1.0e2f,
nav_pitch / 1.0e2f,
wp_bearing / 1.0e2f,
wp_bearing / 1.0e2f,
wp_distance / 1.0e2f,
altitude_error / 1.0e2f,
0,
crosstrack_error); // was 0
}
@ -434,12 +434,12 @@ static void NOINLINE send_vfr_hud(mavlink_channel_t chan)
{
mavlink_msg_vfr_hud_send(
chan,
(float)g_gps->ground_speed / 100.0,
(float)g_gps->ground_speed / 100.0,
(float)g_gps->ground_speed / 100.0f,
(float)g_gps->ground_speed / 100.0f,
(ahrs.yaw_sensor / 100) % 360,
g.rc_3.servo_out/10,
current_loc.alt / 100.0,
climb_rate / 100.0);
current_loc.alt / 100.0f,
climb_rate / 100.0f);
}
static void NOINLINE send_raw_imu1(mavlink_channel_t chan)
@ -449,12 +449,12 @@ static void NOINLINE send_raw_imu1(mavlink_channel_t chan)
mavlink_msg_raw_imu_send(
chan,
micros(),
accel.x * 1000.0 / GRAVITY_MSS,
accel.y * 1000.0 / GRAVITY_MSS,
accel.z * 1000.0 / GRAVITY_MSS,
gyro.x * 1000.0,
gyro.y * 1000.0,
gyro.z * 1000.0,
accel.x * 1000.0f / GRAVITY_MSS,
accel.y * 1000.0f / GRAVITY_MSS,
accel.z * 1000.0f / GRAVITY_MSS,
gyro.x * 1000.0f,
gyro.y * 1000.0f,
gyro.z * 1000.0f,
compass.mag_x,
compass.mag_y,
compass.mag_z);
@ -465,8 +465,8 @@ static void NOINLINE send_raw_imu2(mavlink_channel_t chan)
mavlink_msg_scaled_pressure_send(
chan,
millis(),
(float)barometer.get_pressure()/100.0,
(float)(barometer.get_pressure() - barometer.get_ground_pressure())/100.0,
(float)barometer.get_pressure()/100.0f,
(float)(barometer.get_pressure() - barometer.get_ground_pressure())/100.0f,
(int)(barometer.get_temperature()*10));
}
@ -1344,10 +1344,10 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
if (tell_command.id < MAV_CMD_NAV_LAST) {
// command needs scaling
x = tell_command.lat/1.0e7; // local (x), global (latitude)
y = tell_command.lng/1.0e7; // local (y), global (longitude)
x = tell_command.lat/1.0e7f; // local (x), global (latitude)
y = tell_command.lng/1.0e7f; // local (y), global (longitude)
// ACM is processing alt inside each command. so we save and load raw values. - this is diffrent to APM
z = tell_command.alt/1.0e2; // local (z), global/relative (altitude)
z = tell_command.alt/1.0e2f; // local (z), global/relative (altitude)
}
// Switch to map APM command fields into MAVLink command fields
@ -1594,7 +1594,7 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
* case MAV_FRAME_LOCAL: // local (relative to home position)
* {
* tell_command.lat = 1.0e7*ToDeg(packet.x/
* (radius_of_earth*cos(ToRad(home.lat/1.0e7)))) + home.lat;
* (radius_of_earth*cosf(ToRad(home.lat/1.0e7)))) + home.lat;
* tell_command.lng = 1.0e7*ToDeg(packet.y/radius_of_earth) + home.lng;
* tell_command.alt = packet.z*1.0e2;
* tell_command.options = MASK_OPTIONS_RELATIVE_ALT;
@ -1613,9 +1613,9 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
*/
// we only are supporting Abs position, relative Alt
tell_command.lat = 1.0e7 * packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7 * packet.y; // in as DD converted to * t7
tell_command.alt = packet.z * 1.0e2;
tell_command.lat = 1.0e7f * packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7f * packet.y; // in as DD converted to * t7
tell_command.alt = packet.z * 1.0e2f;
tell_command.options = 1; // store altitude relative to home alt!! Always!!
switch (tell_command.id) { // Switch to map APM command fields into MAVLink command fields
@ -1865,7 +1865,7 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
mavlink_msg_hil_state_decode(msg, &packet);
float vel = pythagorous2(packet.vx, packet.vy);
float cog = wrap_360(ToDeg(atan2(packet.vx, packet.vy)) * 100);
float cog = wrap_360(ToDeg(atan2f(packet.vx, packet.vy)) * 100);
// set gps hil sensor
g_gps->setHIL(packet.time_usec/1000,
@ -2050,8 +2050,8 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
send_text_P(SEVERITY_LOW,PSTR("bad fence point"));
} else {
Vector2l point;
point.x = packet.lat*1.0e7;
point.y = packet.lng*1.0e7;
point.x = packet.lat*1.0e7f;
point.y = packet.lng*1.0e7f;
geofence_limit.set_fence_point_with_index(point, packet.idx);
}
break;
@ -2067,7 +2067,7 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
} else {
Vector2l point = geofence_limit.get_fence_point_with_index(packet.idx);
mavlink_msg_fence_point_send(chan, 0, 0, packet.idx, geofence_limit.fence_total(),
point.x*1.0e-7, point.y*1.0e-7);
point.x*1.0e-7f, point.y*1.0e-7f);
}
break;
}

9
ArduCopter/Log.pde
View File

@ -312,8 +312,8 @@ static void Log_Write_Current()
LOG_PACKET_HEADER_INIT(LOG_CURRENT_MSG),
throttle_in : g.rc_3.control_in,
throttle_integrator : throttle_integrator,
battery_voltage : (int16_t) (battery_voltage1 * 100.0),
current_amps : (int16_t) (current_amps1 * 100.0),
battery_voltage : (int16_t) (battery_voltage1 * 100.0f),
current_amps : (int16_t) (current_amps1 * 100.0f),
current_total : (int16_t) current_total1
};
DataFlash.WriteBlock(&pkt, sizeof(pkt));
@ -329,8 +329,8 @@ static void Log_Read_Current()
cliSerial->printf_P(PSTR("CURR, %d, %lu, %4.4f, %4.4f, %d\n"),
(int)pkt.throttle_in,
(unsigned long)pkt.throttle_integrator,
(float)pkt.battery_voltage/100.f,
(float)pkt.current_amps/100.f,
(float)pkt.battery_voltage/100.0f,
(float)pkt.current_amps/100.0f,
(int)pkt.current_total);
}
@ -1159,7 +1159,6 @@ static void Log_Read_Camera()
{
struct log_Camera pkt;
DataFlash.ReadPacket(&pkt, sizeof(pkt));
// 1
cliSerial->printf_P(PSTR("CAMERA, %lu, "),(unsigned long)pkt.gps_time); // 1 time
print_latlon(cliSerial, pkt.latitude); // 2 lat

6
ArduCopter/commands.pde
View File

@ -188,9 +188,9 @@ static void init_home()
Log_Write_Cmd(0, &home);
// update navigation scalers. used to offset the shrinking longitude as we go towards the poles
float rads = (fabs((float)next_WP.lat)/t7) * 0.0174532925;
scaleLongDown = cos(rads);
scaleLongUp = 1.0f/cos(rads);
float rads = (fabsf((float)next_WP.lat)/t7) * 0.0174532925f;
scaleLongDown = cosf(rads);
scaleLongUp = 1.0f/cosf(rads);
// Save prev loc this makes the calcs look better before commands are loaded
prev_WP = home;

4
ArduCopter/commands_logic.pde
View File

@ -824,7 +824,7 @@ static void do_repeat_servo()
event_timer = 0;
event_value = command_cond_queue.alt;
event_repeat = command_cond_queue.lat * 2;
event_delay = command_cond_queue.lng * 500.0; // /2 (half cycle time) * 1000 (convert to milliseconds)
event_delay = command_cond_queue.lng * 500.0f; // /2 (half cycle time) * 1000 (convert to milliseconds)
switch(command_cond_queue.p1) {
case CH_5:
@ -848,7 +848,7 @@ static void do_repeat_relay()
{
event_id = RELAY_TOGGLE;
event_timer = 0;
event_delay = command_cond_queue.lat * 500.0; // /2 (half cycle time) * 1000 (convert to milliseconds)
event_delay = command_cond_queue.lat * 500.0f; // /2 (half cycle time) * 1000 (convert to milliseconds)
event_repeat = command_cond_queue.alt * 2;
update_events();
}

130
ArduCopter/config.h
View File

@ -114,7 +114,7 @@
# define RC_FAST_SPEED 125
# define RTL_YAW YAW_LOOK_AT_HOME
# define TILT_COMPENSATION 5
# define RATE_INTEGRATOR_LEAK_RATE 0.02
# define RATE_INTEGRATOR_LEAK_RATE 0.02f
# define RATE_ROLL_D 0
# define RATE_PITCH_D 0
# define HELI_PITCH_FF 0
@ -377,17 +377,17 @@
// Battery monitoring
//
#ifndef LOW_VOLTAGE
# define LOW_VOLTAGE 9.6
# define LOW_VOLTAGE 9.6f
#endif
#ifndef VOLT_DIV_RATIO
# define VOLT_DIV_RATIO 3.56
# define VOLT_DIV_RATIO 3.56f
#endif
#ifndef CURR_AMP_PER_VOLT
# define CURR_AMP_PER_VOLT 27.32
# define CURR_AMP_PER_VOLT 27.32f
#endif
#ifndef CURR_AMPS_OFFSET
# define CURR_AMPS_OFFSET 0.0
# define CURR_AMPS_OFFSET 0.0f
#endif
#ifndef HIGH_DISCHARGE
# define HIGH_DISCHARGE 1760
@ -404,7 +404,7 @@
// INPUT_VOLTAGE
//
#ifndef INPUT_VOLTAGE
# define INPUT_VOLTAGE 5.0
# define INPUT_VOLTAGE 5.0f
#endif
@ -437,22 +437,22 @@
#endif
// optical flow based loiter PI values
#ifndef OPTFLOW_ROLL_P
#define OPTFLOW_ROLL_P 2.5
#define OPTFLOW_ROLL_P 2.5f
#endif
#ifndef OPTFLOW_ROLL_I
#define OPTFLOW_ROLL_I 0.5
#define OPTFLOW_ROLL_I 0.5f
#endif
#ifndef OPTFLOW_ROLL_D
#define OPTFLOW_ROLL_D 0.12
#define OPTFLOW_ROLL_D 0.12f
#endif
#ifndef OPTFLOW_PITCH_P
#define OPTFLOW_PITCH_P 2.5
#define OPTFLOW_PITCH_P 2.5f
#endif
#ifndef OPTFLOW_PITCH_I
#define OPTFLOW_PITCH_I 0.5
#define OPTFLOW_PITCH_I 0.5f
#endif
#ifndef OPTFLOW_PITCH_D
#define OPTFLOW_PITCH_D 0.12
#define OPTFLOW_PITCH_D 0.12f
#endif
#ifndef OPTFLOW_IMAX
#define OPTFLOW_IMAX 1
@ -543,7 +543,7 @@
// Y6 Support
#ifndef TOP_BOTTOM_RATIO
# define TOP_BOTTOM_RATIO 1.00
# define TOP_BOTTOM_RATIO 1.00f
#endif
@ -738,26 +738,26 @@
// Extra motor values that are changed from time to time by jani @ jDrones as software
// and charachteristics changes.
#ifdef MOTORS_JD880
# define STABILIZE_ROLL_P 3.7
# define STABILIZE_ROLL_I 0.0
# define STABILIZE_ROLL_IMAX 8.0 // degrees
# define STABILIZE_PITCH_P 3.7
# define STABILIZE_PITCH_I 0.0
# define STABILIZE_PITCH_IMAX 8.0 // degrees
# define STABILIZE_ROLL_P 3.7f
# define STABILIZE_ROLL_I 0.0f
# define STABILIZE_ROLL_IMAX 8.0f // degrees
# define STABILIZE_PITCH_P 3.7f
# define STABILIZE_PITCH_I 0.0f
# define STABILIZE_PITCH_IMAX 8.0f // degrees
#endif
#ifdef MOTORS_JD850
# define STABILIZE_ROLL_P 4.2
# define STABILIZE_ROLL_I 0.0
# define STABILIZE_ROLL_IMAX 8.0 // degrees
# define STABILIZE_PITCH_P 4.2
# define STABILIZE_PITCH_I 0.0
# define STABILIZE_PITCH_IMAX 8.0 // degrees
# define STABILIZE_ROLL_P 4.2f
# define STABILIZE_ROLL_I 0.0f
# define STABILIZE_ROLL_IMAX 8.0f // degrees
# define STABILIZE_PITCH_P 4.2f
# define STABILIZE_PITCH_I 0.0f
# define STABILIZE_PITCH_IMAX 8.0f // degrees
#endif
#ifndef ACRO_P
# define ACRO_P 4.5
# define ACRO_P 4.5f
#endif
#ifndef AXIS_LOCK_ENABLED
@ -766,33 +766,33 @@
// Good for smaller payload motors.
#ifndef STABILIZE_ROLL_P
# define STABILIZE_ROLL_P 4.5
# define STABILIZE_ROLL_P 4.5f
#endif
#ifndef STABILIZE_ROLL_I
# define STABILIZE_ROLL_I 0.0
# define STABILIZE_ROLL_I 0.0f
#endif
#ifndef STABILIZE_ROLL_IMAX
# define STABILIZE_ROLL_IMAX 8.0 // degrees
# define STABILIZE_ROLL_IMAX 8.0f // degrees
#endif
#ifndef STABILIZE_PITCH_P
# define STABILIZE_PITCH_P 4.5
# define STABILIZE_PITCH_P 4.5f
#endif
#ifndef STABILIZE_PITCH_I
# define STABILIZE_PITCH_I 0.0
# define STABILIZE_PITCH_I 0.0f
#endif
#ifndef STABILIZE_PITCH_IMAX
# define STABILIZE_PITCH_IMAX 8.0 // degrees
# define STABILIZE_PITCH_IMAX 8.0f // degrees
#endif
#ifndef STABILIZE_YAW_P
# define STABILIZE_YAW_P 4.5 // increase for more aggressive Yaw Hold, decrease if it's bouncy
# define STABILIZE_YAW_P 4.5f // increase for more aggressive Yaw Hold, decrease if it's bouncy
#endif
#ifndef STABILIZE_YAW_I
# define STABILIZE_YAW_I 0.0
# define STABILIZE_YAW_I 0.0f
#endif
#ifndef STABILIZE_YAW_IMAX
# define STABILIZE_YAW_IMAX 8.0 // degrees * 100
# define STABILIZE_YAW_IMAX 8.0f // degrees * 100
#endif
#ifndef YAW_LOOK_AHEAD_MIN_SPEED
@ -811,42 +811,42 @@
# define MAX_INPUT_PITCH_ANGLE 4500
#endif
#ifndef RATE_ROLL_P
# define RATE_ROLL_P 0.150
# define RATE_ROLL_P 0.150f
#endif
#ifndef RATE_ROLL_I
# define RATE_ROLL_I 0.100
# define RATE_ROLL_I 0.100f
#endif
#ifndef RATE_ROLL_D
# define RATE_ROLL_D 0.004
# define RATE_ROLL_D 0.004f
#endif
#ifndef RATE_ROLL_IMAX
# define RATE_ROLL_IMAX 5.0 // degrees
# define RATE_ROLL_IMAX 5.0f // degrees
#endif
#ifndef RATE_PITCH_P
# define RATE_PITCH_P 0.150
# define RATE_PITCH_P 0.150f
#endif
#ifndef RATE_PITCH_I
# define RATE_PITCH_I 0.100
# define RATE_PITCH_I 0.100f
#endif
#ifndef RATE_PITCH_D
# define RATE_PITCH_D 0.004
# define RATE_PITCH_D 0.004f
#endif
#ifndef RATE_PITCH_IMAX
# define RATE_PITCH_IMAX 5.0 // degrees
# define RATE_PITCH_IMAX 5.0f // degrees
#endif
#ifndef RATE_YAW_P
# define RATE_YAW_P 0.25
# define RATE_YAW_P 0.25f
#endif
#ifndef RATE_YAW_I
# define RATE_YAW_I 0.015
# define RATE_YAW_I 0.015f
#endif
#ifndef RATE_YAW_D
# define RATE_YAW_D 0.000
# define RATE_YAW_D 0.000f
#endif
#ifndef RATE_YAW_IMAX
# define RATE_YAW_IMAX 8.0 // degrees
# define RATE_YAW_IMAX 8.0f // degrees
#endif
@ -882,10 +882,10 @@
// Loiter control gains
//
#ifndef LOITER_P
# define LOITER_P .20
# define LOITER_P .20f
#endif
#ifndef LOITER_I
# define LOITER_I 0.0
# define LOITER_I 0.0f
#endif
#ifndef LOITER_IMAX
# define LOITER_IMAX 30 // degrees
@ -896,7 +896,7 @@
# define LOITER_REPOSITIONING DISABLED
#endif
#ifndef LOITER_REPOSITION_RATE
# define LOITER_REPOSITION_RATE 500.0 // cm/s
# define LOITER_REPOSITION_RATE 500.0f // cm/s
#endif
@ -904,13 +904,13 @@
// Loiter Navigation control gains
//
#ifndef LOITER_RATE_P
# define LOITER_RATE_P 5.0 //
# define LOITER_RATE_P 5.0f //
#endif
#ifndef LOITER_RATE_I
# define LOITER_RATE_I 0.04 // Wind control
# define LOITER_RATE_I 0.04f // Wind control
#endif
#ifndef LOITER_RATE_D
# define LOITER_RATE_D 0.40 // try 2 or 3 for LOITER_RATE 1
# define LOITER_RATE_D 0.40f // try 2 or 3 for LOITER_RATE 1
#endif
#ifndef LOITER_RATE_IMAX
# define LOITER_RATE_IMAX 30 // degrees
@ -920,13 +920,13 @@
// WP Navigation control gains
//
#ifndef NAV_P
# define NAV_P 2.4 //
# define NAV_P 2.4f //
#endif
#ifndef NAV_I
# define NAV_I 0.17 // Wind control
# define NAV_I 0.17f // Wind control
#endif
#ifndef NAV_D
# define NAV_D 0.00 // .95
# define NAV_D 0.00f // .95
#endif
#ifndef NAV_IMAX
# define NAV_IMAX 18 // degrees
@ -963,10 +963,10 @@
#endif
#ifndef ALT_HOLD_P
# define ALT_HOLD_P 2.0
# define ALT_HOLD_P 2.0f
#endif
#ifndef ALT_HOLD_I
# define ALT_HOLD_I 0.0
# define ALT_HOLD_I 0.0f
#endif
#ifndef ALT_HOLD_IMAX
# define ALT_HOLD_IMAX 300
@ -974,13 +974,13 @@
// RATE control
#ifndef THROTTLE_P
# define THROTTLE_P 6.0
# define THROTTLE_P 6.0f
#endif
#ifndef THROTTLE_I
# define THROTTLE_I 0.0
# define THROTTLE_I 0.0f
#endif
#ifndef THROTTLE_D
# define THROTTLE_D 0.2
# define THROTTLE_D 0.2f
#endif
#ifndef THROTTLE_IMAX
@ -1004,13 +1004,13 @@
// Throttle Accel control
#ifndef THROTTLE_ACCEL_P
# define THROTTLE_ACCEL_P 0.75
# define THROTTLE_ACCEL_P 0.75f
#endif
#ifndef THROTTLE_ACCEL_I
# define THROTTLE_ACCEL_I 1.50
# define THROTTLE_ACCEL_I 1.50f
#endif
#ifndef THROTTLE_ACCEL_D
# define THROTTLE_ACCEL_D 0.0
# define THROTTLE_ACCEL_D 0.0f
#endif
#ifndef THROTTLE_ACCEL_IMAX
# define THROTTLE_ACCEL_IMAX 500
@ -1021,7 +1021,7 @@
// Crosstrack compensation
//
#ifndef CROSSTRACK_GAIN
# define CROSSTRACK_GAIN .2
# define CROSSTRACK_GAIN .2f
#endif
#ifndef CROSSTRACK_MIN_DISTANCE
# define CROSSTRACK_MIN_DISTANCE 15

8
ArduCopter/control_modes.pde
View File

@ -176,8 +176,8 @@ static void read_trim_switch()
static void save_trim()
{
// save roll and pitch trim
float roll_trim = ToRad((float)g.rc_1.control_in/100.0);
float pitch_trim = ToRad((float)g.rc_2.control_in/100.0);
float roll_trim = ToRad((float)g.rc_1.control_in/100.0f);
float pitch_trim = ToRad((float)g.rc_2.control_in/100.0f);
ahrs.add_trim(roll_trim, pitch_trim);
}
@ -192,10 +192,10 @@ static void auto_trim()
led_mode = SAVE_TRIM_LEDS;
// calculate roll trim adjustment
float roll_trim_adjustment = ToRad((float)-g.rc_1.control_in / 4000.0);
float roll_trim_adjustment = ToRad((float)-g.rc_1.control_in / 4000.0f);
// calculate pitch trim adjustment
float pitch_trim_adjustment = ToRad((float)g.rc_2.control_in / 4000.0);
float pitch_trim_adjustment = ToRad((float)g.rc_2.control_in / 4000.0f);
// make sure accelerometer values impact attitude quickly
ahrs.set_fast_gains(true);

8
ArduCopter/defines.h
View File

@ -346,8 +346,8 @@ enum gcs_severity {
#define DATA_RTL_REACHED_ALT 31
// battery monitoring macros
#define BATTERY_VOLTAGE(x) (x*(g.input_voltage/1024.0))*g.volt_div_ratio
#define CURRENT_AMPS(x) ((x*(g.input_voltage/1024.0))-CURR_AMPS_OFFSET)*g.curr_amp_per_volt
#define BATTERY_VOLTAGE(x) (x*(g.input_voltage/1024.0f))*g.volt_div_ratio
#define CURRENT_AMPS(x) ((x*(g.input_voltage/1024.0f))-CURR_AMPS_OFFSET)*g.curr_amp_per_volt
/* ************************************************************** */
/* Expansion PIN's that people can use for various things. */
@ -394,8 +394,8 @@ enum gcs_severity {
#define PIEZO_PIN AN5 //Last pin on the back ADC connector
// RADIANS
#define RADX100 0.000174532925
#define DEGX100 5729.57795
#define RADX100 0.000174532925f
#define DEGX100 5729.57795f
// EEPROM addresses

24
ArduCopter/navigation.pde
View File

@ -13,11 +13,11 @@ static void update_navigation()
// used to calculate speed in X and Y, iterms
// ------------------------------------------
dTnav = (float)(millis() - nav_last_gps_update)/ 1000.0;
dTnav = (float)(millis() - nav_last_gps_update)/ 1000.0f;
nav_last_gps_update = millis();
// prevent runup from bad GPS
dTnav = min(dTnav, 1.0);
dTnav = min(dTnav, 1.0f);
// save GPS time
nav_last_gps_time = g_gps->time;
@ -34,7 +34,7 @@ static void update_navigation()
// check for inertial nav updates
if( inertial_nav.position_ok() ) {
// 50hz
dTnav = 0.02; // To-Do: calculate the time from the mainloop or INS readings?
dTnav = 0.02f; // To-Do: calculate the time from the mainloop or INS readings?
// signal to run nav controllers
pos_updated = true;
@ -108,7 +108,7 @@ static void calc_velocity_and_position(){
}
// this speed is ~ in cm because we are using 10^7 numbers from GPS
float tmp = 1.0/dTnav;
float tmp = 1.0f/dTnav;
#if INERTIAL_NAV_XY == ENABLED
if( inertial_nav.position_ok() ) {
@ -338,11 +338,11 @@ static void update_nav_wp()
//1 degree = 0.0174532925 radians
// wrap
if (circle_angle > 6.28318531)
circle_angle -= 6.28318531;
if (circle_angle > 6.28318531f)
circle_angle -= 6.28318531f;
next_WP.lng = circle_WP.lng + (g.circle_radius * 100 * cos(1.57 - circle_angle) * scaleLongUp);
next_WP.lat = circle_WP.lat + (g.circle_radius * 100 * sin(1.57 - circle_angle));
next_WP.lng = circle_WP.lng + (g.circle_radius * 100 * cosf(1.57f - circle_angle) * scaleLongUp);
next_WP.lat = circle_WP.lat + (g.circle_radius * 100 * sinf(1.57f - circle_angle));
// use error as the desired rate towards the target
// nav_lon, nav_lat is calculated
@ -563,8 +563,8 @@ static void calc_nav_rate(int16_t max_speed)
// rotate by 90 to deal with trig functions
temp = (9000l - wp_bearing) * RADX100;
temp_x = cos(temp);
temp_y = sin(temp);
temp_x = cosf(temp);
temp_y = sinf(temp);
// rotate desired spped vector:
int32_t x_target_speed = max_speed * temp_x - cross_speed * temp_y;
@ -633,7 +633,7 @@ static int16_t get_desired_speed(int16_t max_speed)
int32_t s_min = WAYPOINT_SPEED_MIN;
temp += s_min * s_min;
if( temp < 0 ) temp = 0; // check to ensure we don't try to take the sqrt of a negative number
max_speed = sqrt((float)temp);
max_speed = sqrtf((float)temp);
max_speed = min(max_speed, g.waypoint_speed_max);
}
}
@ -657,7 +657,7 @@ static void update_crosstrack(void)
abs(wrap_180(wp_bearing - original_wp_bearing)) < 4500) {
float temp = (wp_bearing - original_wp_bearing) * RADX100;
crosstrack_error = sin(temp) * wp_distance; // Meters we are off track line
crosstrack_error = sinf(temp) * wp_distance; // Meters we are off track line
}else{
// fade out crosstrack
crosstrack_error >>= 1;

12
ArduCopter/sensors.pde
View File

@ -10,9 +10,9 @@ static void ReadSCP1000(void) {
static void init_sonar(void)
{
#if CONFIG_SONAR_SOURCE == SONAR_SOURCE_ADC
sonar->calculate_scaler(g.sonar_type, 3.3);
sonar->calculate_scaler(g.sonar_type, 3.3f);
#else
sonar->calculate_scaler(g.sonar_type, 5.0);
sonar->calculate_scaler(g.sonar_type, 5.0f);
#endif
}
#endif
@ -28,7 +28,7 @@ static void init_barometer(void)
static int32_t read_barometer(void)
{
barometer.read();
return baro_filter.apply(barometer.get_altitude() * 100.0);
return baro_filter.apply(barometer.get_altitude() * 100.0f);
}
// return sonar altitude in centimeters
@ -37,7 +37,7 @@ static int16_t read_sonar(void)
#if CONFIG_SONAR == ENABLED
int16_t temp_alt = sonar->read();
if (temp_alt >= sonar->min_distance && temp_alt <= sonar->max_distance * 0.70) {
if (temp_alt >= sonar->min_distance && temp_alt <= sonar->max_distance * 0.70f) {
if ( sonar_alt_health < SONAR_ALT_HEALTH_MAX ) {
sonar_alt_health++;
}
@ -48,7 +48,7 @@ static int16_t read_sonar(void)
#if SONAR_TILT_CORRECTION == 1
// correct alt for angle of the sonar
float temp = cos_pitch_x * cos_roll_x;
temp = max(temp, 0.707);
temp = max(temp, 0.707f);
temp_alt = (float)temp_alt * temp;
#endif
@ -117,7 +117,7 @@ static void read_battery(void)
if(g.battery_monitoring == 4) {
batt_curr_analog_source->set_pin(g.battery_curr_pin);
current_amps1 = CURRENT_AMPS(batt_curr_analog_source->read_average());
current_total1 += current_amps1 * 0.02778; // called at 100ms on average, .0002778 is 1/3600 (conversion to hours)
current_total1 += current_amps1 * 0.02778f; // called at 100ms on average, .0002778 is 1/3600 (conversion to hours)
}
// check for low voltage or current if the low voltage check hasn't already been triggered

6
ArduCopter/test.pde
View File

@ -201,7 +201,7 @@ test_radio_pwm(uint8_t argc, const Menu::arg *argv)
for(int16_t i = 0; i < 200; i++){
int32_t temp = 2 * 100 * (wp_distance - g.waypoint_radius * 100);
max_speed = sqrt((float)temp);
max_speed = sqrtf((float)temp);
max_speed = min(max_speed, g.waypoint_speed_max);
cliSerial->printf("Zspeed: %ld, %d, %ld\n", temp, max_speed, wp_distance);
wp_distance += 100;
@ -561,8 +561,8 @@ test_gps(uint8_t argc, const Menu::arg *argv)
* temp.c.x, temp.c.y, temp.c.z);
*
* int16_t _pitch = degrees(-asin(temp.c.x));
* int16_t _roll = degrees(atan2(temp.c.y, temp.c.z));
* int16_t _yaw = degrees(atan2(temp.b.x, temp.a.x));
* int16_t _roll = degrees(atan2f(temp.c.y, temp.c.z));
* int16_t _yaw = degrees(atan2f(temp.b.x, temp.a.x));
* cliSerial->printf_P(PSTR( "angles\n"
* "%d \t %d \t %d\n\n"),
* _pitch,

2
ArduCopter/toy.pde
View File

@ -116,7 +116,7 @@ void roll_pitch_toy()
get_acro_yaw(0);
yaw_timer--;
if((yaw_timer == 0) || (fabs(omega.z) < .17)) {
if((yaw_timer == 0) || (fabsf(omega.z) < 0.17f)) {
ap_system.yaw_stopped = true;
nav_yaw = ahrs.yaw_sensor;
}

12
ArduPlane/Attitude.pde
View File

@ -94,7 +94,7 @@ static void stabilize_pitch(float speed_scaler)
{
#if APM_CONTROL == DISABLED
int32_t tempcalc = nav_pitch_cd +
fabs(ahrs.roll_sensor * g.kff_pitch_compensation) +
fabsf(ahrs.roll_sensor * g.kff_pitch_compensation) +
(g.channel_throttle.servo_out * g.kff_throttle_to_pitch) -
(ahrs.pitch_sensor - g.pitch_trim_cd);
if (inverted_flight) {
@ -123,12 +123,12 @@ static void stabilize_stick_mixing()
float ch2_inf;
ch1_inf = (float)g.channel_roll.radio_in - (float)g.channel_roll.radio_trim;
ch1_inf = fabs(ch1_inf);
ch1_inf = fabsf(ch1_inf);
ch1_inf = min(ch1_inf, 400.0);
ch1_inf = ((400.0 - ch1_inf) /400.0);
ch2_inf = (float)g.channel_pitch.radio_in - g.channel_pitch.radio_trim;
ch2_inf = fabs(ch2_inf);
ch2_inf = fabsf(ch2_inf);
ch2_inf = min(ch2_inf, 400.0);
ch2_inf = ((400.0 - ch2_inf) /400.0);
@ -156,7 +156,7 @@ static void stabilize_yaw(float speed_scaler)
// important for steering on the ground during landing
// -----------------------------------------------
ch4_inf = (float)g.channel_rudder.radio_in - (float)g.channel_rudder.radio_trim;
ch4_inf = fabs(ch4_inf);
ch4_inf = fabsf(ch4_inf);
ch4_inf = min(ch4_inf, 400.0);
ch4_inf = ((400.0 - ch4_inf) /400.0);
}
@ -328,7 +328,7 @@ static void calc_nav_roll()
}
// Bank angle = V*R/g, where V is airspeed, R is turn rate, and g is gravity.
nav_roll = ToDeg(atan(speed*turn_rate/GRAVITY_MSS)*100);
nav_roll = ToDeg(atanf(speed*turn_rate/GRAVITY_MSS)*100);
#else
// this is the old nav_roll calculation. We will use this for 2.50
@ -362,7 +362,7 @@ static void throttle_slew_limit(int16_t last_throttle)
// if slew limit rate is set to zero then do not slew limit
if (g.throttle_slewrate) {
// limit throttle change by the given percentage per second
float temp = g.throttle_slewrate * G_Dt * 0.01 * fabs(g.channel_throttle.radio_max - g.channel_throttle.radio_min);
float temp = g.throttle_slewrate * G_Dt * 0.01 * fabsf(g.channel_throttle.radio_max - g.channel_throttle.radio_min);
// allow a minimum change of 1 PWM per cycle
if (temp < 1) {
temp = 1;

32
ArduPlane/GCS_Mavlink.pde
View File

@ -479,7 +479,7 @@ static void NOINLINE send_wind(mavlink_channel_t chan)
Vector3f wind = ahrs.wind_estimate();
mavlink_msg_wind_send(
chan,
degrees(atan2(-wind.y, -wind.x)), // use negative, to give
degrees(atan2f(-wind.y, -wind.x)), // use negative, to give
// direction wind is coming from
wind.length(),
wind.z);
@ -1467,9 +1467,9 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
case MAV_FRAME_MISSION:
case MAV_FRAME_GLOBAL:
{
tell_command.lat = 1.0e7*packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7*packet.y; // in as DD converted to * t7
tell_command.alt = packet.z*1.0e2; // in as m converted to cm
tell_command.lat = 1.0e7f*packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7f*packet.y; // in as DD converted to * t7
tell_command.alt = packet.z*1.0e2f; // in as m converted to cm
tell_command.options = 0; // absolute altitude
break;
}
@ -1477,10 +1477,10 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
#ifdef MAV_FRAME_LOCAL_NED
case MAV_FRAME_LOCAL_NED: // local (relative to home position)
{
tell_command.lat = 1.0e7*ToDeg(packet.x/
(radius_of_earth*cos(ToRad(home.lat/1.0e7)))) + home.lat;
tell_command.lng = 1.0e7*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = -packet.z*1.0e2;
tell_command.lat = 1.0e7f*ToDeg(packet.x/
(radius_of_earth*cosf(ToRad(home.lat/1.0e7f)))) + home.lat;
tell_command.lng = 1.0e7f*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = -packet.z*1.0e2f;
tell_command.options = MASK_OPTIONS_RELATIVE_ALT;
break;
}
@ -1489,10 +1489,10 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
#ifdef MAV_FRAME_LOCAL
case MAV_FRAME_LOCAL: // local (relative to home position)
{
tell_command.lat = 1.0e7*ToDeg(packet.x/
(radius_of_earth*cos(ToRad(home.lat/1.0e7)))) + home.lat;
tell_command.lng = 1.0e7*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = packet.z*1.0e2;
tell_command.lat = 1.0e7f*ToDeg(packet.x/
(radius_of_earth*cosf(ToRad(home.lat/1.0e7f)))) + home.lat;
tell_command.lng = 1.0e7f*ToDeg(packet.y/radius_of_earth) + home.lng;
tell_command.alt = packet.z*1.0e2f;
tell_command.options = MASK_OPTIONS_RELATIVE_ALT;
break;
}
@ -1500,9 +1500,9 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
case MAV_FRAME_GLOBAL_RELATIVE_ALT: // absolute lat/lng, relative altitude
{
tell_command.lat = 1.0e7 * packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7 * packet.y; // in as DD converted to * t7
tell_command.alt = packet.z * 1.0e2;
tell_command.lat = 1.0e7f * packet.x; // in as DD converted to * t7
tell_command.lng = 1.0e7f * packet.y; // in as DD converted to * t7
tell_command.alt = packet.z * 1.0e2f;
tell_command.options = MASK_OPTIONS_RELATIVE_ALT; // store altitude relative!! Always!!
break;
}
@ -1800,7 +1800,7 @@ mission_failed:
mavlink_msg_hil_state_decode(msg, &packet);
float vel = pythagorous2(packet.vx, packet.vy);
float cog = wrap_360_cd(ToDeg(atan2(packet.vy, packet.vx)) * 100);
float cog = wrap_360_cd(ToDeg(atan2f(packet.vy, packet.vx)) * 100);
if (g_gps != NULL) {
// set gps hil sensor

10
ArduPlane/navigation.pde
View File

@ -53,7 +53,7 @@ static void navigate()
// Disabled for now
void calc_distance_error()
{
distance_estimate += (float)g_gps->ground_speed * .0002 * cos(radians(bearing_error_cd * .01));
distance_estimate += (float)g_gps->ground_speed * .0002f * cosf(radians(bearing_error_cd * .01f));
distance_estimate -= DST_EST_GAIN * (float)(distance_estimate - GPS_wp_distance);
wp_distance = max(distance_estimate,10);
}
@ -165,7 +165,7 @@ static void update_loiter()
* if (wp_distance < g.loiter_radius){
* nav_bearing += 9000;
* }else{
* nav_bearing -= 100 * M_PI / 180 * asin(g.loiter_radius / wp_distance);
* nav_bearing -= 100 * M_PI / 180 * asinf(g.loiter_radius / wp_distance);
* }
*
* update_crosstrack();
@ -182,9 +182,9 @@ static void update_crosstrack(void)
Vector2f wind2d = Vector2f(wind.x, wind.y);
float speed;
if (ahrs.airspeed_estimate(&speed)) {
Vector2f nav_vector = Vector2f(cos(radians(nav_bearing_cd*0.01)), sin(radians(nav_bearing_cd*0.01))) * speed;
Vector2f nav_vector = Vector2f(cosf(radians(nav_bearing_cd*0.01)), sinf(radians(nav_bearing_cd*0.01))) * speed;
Vector2f nav_adjusted = nav_vector - wind2d;
nav_bearing_cd = degrees(atan2(nav_adjusted.y, nav_adjusted.x)) * 100;
nav_bearing_cd = degrees(atan2f(nav_adjusted.y, nav_adjusted.x)) * 100;
}
}
@ -194,7 +194,7 @@ static void update_crosstrack(void)
if (wp_totalDistance >= g.crosstrack_min_distance &&
abs(wrap_180_cd(target_bearing_cd - crosstrack_bearing_cd)) < 4500) {
// Meters we are off track line
crosstrack_error = sin(radians((target_bearing_cd - crosstrack_bearing_cd) * 0.01)) * wp_distance;
crosstrack_error = sinf(radians((target_bearing_cd - crosstrack_bearing_cd) * 0.01)) * wp_distance;
nav_bearing_cd += constrain_int32(crosstrack_error * g.crosstrack_gain, -g.crosstrack_entry_angle.get(), g.crosstrack_entry_angle.get());
nav_bearing_cd = wrap_360_cd(nav_bearing_cd);
}

4
Tools/ArduTracker/ArduTracker.pde
View File

@ -742,8 +742,8 @@ void update_GPS(void)
// Calculate new climb rate
add_altitude_data(millis()/100, gps.altitude/10);
COGX = cos(ToRad(gps.ground_course/100.0));
COGY = sin(ToRad(gps.ground_course/100.0));
COGX = cosf(ToRad(gps.ground_course/100.0));
COGY = sinf(ToRad(gps.ground_course/100.0));
}
}

38
Tools/ArduTracker/Attitude.pde
View File

@ -6,21 +6,21 @@
void stabilize()
{
float ch1_inf = 1.0;
float ch2_inf = 1.0;
float ch4_inf = 1.0;
float ch1_inf = 1.0f;
float ch2_inf = 1.0f;
float ch4_inf = 1.0f;
#if AIRSPEED_SENSOR == ENABLED
float speed_scaler = STANDARD_SPEED_SQUARED / (airspeed * airspeed);
speed_scaler = constrain(speed_scaler, 0.11, 9.0);
speed_scaler = constrain(speed_scaler, 0.11f, 9.0f);
#endif
#if AIRSPEED_SENSOR == DISABLED
float speed_scaler;
if (servo_out[CH_THROTTLE] > 0)
speed_scaler = 0.5 + (THROTTLE_CRUISE / servo_out[CH_THROTTLE] / 2.0); // First order taylor expansion of square root
speed_scaler = 0.5f + (THROTTLE_CRUISE / servo_out[CH_THROTTLE] / 2.0f); // First order taylor expansion of square root
// Should maybe be to the 2/7 power, but we aren't goint to implement that...
else
speed_scaler = 1.67;
speed_scaler = constrain(speed_scaler, 0.6, 1.67); // This case is constrained tighter as we don't have real speed info
speed_scaler = 1.67f;
speed_scaler = constrain(speed_scaler, 0.6f, 1.67f); // This case is constrained tighter as we don't have real speed info
#endif
@ -36,7 +36,7 @@ void stabilize()
// Calculate dersired servo output for the roll
// ---------------------------------------------
servo_out[CH_ROLL] = pidServoRoll.get_pid((nav_roll - dcm.roll_sensor), deltaMiliSeconds, speed_scaler);
servo_out[CH_PITCH] = pidServoPitch.get_pid((nav_pitch + fabs(dcm.roll_sensor * get(PARAM_KFF_PTCHCOMP)) - (dcm.pitch_sensor - get(PARAM_TRIM_PITCH))), deltaMiliSeconds, speed_scaler);
servo_out[CH_PITCH] = pidServoPitch.get_pid((nav_pitch + fabsf(dcm.roll_sensor * get(PARAM_KFF_PTCHCOMP)) - (dcm.pitch_sensor - get(PARAM_TRIM_PITCH))), deltaMiliSeconds, speed_scaler);
//Serial.print(" servo_out[CH_ROLL] ");
//Serial.print(servo_out[CH_ROLL],DEC);
@ -45,12 +45,12 @@ void stabilize()
if ((control_mode < FLY_BY_WIRE_A) || (ENABLE_STICK_MIXING == 1 && control_mode > FLY_BY_WIRE_B)) {
ch1_inf = (float)radio_in[CH_ROLL] - (float)radio_trim(CH_ROLL);
ch1_inf = fabs(ch1_inf);
ch1_inf = fabsf(ch1_inf);
ch1_inf = min(ch1_inf, 400.0);
ch1_inf = ((400.0 - ch1_inf) /400.0);
ch2_inf = (float)radio_in[CH_PITCH] - radio_trim(CH_PITCH);
ch2_inf = fabs(ch2_inf);
ch2_inf = fabsf(ch2_inf);
ch2_inf = min(ch2_inf, 400.0);
ch2_inf = ((400.0 - ch2_inf) /400.0);
@ -73,7 +73,7 @@ void stabilize()
// -----------------------------------------------
if (control_mode <= FLY_BY_WIRE_B || ENABLE_STICK_MIXING == 1) {
ch4_inf = (float)radio_in[CH_RUDDER] - (float)radio_trim(CH_RUDDER);
ch4_inf = fabs(ch4_inf);
ch4_inf = fabsf(ch4_inf);
ch4_inf = min(ch4_inf, 400.0);
ch4_inf = ((400.0 - ch4_inf) /400.0);
}
@ -249,19 +249,19 @@ void set_servos_4(void)
float x1,x2,y1,y2,x,y,r,z;
y1 = 110600*current_loc.lat/t7;
x1 = (PI/180)*6378137*(cos(atan(0.99664719*tan(current_loc.lat/t7*PI/180))))*(current_loc.lng/t7);
x1 = (PI/180)*6378137*(cosf(atanf(0.99664719f*tanf(current_loc.lat/t7*PI/180))))*(current_loc.lng/t7);
y2 = 110600*trackVehicle_loc.lat/t7;
x2 = (PI/180)*6378137*(cos(atan(0.99664719*tan(current_loc.lat/t7*PI/180))))*(trackVehicle_loc.lng/t7);
x2 = (PI/180)*6378137*(cosf(atanf(0.99664719f*tanf(current_loc.lat/t7*PI/180))))*(trackVehicle_loc.lng/t7);
x = abs(x2 - x1);
y = abs(y2 - y1);
r = sqrt(x*x+y*y);
z = trackVehicle_loc.alt/100.0 - current_loc.alt;
r = sqrtf(x*x+y*y);
z = trackVehicle_loc.alt/100.0f - current_loc.alt;
phi = (atan(z/r)*180/PI);
theta = (atan(x/y)*180/PI);
phi = (atanf(z/r)*180/PI);
theta = (atanf(x/y)*180/PI);
// Check to see which quadrant of the angle
if (trackVehicle_loc.lat >= current_loc.lat && trackVehicle_loc.lng >= current_loc.lng)
@ -294,8 +294,8 @@ void set_servos_4(void)
Serial.print("theta: "); Serial.println(theta);
// Outputing to the servos
servo_out[CH_ROLL] = 10000*phi/90.0;
servo_out[CH_PITCH] = 10000*theta/360.0;
servo_out[CH_ROLL] = 10000*phi/90.0f;
servo_out[CH_PITCH] = 10000*theta/360.0f;
servo_out[CH_RUDDER] = 0;
servo_out[CH_THROTTLE] = 0;

12
Tools/ArduTracker/GCS_DebugTerminal.pde
View File

@ -781,8 +781,8 @@ GCS_DEBUGTERMINAL::run_debugt_command(char *buf)
port->printf_P(PSTR("nav_pitch (%.2f) - pitch_sensor (%.2f) + pitch_comp (%.2f) = %.2f\n"),
(float)nav_pitch / 100,
(float)dcm.pitch_sensor / 100,
fabs(dcm.roll_sensor * get(PARAM_KFF_PTCHCOMP)) / 100,
(float)(nav_pitch-dcm.pitch_sensor + fabs(dcm.roll_sensor * get(PARAM_KFF_PTCHCOMP))) / 100);
fabsf(dcm.roll_sensor * get(PARAM_KFF_PTCHCOMP)) / 100,
(float)(nav_pitch-dcm.pitch_sensor + fabsf(dcm.roll_sensor * get(PARAM_KFF_PTCHCOMP))) / 100);
port->printf_P(PSTR("servo_out[CH_PITCH] (%.2f) = PID[nav_pitch + pitch_comp - pitch_sensor]"),
(float)servo_out[CH_PITCH] / 100);
@ -1275,12 +1275,12 @@ void
GCS_DEBUGTERMINAL::print_rlocation(Location *wp)
{
//float x, y;
//y = (float)(wp->lat - current_loc.lat) * 0.0111194927;
//x = (float)(wp->lng - current_loc.lng) * cos(radians(current_loc.lat)) * 0.0111194927;
//y = (float)(wp->lat - current_loc.lat) * 0.0111194927f;
//x = (float)(wp->lng - current_loc.lng) * cosf(radians(current_loc.lat)) * 0.0111194927f;
BetterStream *port = _port;
int x, y;
y = (wp->lat - current_loc.lat) * 0.0111194927;
x = (wp->lng - current_loc.lng) * cos(radians(current_loc.lat)) * 0.0111194927;
y = (wp->lat - current_loc.lat) * 0.0111194927f;
x = (wp->lng - current_loc.lng) * cosf(radians(current_loc.lat)) * 0.0111194927f;
port->printf_P(PSTR("dP = <%d%c, %d%c, %.1f> meters\n"),
abs(y), (y >= 0 ? 'N' : 'S'),
abs(x), (x >= 0 ? 'E' : 'W'),

14
Tools/ArduTracker/GCS_Mavlink.pde
View File

@ -490,18 +490,18 @@ void GCS_MAVLINK::handleMessage(mavlink_message_t* msg)
{
case MAV_FRAME_GLOBAL:
{
tell_command.lng = 1.0e7*packet.x;
tell_command.lat = 1.0e7*packet.y;
tell_command.alt = packet.z*1.0e2;
tell_command.lng = 1.0e7f*packet.x;
tell_command.lat = 1.0e7f*packet.y;
tell_command.alt = packet.z*1.0e2f;
break;
}
case MAV_FRAME_LOCAL: // local (relative to home position)
{
tell_command.lng = 1.0e7*ToDeg(packet.x/
(radius_of_earth*cos(ToRad(home.lat/1.0e7)))) + home.lng;
tell_command.lat = 1.0e7*ToDeg(packet.y/radius_of_earth) + home.lat;
tell_command.alt = -packet.z*1.0e2 + home.alt;
tell_command.lng = 1.0e7f*ToDeg(packet.x/
(radius_of_earth*cosf(ToRad(home.lat/1.0e7f)))) + home.lng;
tell_command.lat = 1.0e7f*ToDeg(packet.y/radius_of_earth) + home.lat;
tell_command.alt = -packet.z*1.0e2f + home.alt;
break;
}
}

22
Tools/ArduTracker/Mavlink_Common.h
View File

@ -120,26 +120,26 @@ void mavlink_send_message(mavlink_channel_t chan, uint8_t id, uint32_t param, ui
{
float gamma = dcm.pitch; // neglecting angle of attack for now
float yaw = dcm.yaw;
mavlink_msg_global_position_send(chan,timeStamp,current_loc.lat/1.0e7,
current_loc.lng/1.0e7,current_loc.alt/1.0e2,gps.ground_speed/1.0e2*cos(gamma)*cos(yaw),
gps.ground_speed/1.0e2*cos(gamma)*sin(yaw),gps.ground_speed/1.0e2*sin(gamma));
mavlink_msg_global_position_send(chan,timeStamp,current_loc.lat/1.0e7f,
current_loc.lng/1.0e7f,current_loc.alt/1.0e2f,gps.ground_speed/1.0e2f*cosf(gamma)*cosf(yaw),
gps.ground_speed/1.0e2f*cosf(gamma)*sinf(yaw),gps.ground_speed/1.0e2f*sinf(gamma));
break;
}
case MSG_LOCAL_LOCATION:
{
float gamma = dcm.pitch; // neglecting angle of attack for now
float yaw = dcm.yaw;
mavlink_msg_local_position_send(chan,timeStamp,ToRad((current_loc.lat-home.lat)/1.0e7)*radius_of_earth,
ToRad((current_loc.lng-home.lng)/1.0e7)*radius_of_earth*cos(ToRad(home.lat/1.0e7)),
(current_loc.alt-home.alt)/1.0e2, gps.ground_speed/1.0e2*cos(gamma)*cos(yaw),
gps.ground_speed/1.0e2*cos(gamma)*sin(yaw),gps.ground_speed/1.0e2*sin(gamma));
mavlink_msg_local_position_send(chan,timeStamp,ToRad((current_loc.lat-home.lat)/1.0e7f)*radius_of_earth,
ToRad((current_loc.lng-home.lng)/1.0e7f)*radius_of_earth*cosf(ToRad(home.lat/1.0e7f)),
(current_loc.alt-home.alt)/1.0e2f, gps.ground_speed/1.0e2f*cosf(gamma)*cosf(yaw),
gps.ground_speed/1.0e2f*cosf(gamma)*sinf(yaw),gps.ground_speed/1.0e2f*sinf(gamma));
break;
}
case MSG_GPS_RAW:
{
mavlink_msg_gps_raw_send(chan,timeStamp,gps.status(),
gps.latitude/1.0e7,gps.longitude/1.0e7,gps.altitude/100.0,
2.0,10.0,gps.ground_speed/100.0,gps.ground_course/100.0);
gps.latitude/1.0e7f,gps.longitude/1.0e7f,gps.altitude/100.0f,
2.0f,10.0f,gps.ground_speed/100.0f,gps.ground_course/100.0f);
break;
}
case MSG_AIRSPEED:
@ -179,8 +179,8 @@ void mavlink_send_message(mavlink_channel_t chan, uint8_t id, uint32_t param, ui
//Serial.printf_P(PSTR("sending accel: %f %f %f\n"), accel.x, accel.y, accel.z);
//Serial.printf_P(PSTR("sending gyro: %f %f %f\n"), gyro.x, gyro.y, gyro.z);
mavlink_msg_raw_imu_send(chan,timeStamp,
accel.x*1000.0/gravity,accel.y*1000.0/gravity,accel.z*1000.0/gravity,
gyro.x*1000.0,gyro.y*1000.0,gyro.z*1000.0,
accel.x*1000.0f/gravity,accel.y*1000.0f/gravity,accel.z*1000.0f/gravity,
gyro.x*1000.0f,gyro.y*1000.0f,gyro.z*1000.0f,
compass.mag_x,compass.mag_y,compass.mag_z);
mavlink_msg_raw_pressure_send(chan,timeStamp,
adc.Ch(AIRSPEED_CH),pitot.RawPress,0);

6
Tools/ArduTracker/commands.pde
View File

@ -178,10 +178,10 @@ void set_next_WP(struct Location *wp)
loiter_sum = 0;
loiter_total = 0;
float rads = (abs(next_WP.lat)/t7) * 0.0174532925;
float rads = (abs(next_WP.lat)/t7) * 0.0174532925f;
//377,173,810 / 10,000,000 = 37.717381 * 0.0174532925 = 0.658292482926943
scaleLongDown = cos(rads);
scaleLongUp = 1.0f/cos(rads);
scaleLongDown = cosf(rads);
scaleLongUp = 1.0f/cosf(rads);
// this is handy for the groundstation
wp_totalDistance = getDistance(&current_loc, &next_WP);

10
Tools/ArduTracker/navigation.pde
View File

@ -91,7 +91,7 @@ void update_navigation()
Disabled for now
void calc_distance_error()
{
//distance_estimate += (float)gps.ground_speed * .0002 * cos(radians(bearing_error * .01));
//distance_estimate += (float)gps.ground_speed * .0002f * cosf(radians(bearing_error * .01f));
//distance_estimate -= DST_EST_GAIN * (float)(distance_estimate - GPS_wp_distance);
//wp_distance = max(distance_estimate,10);
}
@ -134,7 +134,7 @@ void calc_altitude_error()
// special thanks to Ryan Beall for this one
float pitch_angle = pitch_sensor - AOA; // pitch_angle = pitch sensor - angle of attack of your plane at level *100 (50 = .5°)
pitch_angle = constrain(pitch_angle, -2000, 2000);
float scale = sin(radians(pitch_angle * .01));
float scale = sinf(radians(pitch_angle * .01));
altitude_estimate += (float)airspeed * .0002 * scale;
altitude_estimate -= ALT_EST_GAIN * (float)(altitude_estimate - current_loc.alt);
@ -195,7 +195,7 @@ void update_crosstrack(void)
// Crosstrack Error
// ----------------
if (abs(target_bearing - crosstrack_bearing) < 4500) { // If we are too far off or too close we don't do track following
crosstrack_error = sin(radians((target_bearing - crosstrack_bearing)/100)) * wp_distance; // Meters we are off track line
crosstrack_error = sinf(radians((target_bearing - crosstrack_bearing)/100)) * wp_distance; // Meters we are off track line
nav_bearing += constrain(crosstrack_error * get(PARAM_XTRACK_GAIN), -get(PARAM_XTRACK_ANGLE), get(PARAM_XTRACK_ANGLE));
nav_bearing = wrap_360(nav_bearing);
}
@ -223,7 +223,7 @@ long getDistance(struct Location *loc1, struct Location *loc2)
return -1;
float dlat = (float)(loc2->lat - loc1->lat);
float dlong = ((float)(loc2->lng - loc1->lng)) * scaleLongDown;
return sqrt(sq(dlat) + sq(dlong)) * .01113195;
return sqrtf(sq(dlat) + sq(dlong)) * .01113195f;
}
long get_alt_distance(struct Location *loc1, struct Location *loc2)
@ -235,7 +235,7 @@ long get_bearing(struct Location *loc1, struct Location *loc2)
{
long off_x = loc2->lng - loc1->lng;
long off_y = (loc2->lat - loc1->lat) * scaleLongUp;
long bearing = 9000 + atan2(-off_y, off_x) * 5729.57795;
long bearing = 9000 + atan2f(-off_y, off_x) * 5729.57795f;
if (bearing < 0) bearing += 36000;
return bearing;
}

2
Tools/ArduTracker/sensors.pde
View File

@ -28,7 +28,7 @@ void read_airspeed(void)
airpressure_raw = ((float)adc.Ch(AIRSPEED_CH) * .25) + (airpressure_raw * .75);
airpressure = (int)airpressure_raw - airpressure_offset;
airpressure = max(airpressure, 0);
airspeed = sqrt((float)airpressure * get(PARAM_ARSPD_RATIO)) * 100;
airspeed = sqrtf((float)airpressure * get(PARAM_ARSPD_RATIO)) * 100;
#endif
calc_airspeed_errors();

14
Tools/CPUInfo/CPUInfo.pde
View File

@ -100,13 +100,13 @@ static void show_timings(void)
TIMEIT("dmul", v_out_d *= v_d, 100);
TIMEIT("ddiv", v_out_d /= v_d, 100);
TIMEIT("sin()", v_out = sin(v_f), 20);
TIMEIT("cos()", v_out = cos(v_f), 20);
TIMEIT("tan()", v_out = tan(v_f), 20);
TIMEIT("acos()", v_out = acos(v_f * 0.2), 20);
TIMEIT("asin()", v_out = asin(v_f * 0.2), 20);
TIMEIT("atan2()", v_out = atan2(v_f * 0.2, v_f * 0.3), 20);
TIMEIT("sqrt()",v_out = sqrt(v_f), 20);
TIMEIT("sin()", v_out = sinf(v_f), 20);
TIMEIT("cos()", v_out = cosf(v_f), 20);
TIMEIT("tan()", v_out = tanf(v_f), 20);
TIMEIT("acos()", v_out = acosf(v_f * 0.2), 20);
TIMEIT("asin()", v_out = asinf(v_f * 0.2), 20);
TIMEIT("atan2()", v_out = atan2f(v_f * 0.2, v_f * 0.3), 20);
TIMEIT("sqrt()",v_out = sqrtf(v_f), 20);
TIMEIT("iadd8", v_out_8 += v_8, 100);
TIMEIT("isub8", v_out_8 -= v_8, 100);

10
libraries/APM_Control/AP_PitchController.cpp
View File

@ -37,7 +37,7 @@ int32_t AP_PitchController::get_servo_out(int32_t angle, float scaler, bool stab
_last_t = tnow;
if(_ahrs == NULL) return 0;
float delta_time = (float)dt / 1000.0;
float delta_time = (float)dt / 1000.0f;
int8_t inv = 1;
if(abs(_ahrs->roll_sensor)>9000) inv = -1;
@ -47,12 +47,12 @@ int32_t AP_PitchController::get_servo_out(int32_t angle, float scaler, bool stab
float rate = _ahrs->get_pitch_rate_earth();
float RC = 1/(2*M_PI*_fCut);
float RC = 1/(2*PI*_fCut);
rate = _last_rate +
(delta_time / (RC + delta_time)) * (rate - _last_rate);
_last_rate = rate;
float roll_scaler = 1/constrain(cos(_ahrs->roll),.33,1);
float roll_scaler = 1/constrain(cosf(_ahrs->roll),0.33f,1);
int32_t desired_rate = angle_err * _kp_angle;
@ -70,7 +70,7 @@ int32_t AP_PitchController::get_servo_out(int32_t angle, float scaler, bool stab
int32_t rate_error = desired_rate - ToDeg(rate)*100;
float roll_ff = _roll_ff * 1000 * (roll_scaler-1.0);
float roll_ff = _roll_ff * 1000 * (roll_scaler-1.0f);
if(roll_ff > 4500)
roll_ff = 4500;
else if(roll_ff < 0)
@ -80,7 +80,7 @@ int32_t AP_PitchController::get_servo_out(int32_t angle, float scaler, bool stab
//rate integrator
if (!stabilize) {
if ((fabs(_ki_rate) > 0) && (dt > 0))
if ((fabsf(_ki_rate) > 0) && (dt > 0))
{
_integrator += (rate_error * _ki_rate) * scaler * delta_time;
if (_integrator < -4500-out) _integrator = -4500-out;

6
libraries/APM_Control/AP_RollController.cpp
View File

@ -34,13 +34,13 @@ int32_t AP_RollController::get_servo_out(int32_t angle, float scaler, bool stabi
_last_t = tnow;
if(_ahrs == NULL) return 0; // can't control without a reference
float delta_time = (float)dt / 1000.0;
float delta_time = (float)dt / 1000.0f;
int32_t angle_err = angle - _ahrs->roll_sensor;
float rate = _ahrs->get_roll_rate_earth();
float RC = 1/(2*M_PI*_fCut);
float RC = 1/(2*PI*_fCut);
rate = _last_rate +
(delta_time / (RC + delta_time)) * (rate - _last_rate);
_last_rate = rate;
@ -60,7 +60,7 @@ int32_t AP_RollController::get_servo_out(int32_t angle, float scaler, bool stabi
//rate integrator
if (!stabilize) {
if ((fabs(_ki_rate) > 0) && (dt > 0))
if ((fabsf(_ki_rate) > 0) && (dt > 0))
{
_integrator += (rate_error * _ki_rate) * scaler * delta_time;
if (_integrator < -4500-out) _integrator = -4500-out;

12
libraries/APM_Control/AP_YawController.cpp
View File

@ -22,8 +22,8 @@ const AP_Param::GroupInfo AP_YawController::var_info[] PROGMEM = {
// Low pass filter cut frequency for derivative calculation.
// FCUT macro computes a frequency cut based on an acceptable delay.
#define FCUT(d) (1 / ( 2 * 3.14 * (d) ) )
const float AP_YawController::_fCut = FCUT(.5);
#define FCUT(d) (1 / ( 2 * 3.14f * (d) ) )
const float AP_YawController::_fCut = FCUT(0.5f);
int32_t AP_YawController::get_servo_out(float scaler, bool stick_movement)
{
@ -38,7 +38,7 @@ int32_t AP_YawController::get_servo_out(float scaler, bool stick_movement)
return 0;
}
float delta_time = (float) dt / 1000.0;
float delta_time = (float) dt / 1000.0f;
if(stick_movement) {
if(!_stick_movement) {
@ -54,20 +54,20 @@ int32_t AP_YawController::get_servo_out(float scaler, bool stick_movement)
Vector3f accels = _ins->get_accel();
// I didn't pull 512 out of a hat - it is a (very) loose approximation of
// 100*ToDeg(asin(-accels.y/9.81))
// 100*ToDeg(asinf(-accels.y/9.81f))
// which, with a P of 1.0, would mean that your rudder angle would be
// equal to your roll angle when
// the plane is still. Thus we have an (approximate) unit to go by.
float error = 512 * -accels.y;
// strongly filter the error
float RC = 1/(2*M_PI*_fCut);
float RC = 1/(2*PI*_fCut);
error = _last_error +
(delta_time / (RC + delta_time)) * (error - _last_error);
_last_error = error;
// integrator
if(_freeze_start_time < (tnow - 2000)) {
if ((fabs(_ki) > 0) && (dt > 0)) {
if ((fabsf(_ki) > 0) && (dt > 0)) {
_integrator += (error * _ki) * scaler * delta_time;
if (_integrator < -_imax) _integrator = -_imax;
else if (_integrator > _imax) _integrator = _imax;

2
libraries/AP_ADC/examples/AP_ADC_test/AP_ADC_test.pde
View File

@ -82,7 +82,7 @@ static void show_data()
for (i=0; i<6; i++) {
if (result[i] < min[i]) min[i] = result[i];
if (result[i] > max[i]) max[i] = result[i];
if (fabs(result[i]) > 0x8000) {
if (fabsf(result[i]) > 0x8000) {
hal.console->printf("result[%u]=%f\n", (unsigned)i, result[i]);
}
}

20
libraries/AP_AHRS/AP_AHRS.cpp
View File

@ -19,7 +19,7 @@ const AP_Param::GroupInfo AP_AHRS::var_info[] PROGMEM = {
// @Description: This controls how how much to use the GPS to correct the attitude. This should never be set to zero for a plane as it would result in the plane losing control in turns. For a plane please use the default value of 1.0.
// @Range: 0.0 1.0
// @Increment: .01
AP_GROUPINFO("GPS_GAIN", 2, AP_AHRS, gps_gain, 1.0),
AP_GROUPINFO("GPS_GAIN", 2, AP_AHRS, gps_gain, 1.0f),
// @Param: GPS_USE
// @DisplayName: AHRS use GPS for navigation
@ -32,14 +32,14 @@ const AP_Param::GroupInfo AP_AHRS::var_info[] PROGMEM = {
// @Description: This controls the weight the compass or GPS has on the heading. A higher value means the heading will track the yaw source (GPS or compass) more rapidly.
// @Range: 0.1 0.4
// @Increment: .01
AP_GROUPINFO("YAW_P", 4, AP_AHRS, _kp_yaw, 0.4),
AP_GROUPINFO("YAW_P", 4, AP_AHRS, _kp_yaw, 0.4f),
// @Param: RP_P
// @DisplayName: AHRS RP_P
// @Description: This controls how fast the accelerometers correct the attitude
// @Range: 0.1 0.4
// @Increment: .01
AP_GROUPINFO("RP_P", 5, AP_AHRS, _kp, 0.4),
AP_GROUPINFO("RP_P", 5, AP_AHRS, _kp, 0.4f),
// @Param: WIND_MAX
// @DisplayName: Maximum wind
@ -47,7 +47,7 @@ const AP_Param::GroupInfo AP_AHRS::var_info[] PROGMEM = {
// @Range: 0 127
// @Units: m/s
// @Increment: 1
AP_GROUPINFO("WIND_MAX", 6, AP_AHRS, _wind_max, 0.0),
AP_GROUPINFO("WIND_MAX", 6, AP_AHRS, _wind_max, 0.0f),
// @Param: BARO_USE
// @DisplayName: AHRS Use Barometer
@ -89,13 +89,13 @@ const AP_Param::GroupInfo AP_AHRS::var_info[] PROGMEM = {
float AP_AHRS::get_pitch_rate_earth(void)
{
Vector3f omega = get_gyro();
return cos(roll) * omega.y - sin(roll) * omega.z;
return cosf(roll) * omega.y - sinf(roll) * omega.z;
}
// get roll rate in earth frame, in radians/s
float AP_AHRS::get_roll_rate_earth(void) {
Vector3f omega = get_gyro();
return omega.x + tan(pitch)*(omega.y*sin(roll) + omega.z*cos(roll));
return omega.x + tanf(pitch)*(omega.y*sinf(roll) + omega.z*cosf(roll));
}
// return airspeed estimate if available
@ -107,8 +107,8 @@ bool AP_AHRS::airspeed_estimate(float *airspeed_ret)
// constrain the airspeed by the ground speed
// and AHRS_WIND_MAX
*airspeed_ret = constrain(*airspeed_ret,
_gps->ground_speed*0.01 - _wind_max,
_gps->ground_speed*0.01 + _wind_max);
_gps->ground_speed*0.01f - _wind_max,
_gps->ground_speed*0.01f + _wind_max);
}
return true;
}
@ -121,8 +121,8 @@ void AP_AHRS::add_trim(float roll_in_radians, float pitch_in_radians, bool save_
Vector3f trim = _trim.get();
// add new trim
trim.x = constrain(trim.x + roll_in_radians, ToRad(-10.0), ToRad(10.0));
trim.y = constrain(trim.y + pitch_in_radians, ToRad(-10.0), ToRad(10.0));
trim.x = constrain(trim.x + roll_in_radians, ToRad(-10.0f), ToRad(10.0f));
trim.y = constrain(trim.y + pitch_in_radians, ToRad(-10.0f), ToRad(10.0f));
// set new trim values
_trim.set(trim);

70
libraries/AP_AHRS/AP_AHRS_DCM.cpp
View File

@ -48,7 +48,7 @@ AP_AHRS_DCM::update(void)
// if the update call took more than 0.2 seconds then discard it,
// otherwise we may move too far. This happens when arming motors
// in ArduCopter
if (delta_t > 0.2) {
if (delta_t > 0.2f) {
_ra_sum.zero();
_ra_deltat = 0;
return;
@ -129,14 +129,14 @@ AP_AHRS_DCM::check_matrix(void)
// the pitch calculation via asin(). These NaN values can
// feed back into the rest of the DCM matrix via the
// error_course value.
if (!(_dcm_matrix.c.x < 1.0 &&
_dcm_matrix.c.x > -1.0)) {
if (!(_dcm_matrix.c.x < 1.0f &&
_dcm_matrix.c.x > -1.0f)) {
// We have an invalid matrix. Force a normalisation.
renorm_range_count++;
normalize();
if (_dcm_matrix.is_nan() ||
fabs(_dcm_matrix.c.x) > 10) {
fabsf(_dcm_matrix.c.x) > 10) {
// normalisation didn't fix the problem! We're
// in real trouble. All we can do is reset
//Serial.printf("ERROR: DCM matrix error. _dcm_matrix.c.x=%f\n",
@ -172,16 +172,16 @@ AP_AHRS_DCM::renorm(Vector3f const &a, Vector3f &result)
// we don't want to compound the error by making DCM less
// accurate.
renorm_val = 1.0 / a.length();
renorm_val = 1.0f / a.length();
// keep the average for reporting
_renorm_val_sum += renorm_val;
_renorm_val_count++;
if (!(renorm_val < 2.0 && renorm_val > 0.5)) {
if (!(renorm_val < 2.0f && renorm_val > 0.5f)) {
// this is larger than it should get - log it as a warning
renorm_range_count++;
if (!(renorm_val < 1.0e6 && renorm_val > 1.0e-6)) {
if (!(renorm_val < 1.0e6f && renorm_val > 1.0e-6f)) {
// we are getting values which are way out of
// range, we will reset the matrix and hope we
// can recover our attitude using drift
@ -245,8 +245,8 @@ AP_AHRS_DCM::yaw_error_compass(void)
}
// get the earths magnetic field (only X and Y components needed)
Vector3f mag_earth = Vector3f(cos(_compass->get_declination()),
sin(_compass->get_declination()), 0);
Vector3f mag_earth = Vector3f(cosf(_compass->get_declination()),
sinf(_compass->get_declination()), 0);
// calculate the error term in earth frame
Vector3f error = rb % mag_earth;
@ -259,7 +259,7 @@ AP_AHRS_DCM::yaw_error_compass(void)
float
AP_AHRS_DCM::yaw_error_gps(void)
{
return sin(ToRad(_gps->ground_course * 0.01) - yaw);
return sinf(ToRad(_gps->ground_course * 0.01f) - yaw);
}
@ -270,10 +270,10 @@ float
AP_AHRS_DCM::_P_gain(float spin_rate)
{
if (spin_rate < ToDeg(50)) {
return 1.0;
return 1.0f;
}
if (spin_rate > ToDeg(500)) {
return 10.0;
return 10.0f;
}
return spin_rate/ToDeg(50);
}
@ -299,7 +299,7 @@ AP_AHRS_DCM::drift_correction_yaw(void)
if (_compass && _compass->use_for_yaw()) {
if (_compass->last_update != _compass_last_update) {
yaw_deltat = (_compass->last_update - _compass_last_update) * 1.0e-6;
yaw_deltat = (_compass->last_update - _compass_last_update) * 1.0e-6f;
_compass_last_update = _compass->last_update;
// we force an additional compass read()
// here. This has the effect of throwing away
@ -316,10 +316,10 @@ AP_AHRS_DCM::drift_correction_yaw(void)
} else if (_fly_forward && have_gps()) {
if (_gps->last_fix_time != _gps_last_update &&
_gps->ground_speed >= GPS_SPEED_MIN) {
yaw_deltat = (_gps->last_fix_time - _gps_last_update) * 1.0e-3;
yaw_deltat = (_gps->last_fix_time - _gps_last_update) * 1.0e-3f;
_gps_last_update = _gps->last_fix_time;
if (!_have_initial_yaw) {
_dcm_matrix.from_euler(roll, pitch, ToRad(_gps->ground_course*0.01));
_dcm_matrix.from_euler(roll, pitch, ToRad(_gps->ground_course*0.01f));
_omega_yaw_P.zero();
_have_initial_yaw = true;
}
@ -332,7 +332,7 @@ AP_AHRS_DCM::drift_correction_yaw(void)
// we don't have any new yaw information
// slowly decay _omega_yaw_P to cope with loss
// of our yaw source
_omega_yaw_P *= 0.97;
_omega_yaw_P *= 0.97f;
return;
}
@ -358,12 +358,12 @@ AP_AHRS_DCM::drift_correction_yaw(void)
// don't update the drift term if we lost the yaw reference
// for more than 2 seconds
if (yaw_deltat < 2.0 && spin_rate < ToRad(SPIN_RATE_LIMIT)) {
if (yaw_deltat < 2.0f && spin_rate < ToRad(SPIN_RATE_LIMIT)) {
// also add to the I term
_omega_I_sum.z += error.z * _ki_yaw * yaw_deltat;
}
_error_yaw_sum += fabs(yaw_error);
_error_yaw_sum += fabsf(yaw_error);
_error_yaw_count++;
}
@ -411,7 +411,7 @@ AP_AHRS_DCM::drift_correction(float deltat)
// As a fallback we use the fixed wing acceleration correction
// if we have an airspeed estimate (which we only have if
// _fly_forward is set), otherwise no correction
if (_ra_deltat < 0.2) {
if (_ra_deltat < 0.2f) {
// not enough time has accumulated
return;
}
@ -489,8 +489,8 @@ AP_AHRS_DCM::drift_correction(float deltat)
Vector3f vdelta = (velocity - _last_velocity) * v_scale;
// limit vertical acceleration correction to 0.5 gravities. The
// barometer sometimes gives crazy acceleration changes.
vdelta.z = constrain(vdelta.z, -0.5, 0.5);
GA_e = Vector3f(0, 0, -1.0) + vdelta;
vdelta.z = constrain(vdelta.z, -0.5f, 0.5f);
GA_e = Vector3f(0, 0, -1.0f) + vdelta;
GA_e.normalize();
if (GA_e.is_inf()) {
// wait for some non-zero acceleration information
@ -500,7 +500,7 @@ AP_AHRS_DCM::drift_correction(float deltat)
// calculate the error term in earth frame.
Vector3f GA_b = _ra_sum / (_ra_deltat * GRAVITY_MSS);
float length = GA_b.length();
if (length > 1.0) {
if (length > 1.0f) {
GA_b /= length;
if (GA_b.is_inf()) {
// wait for some non-zero acceleration information
@ -518,10 +518,10 @@ AP_AHRS_DCM::drift_correction(float deltat)
float tilt = pythagorous2(GA_e.x, GA_e.y);
// equation 11
float theta = atan2(GA_b.y, GA_b.x);
float theta = atan2f(GA_b.y, GA_b.x);
// equation 12
Vector3f GA_e2 = Vector3f(cos(theta)*tilt, sin(theta)*tilt, GA_e.z);
Vector3f GA_e2 = Vector3f(cosf(theta)*tilt, sinf(theta)*tilt, GA_e.z);
// step 6
error = GA_b % GA_e2;
@ -533,8 +533,8 @@ AP_AHRS_DCM::drift_correction(float deltat)
// flat, but still allow for yaw correction using the
// accelerometers at high roll angles as long as we have a GPS
if (_compass && _compass->use_for_yaw()) {
if (have_gps() && gps_gain == 1.0) {
error.z *= sin(fabs(roll));
if (have_gps() && gps_gain == 1.0f) {
error.z *= sinf(fabsf(roll));
} else {
error.z = 0;
}
@ -617,7 +617,7 @@ void AP_AHRS_DCM::estimate_wind(Vector3f &velocity)
}
float diff_length = fuselageDirectionDiff.length();
if (diff_length > 0.2) {
if (diff_length > 0.2f) {
// when turning, use the attitude response to estimate
// wind speed
float V;
@ -632,18 +632,18 @@ void AP_AHRS_DCM::estimate_wind(Vector3f &velocity)
Vector3f fuselageDirectionSum = fuselageDirection + _last_fuse;
Vector3f velocitySum = velocity + _last_vel;
float theta = atan2(velocityDiff.y, velocityDiff.x) - atan2(fuselageDirectionDiff.y, fuselageDirectionDiff.x);
float sintheta = sin(theta);
float costheta = cos(theta);
float theta = atan2f(velocityDiff.y, velocityDiff.x) - atan2f(fuselageDirectionDiff.y, fuselageDirectionDiff.x);
float sintheta = sinf(theta);
float costheta = cosf(theta);
Vector3f wind = Vector3f();
wind.x = velocitySum.x - V * (costheta * fuselageDirectionSum.x - sintheta * fuselageDirectionSum.y);
wind.y = velocitySum.y - V * (sintheta * fuselageDirectionSum.x + costheta * fuselageDirectionSum.y);
wind.z = velocitySum.z - V * fuselageDirectionSum.z;
wind *= 0.5;
wind *= 0.5f;
if (wind.length() < _wind.length() + 20) {
_wind = _wind * 0.95 + wind * 0.05;
_wind = _wind * 0.95f + wind * 0.05f;
}
_last_wind_time = now;
@ -651,7 +651,7 @@ void AP_AHRS_DCM::estimate_wind(Vector3f &velocity)
// when flying straight use airspeed to get wind estimate if available
Vector3f airspeed = _dcm_matrix.colx() * _airspeed->get_airspeed();
Vector3f wind = velocity - airspeed;
_wind = _wind * 0.92 + wind * 0.08;
_wind = _wind * 0.92f + wind * 0.08f;
}
}
@ -734,8 +734,8 @@ bool AP_AHRS_DCM::airspeed_estimate(float *airspeed_ret)
// constrain the airspeed by the ground speed
// and AHRS_WIND_MAX
*airspeed_ret = constrain(*airspeed_ret,
_gps->ground_speed*0.01 - _wind_max,
_gps->ground_speed*0.01 + _wind_max);
_gps->ground_speed*0.01f - _wind_max,
_gps->ground_speed*0.01f + _wind_max);
}
return ret;
}

22
libraries/AP_AHRS/AP_AHRS_MPU6000.cpp
View File

@ -79,11 +79,11 @@ AP_AHRS_MPU6000::update(void)
// TO-DO: should remove and replace with more standard functions
float AP_AHRS_MPU6000::wrap_PI(float angle_in_radians)
{
if( angle_in_radians > M_PI ) {
return(angle_in_radians - 2*M_PI);
if( angle_in_radians > PI ) {
return(angle_in_radians - 2*PI);
}
else if( angle_in_radians < -M_PI ) {
return(angle_in_radians + 2*M_PI);
else if( angle_in_radians < -PI ) {
return(angle_in_radians + 2*PI);
}
else{
return(angle_in_radians);
@ -141,13 +141,13 @@ void AP_AHRS_MPU6000::drift_correction( float deltat )
// TO-DO: fix this. Currently it makes the roll and pitch drift more!
// If bias values are greater than 1 LSB we update the hardware offset
// registers
if( fabs(_gyro_bias[0])>1.0 ) {
if( fabsf(_gyro_bias[0])>1.0f ) {
//_mpu6000->set_gyro_offsets(-1*(int)_gyro_bias[0],0,0);
//_mpu6000->set_gyro_offsets(0,-1*(int)_gyro_bias[0],0);
//_gyro_bias[0] -= (int)_gyro_bias[0]; // we remove the part that
// we have already corrected on registers...
}
if (fabs(_gyro_bias[1])>1.0) {
if (fabsf(_gyro_bias[1])>1.0f) {
//_mpu6000->set_gyro_offsets(-1*(int)_gyro_bias[1],0,0);
//_gyro_bias[1] -= (int)_gyro_bias[1];
}
@ -199,9 +199,9 @@ void
AP_AHRS_MPU6000::push_gains_to_dmp()
{
uint8_t gain;
if( _kp.get() >= 1.0 ) {
if( _kp.get() >= 1.0f ) {
gain = 0xFF;
}else if( _kp.get() <= 0.0 ) {
}else if( _kp.get() <= 0.0f ) {
gain = 0x00;
}else{
gain = (uint8_t)((float)0xFF * _kp.get());
@ -226,8 +226,8 @@ AP_AHRS_MPU6000::yaw_error_compass(void)
}
// get the earths magnetic field (only X and Y components needed)
Vector3f mag_earth = Vector3f(cos(_compass->get_declination()),
sin(_compass->get_declination()), 0);
Vector3f mag_earth = Vector3f(cosf(_compass->get_declination()),
sinf(_compass->get_declination()), 0);
// calculate the error term in earth frame
Vector3f error = rb % mag_earth;
@ -290,7 +290,7 @@ AP_AHRS_MPU6000::drift_correction_yaw(void)
yaw_error = wrap_PI(heading - yaw_corrected);
// shift the corrected yaw towards the compass heading a bit
yaw_corrected += wrap_PI(yaw_error * _kp_yaw.get() * 0.1);
yaw_corrected += wrap_PI(yaw_error * _kp_yaw.get() * 0.1f);
// rebuild the dcm matrix yet again
_dcm_matrix.from_euler(dmp_roll, dmp_pitch, yaw_corrected);

6
libraries/AP_Airspeed/AP_Airspeed.cpp
View File

@ -40,7 +40,7 @@ const AP_Param::GroupInfo AP_Airspeed::var_info[] PROGMEM = {
// @DisplayName: Airspeed ratio
// @Description: Airspeed calibration ratio
// @Increment: 0.1
AP_GROUPINFO("RATIO", 3, AP_Airspeed, _ratio, 1.9936),
AP_GROUPINFO("RATIO", 3, AP_Airspeed, _ratio, 1.9936f),
AP_GROUPEND
};
@ -73,6 +73,6 @@ void AP_Airspeed::read(void)
}
_airspeed_raw = _source->read_average();
airspeed_pressure = max(_airspeed_raw - _offset, 0);
_airspeed = 0.7 * _airspeed +
0.3 * sqrt(airspeed_pressure * _ratio);
_airspeed = 0.7f * _airspeed +
0.3f * sqrtf(airspeed_pressure * _ratio);
}

10
libraries/AP_Baro/AP_Baro.cpp
View File

@ -83,9 +83,9 @@ void AP_Baro::calibrate()
"for more than 500ms in AP_Baro::calibrate [3]\r\n"));
}
} while (!healthy);
ground_pressure = (ground_pressure * 0.8) + (get_pressure() * 0.2);
ground_temperature = (ground_temperature * 0.8) +
(get_temperature() * 0.2);
ground_pressure = (ground_pressure * 0.8f) + (get_pressure() * 0.2f);
ground_temperature = (ground_temperature * 0.8f) +
(get_temperature() * 0.2f);
hal.scheduler->delay(100);
}
@ -111,7 +111,7 @@ float AP_Baro::get_altitude(void)
// unsmoothed values
scaling = (float)_ground_pressure / (float)get_pressure();
temp = ((float)_ground_temperature) + 273.15f;
_altitude = log(scaling) * temp * 29.271267f;
_altitude = logf(scaling) * temp * 29.271267f;
_last_altitude_t = _last_update;
@ -128,6 +128,6 @@ float AP_Baro::get_climb_rate(void)
{
// we use a 7 point derivative filter on the climb rate. This seems
// to produce somewhat reasonable results on real hardware
return _climb_rate_filter.slope() * 1.0e3;
return _climb_rate_filter.slope() * 1.0e3f;
}

8
libraries/AP_Baro/AP_Baro_MS5611.cpp
View File

@ -379,15 +379,15 @@ void AP_Baro_MS5611::_calculate()
// multiple samples, giving us more precision
dT = D2-(((uint32_t)C5)<<8);
TEMP = (dT * C6)/8388608;
OFF = C2 * 65536.0 + (C4 * dT) / 128;
SENS = C1 * 32768.0 + (C3 * dT) / 256;
OFF = C2 * 65536.0f + (C4 * dT) / 128;
SENS = C1 * 32768.0f + (C3 * dT) / 256;
if (TEMP < 0) {
// second order temperature compensation when under 20 degrees C
float T2 = (dT*dT) / 0x80000000;
float Aux = TEMP*TEMP;
float OFF2 = 2.5*Aux;
float SENS2 = 1.25*Aux;
float OFF2 = 2.5f*Aux;
float SENS2 = 1.25f*Aux;
TEMP = TEMP - T2;
OFF = OFF - OFF2;
SENS = SENS - SENS2;

12
libraries/AP_Compass/AP_Compass_HMC5843.cpp
View File

@ -221,13 +221,13 @@ AP_Compass_HMC5843::init()
float cal[3];
cal[0] = fabs(expected_x / (float)_mag_x);
cal[1] = fabs(expected_yz / (float)_mag_y);
cal[2] = fabs(expected_yz / (float)_mag_z);
cal[0] = fabsf(expected_x / (float)_mag_x);
cal[1] = fabsf(expected_yz / (float)_mag_y);
cal[2] = fabsf(expected_yz / (float)_mag_z);
if (cal[0] > 0.7 && cal[0] < 1.3 &&
cal[1] > 0.7 && cal[1] < 1.3 &&
cal[2] > 0.7 && cal[2] < 1.3) {
if (cal[0] > 0.7f && cal[0] < 1.3f &&
cal[1] > 0.7f && cal[1] < 1.3f &&
cal[2] > 0.7f && cal[2] < 1.3f) {
good_count++;
calibration[0] += cal[0];
calibration[1] += cal[1];

44
libraries/AP_Compass/Compass.cpp
View File

@ -144,26 +144,26 @@ Compass::calculate_heading(float roll, float pitch)
float sin_pitch;
float heading;
cos_roll = cos(roll);
sin_roll = sin(roll);
cos_pitch = cos(pitch);
sin_pitch = sin(pitch);
cos_roll = cosf(roll);
sin_roll = sinf(roll);
cos_pitch = cosf(pitch);
sin_pitch = sinf(pitch);
// Tilt compensated magnetic field X component:
headX = mag_x*cos_pitch + mag_y*sin_roll*sin_pitch + mag_z*cos_roll*sin_pitch;
// Tilt compensated magnetic field Y component:
headY = mag_y*cos_roll - mag_z*sin_roll;
// magnetic heading
heading = atan2(-headY,headX);
heading = atan2f(-headY,headX);
// Declination correction (if supplied)
if( fabs(_declination) > 0.0 )
if( fabsf(_declination) > 0.0f )
{
heading = heading + _declination;
if (heading > M_PI) // Angle normalization (-180 deg, 180 deg)
heading -= (2.0 * M_PI);
else if (heading < -M_PI)
heading += (2.0 * M_PI);
if (heading > PI) // Angle normalization (-180 deg, 180 deg)
heading -= (2.0f * PI);
else if (heading < -PI)
heading += (2.0f * PI);
}
return heading;
@ -178,11 +178,11 @@ Compass::calculate_heading(const Matrix3f &dcm_matrix)
float cos_pitch = safe_sqrt(1-(dcm_matrix.c.x*dcm_matrix.c.x));
float heading;
// sin(pitch) = - dcm_matrix(3,1)
// cos(pitch)*sin(roll) = - dcm_matrix(3,2)
// cos(pitch)*cos(roll) = - dcm_matrix(3,3)
// sinf(pitch) = - dcm_matrix(3,1)
// cosf(pitch)*sinf(roll) = - dcm_matrix(3,2)
// cosf(pitch)*cosf(roll) = - dcm_matrix(3,3)
if (cos_pitch == 0.0) {
if (cos_pitch == 0.0f) {
// we are pointing straight up or down so don't update our
// heading using the compass. Wait for the next iteration when
// we hopefully will have valid values again.
@ -195,16 +195,16 @@ Compass::calculate_heading(const Matrix3f &dcm_matrix)
headY = mag_y*dcm_matrix.c.z/cos_pitch - mag_z*dcm_matrix.c.y/cos_pitch;
// magnetic heading
// 6/4/11 - added constrain to keep bad values from ruining DCM Yaw - Jason S.
heading = constrain(atan2(-headY,headX), -3.15, 3.15);
heading = constrain(atan2f(-headY,headX), -3.15f, 3.15f);
// Declination correction (if supplied)
if( fabs(_declination) > 0.0 )
if( fabsf(_declination) > 0.0f )
{
heading = heading + _declination;
if (heading > M_PI) // Angle normalization (-180 deg, 180 deg)
heading -= (2.0 * M_PI);
else if (heading < -M_PI)
heading += (2.0 * M_PI);
if (heading > PI) // Angle normalization (-180 deg, 180 deg)
heading -= (2.0f * PI);
else if (heading < -PI)
heading += (2.0f * PI);
}
return heading;
@ -254,7 +254,7 @@ Compass::null_offsets(void)
for (uint8_t i=0; i<_mag_history_size; i++) {
// fill the history buffer with the current mag vector,
// with the offset removed
_mag_history[i] = Vector3i((mag_x+0.5) - ofs.x, (mag_y+0.5) - ofs.y, (mag_z+0.5) - ofs.z);
_mag_history[i] = Vector3i((mag_x+0.5f) - ofs.x, (mag_y+0.5f) - ofs.y, (mag_z+0.5f) - ofs.z);
}
_mag_history_index = 0;
return;
@ -289,7 +289,7 @@ Compass::null_offsets(void)
}
// put the vector in the history
_mag_history[_mag_history_index] = Vector3i((mag_x+0.5) - ofs.x, (mag_y+0.5) - ofs.y, (mag_z+0.5) - ofs.z);
_mag_history[_mag_history_index] = Vector3i((mag_x+0.5f) - ofs.x, (mag_y+0.5f) - ofs.y, (mag_z+0.5f) - ofs.z);
_mag_history_index = (_mag_history_index + 1) % _mag_history_size;
// equation 6 of Bills paper

4
libraries/AP_Declination/AP_Declination.cpp
View File

@ -118,8 +118,8 @@ AP_Declination::get_declination(float lat, float lon)
lat = constrain(lat, -90, 90);
lon = constrain(lon, -180, 180);
latmin = floor(lat/5)*5;
lonmin = floor(lon/5)*5;
latmin = floorf(lat/5)*5;
lonmin = floorf(lon/5)*5;
latmin_index= (90+latmin)/5;
lonmin_index= (180+lonmin)/5;

12
libraries/AP_GPS/AP_GPS_HIL.cpp
View File

@ -34,12 +34,12 @@ void AP_GPS_HIL::setHIL(uint32_t _time, float _latitude, float _longitude, float
float _ground_speed, float _ground_course, float _speed_3d, uint8_t _num_sats)
{
time = _time;
latitude = _latitude*1.0e7;
longitude = _longitude*1.0e7;
altitude = _altitude*1.0e2;
ground_speed = _ground_speed*1.0e2;
ground_course = _ground_course*1.0e2;
speed_3d = _speed_3d*1.0e2;
latitude = _latitude*1.0e7f;
longitude = _longitude*1.0e7f;
altitude = _altitude*1.0e2f;
ground_speed = _ground_speed*1.0e2f;
ground_course = _ground_course*1.0e2f;
speed_3d = _speed_3d*1.0e2f;
num_sats = _num_sats;
fix = true;
new_data = true;

14
libraries/AP_GPS/GPS.cpp
View File

@ -54,16 +54,16 @@ GPS::update(void)
if (_have_raw_velocity) {
// the GPS is able to give us velocity numbers directly
_velocity_north = _vel_north * 0.01;
_velocity_east = _vel_east * 0.01;
_velocity_down = _vel_down * 0.01;
_velocity_north = _vel_north * 0.01f;
_velocity_east = _vel_east * 0.01f;
_velocity_down = _vel_down * 0.01f;
} else {
float gps_heading = ToRad(ground_course * 0.01);
float gps_speed = ground_speed * 0.01;
float gps_heading = ToRad(ground_course * 0.01f);
float gps_speed = ground_speed * 0.01f;
float sin_heading, cos_heading;
cos_heading = cos(gps_heading);
sin_heading = sin(gps_heading);
cos_heading = cosf(gps_heading);
sin_heading = sinf(gps_heading);
_velocity_north = gps_speed * cos_heading;
_velocity_east = gps_speed * sin_heading;

6
libraries/AP_HAL/utility/Print.cpp
View File

@ -197,7 +197,7 @@ size_t Print::printFloat(float number, uint8_t digits)
size_t n = 0;
// Handle negative numbers
if (number < 0.0)
if (number < 0.0f)
{
n += print('-');
number = -number;
@ -206,7 +206,7 @@ size_t Print::printFloat(float number, uint8_t digits)
// Round correctly so that print(1.999, 2) prints as "2.00"
float rounding = 0.5;
for (uint8_t i=0; i<digits; ++i)
rounding /= 10.0;
rounding /= 10.0f;
number += rounding;
@ -223,7 +223,7 @@ size_t Print::printFloat(float number, uint8_t digits)
// Extract digits from the remainder one at a time
while (digits-- > 0)
{
remainder *= 10.0;
remainder *= 10.0f;
int toPrint = int(remainder);
n += print(toPrint);
remainder -= toPrint;

2
libraries/AP_HAL_AVR_SITL/sitl_gps.cpp
View File

@ -226,7 +226,7 @@ void SITL_State::_update_gps(double latitude, double longitude, float altitude,
velned.ned_down = 0;
velned.speed_2d = pythagorous2(d.speedN, d.speedE) * 100;
velned.speed_3d = velned.speed_2d;
velned.heading_2d = ToDeg(atan2(d.speedE, d.speedN)) * 100000.0;
velned.heading_2d = ToDeg(atan2f(d.speedE, d.speedN)) * 100000.0;
if (velned.heading_2d < 0.0) {
velned.heading_2d += 360.0 * 100000.0;
}

12
libraries/AP_InertialNav/AP_InertialNav.cpp
View File

@ -64,7 +64,7 @@ void AP_InertialNav::update(float dt)
Vector3f velocity_increase;
// discard samples where dt is too large
if( dt > 0.1 ) {
if( dt > 0.1f ) {
return;
}
@ -149,7 +149,7 @@ void AP_InertialNav::check_gps()
// calculate time since last gps reading
now = hal.scheduler->millis();
float dt = (float)(now - _gps_last_update) / 1000.0;
float dt = (float)(now - _gps_last_update) / 1000.0f;
// call position correction method
correct_with_gps((*_gps_ptr)->longitude, (*_gps_ptr)->latitude, dt);
@ -167,7 +167,7 @@ void AP_InertialNav::correct_with_gps(int32_t lon, int32_t lat, float dt)
float hist_position_base_x, hist_position_base_y;
// discard samples where dt is too large
if( dt > 1.0 || dt == 0 || !_xy_enabled) {
if( dt > 1.0f || dt == 0 || !_xy_enabled) {
return;
}
@ -240,7 +240,7 @@ void AP_InertialNav::set_current_position(int32_t lon, int32_t lat)
// set longitude->meters scaling
// this is used to offset the shrinking longitude as we go towards the poles
_lon_to_m_scaling = cos((fabs((float)lat)/10000000.0) * 0.0174532925);
_lon_to_m_scaling = cosf((fabsf((float)lat)/10000000.0f) * 0.0174532925f);
// reset corrections to base position to zero
_position_base.x = 0;
@ -332,7 +332,7 @@ void AP_InertialNav::check_baro()
// calculate time since last baro reading
baro_update_time = _baro->get_last_update();
if( baro_update_time != _baro_last_update ) {
float dt = (float)(baro_update_time - _baro_last_update) / 1000.0;
float dt = (float)(baro_update_time - _baro_last_update) / 1000.0f;
// call correction method
correct_with_baro(_baro->get_altitude()*100, dt);
_baro_last_update = baro_update_time;
@ -348,7 +348,7 @@ void AP_InertialNav::correct_with_baro(float baro_alt, float dt)
float accel_ef_z_correction;
// discard samples where dt is too large
if( dt > 0.5 ) {
if( dt > 0.5f ) {
return;
}

8
libraries/AP_InertialNav/AP_InertialNav.h
View File

@ -8,9 +8,9 @@
#include <AP_Baro.h> // ArduPilot Mega Barometer Library
#include <AP_Buffer.h> // FIFO buffer library
#define AP_INTERTIALNAV_GRAVITY 9.80665
#define AP_INTERTIALNAV_TC_XY 3.0 // default time constant for complementary filter's X & Y axis
#define AP_INTERTIALNAV_TC_Z 7.0 // default time constant for complementary filter's Z axis
#define AP_INTERTIALNAV_GRAVITY 9.80665f
#define AP_INTERTIALNAV_TC_XY 3.0f // default time constant for complementary filter's X & Y axis
#define AP_INTERTIALNAV_TC_Z 7.0f // default time constant for complementary filter's Z axis
#define AP_INTERTIALNAV_ACCEL_CORR_MAX 100.0 // max allowed accelerometer offset correction
@ -19,7 +19,7 @@
#define AP_INTERTIALNAV_SAVE_POS_AFTER_ITERATIONS 10
#define AP_INTERTIALNAV_GPS_LAG_IN_10HZ_INCREMENTS 4 // must not be larger than size of _hist_position_estimate_x and _hist_position_estimate_y
#define AP_INERTIALNAV_LATLON_TO_CM 1.1113175
#define AP_INERTIALNAV_LATLON_TO_CM 1.1113175f
/*
* AP_InertialNav is an attempt to use accelerometers to augment other sensors to improve altitud e position hold

22
libraries/AP_InertialSensor/AP_InertialSensor.cpp
View File

@ -289,7 +289,7 @@ AP_InertialSensor::_init_accel(void (*flash_leds_cb)(bool on))
// TO-DO: replace with gravity #define form location.cpp
accel_offset.z += GRAVITY;
total_change = fabs(prev.x - accel_offset.x) + fabs(prev.y - accel_offset.y) + fabs(prev.z - accel_offset.z);
total_change = fabsf(prev.x - accel_offset.x) + fabsf(prev.y - accel_offset.y) + fabsf(prev.z - accel_offset.z);
max_offset = (accel_offset.x > accel_offset.y) ? accel_offset.x : accel_offset.y;
max_offset = (max_offset > accel_offset.z) ? max_offset : accel_offset.z;
@ -416,7 +416,7 @@ bool AP_InertialSensor::_calibrate_accel( Vector3f accel_sample[6],
// reset
beta[0] = beta[1] = beta[2] = 0;
beta[3] = beta[4] = beta[5] = 1.0/GRAVITY;
beta[3] = beta[4] = beta[5] = 1.0f/GRAVITY;
while( num_iterations < 20 && change > eps ) {
num_iterations++;
@ -454,11 +454,11 @@ bool AP_InertialSensor::_calibrate_accel( Vector3f accel_sample[6],
accel_offsets.z = beta[2] * accel_scale.z;
// sanity check scale
if( accel_scale.is_nan() || fabs(accel_scale.x-1.0) > 0.1 || fabs(accel_scale.y-1.0) > 0.1 || fabs(accel_scale.z-1.0) > 0.1 ) {
if( accel_scale.is_nan() || fabsf(accel_scale.x-1.0f) > 0.1f || fabsf(accel_scale.y-1.0f) > 0.1f || fabsf(accel_scale.z-1.0f) > 0.1f ) {
success = false;
}
// sanity check offsets (2.0 is roughly 2/10th of a G, 5.0 is roughly half a G)
if( accel_offsets.is_nan() || fabs(accel_offsets.x) > 2.0 || fabs(accel_offsets.y) > 2.0 || fabs(accel_offsets.z) > 3.0 ) {
if( accel_offsets.is_nan() || fabsf(accel_offsets.x) > 2.0f || fabsf(accel_offsets.y) > 2.0f || fabsf(accel_offsets.z) > 3.0f ) {
success = false;
}
@ -478,8 +478,8 @@ void AP_InertialSensor::_calibrate_update_matrices(float dS[6], float JS[6][6],
b = beta[3+j];
dx = (float)data[j] - beta[j];
residual -= b*b*dx*dx;
jacobian[j] = 2.0*b*b*dx;
jacobian[3+j] = -2.0*b*dx*dx;
jacobian[j] = 2.0f*b*b*dx;
jacobian[3+j] = -2.0f*b*dx*dx;
}
for( j=0; j<6; j++ ) {
@ -496,9 +496,9 @@ void AP_InertialSensor::_calibrate_reset_matrices(float dS[6], float JS[6][6])
{
int16_t j,k;
for( j=0; j<6; j++ ) {
dS[j] = 0.0;
dS[j] = 0.0f;
for( k=0; k<6; k++ ) {
JS[j][k] = 0.0;
JS[j][k] = 0.0f;
}
}
}
@ -515,7 +515,7 @@ void AP_InertialSensor::_calibrate_find_delta(float dS[6], float JS[6][6], float
//eliminate all nonzero entries below JS[i][i]
for( j=i+1; j<6; j++ ) {
mu = JS[i][j]/JS[i][i];
if( mu != 0.0 ) {
if( mu != 0.0f ) {
dS[j] -= mu*dS[i];
for( k=j; k<6; k++ ) {
JS[k][j] -= mu*JS[k][i];
@ -527,12 +527,12 @@ void AP_InertialSensor::_calibrate_find_delta(float dS[6], float JS[6][6], float
//back-substitute
for( i=5; i>=0; i-- ) {
dS[i] /= JS[i][i];
JS[i][i] = 1.0;
JS[i][i] = 1.0f;
for( j=0; j<i; j++ ) {
mu = JS[i][j];
dS[j] -= mu*dS[i];
JS[i][j] = 0.0;
JS[i][j] = 0.0f;
}
}

6
libraries/AP_InertialSensor/AP_InertialSensor.h
View File

@ -3,10 +3,10 @@
#ifndef __AP_INERTIAL_SENSOR_H__
#define __AP_INERTIAL_SENSOR_H__
#define GRAVITY 9.80665
#define GRAVITY 9.80665f
// Gyro and Accelerometer calibration criteria
#define AP_INERTIAL_SENSOR_ACCEL_TOT_MAX_OFFSET_CHANGE 4.0
#define AP_INERTIAL_SENSOR_ACCEL_MAX_OFFSET 250.0
#define AP_INERTIAL_SENSOR_ACCEL_TOT_MAX_OFFSET_CHANGE 4.0f
#define AP_INERTIAL_SENSOR_ACCEL_MAX_OFFSET 250.0f
#include <stdint.h>
#include <AP_HAL.h>

4
libraries/AP_InertialSensor/AP_InertialSensor_MPU6000.cpp
View File

@ -6,7 +6,7 @@
extern const AP_HAL::HAL& hal;
// MPU6000 accelerometer scaling
#define MPU6000_ACCEL_SCALE_1G (GRAVITY / 4096.0)
#define MPU6000_ACCEL_SCALE_1G (GRAVITY / 4096.0f)
// MPU 6000 registers
#define MPUREG_XG_OFFS_TC 0x00
@ -318,7 +318,7 @@ bool AP_InertialSensor_MPU6000::update( void )
}
hal.scheduler->resume_timer_procs();
count_scale = 1.0 / _num_samples;
count_scale = 1.0f / _num_samples;
_gyro = Vector3f(_gyro_data_sign[0] * sum[_gyro_data_index[0]],
_gyro_data_sign[1] * sum[_gyro_data_index[1]],

12
libraries/AP_InertialSensor/AP_InertialSensor_Oilpan.cpp
View File

@ -24,17 +24,17 @@ const float AP_InertialSensor_Oilpan::_adc_constraint = 900;
// Tested value : 418
// Oilpan accelerometer scaling & offsets
#define OILPAN_ACCEL_SCALE_1G (GRAVITY * 2.0 / (2465.0 - 1617.0))
#define OILPAN_RAW_ACCEL_OFFSET ((2465.0 + 1617.0) * 0.5)
#define OILPAN_RAW_GYRO_OFFSET 1658.0
#define OILPAN_ACCEL_SCALE_1G (GRAVITY * 2.0f / (2465.0f - 1617.0f))
#define OILPAN_RAW_ACCEL_OFFSET ((2465.0f + 1617.0f) * 0.5f)
#define OILPAN_RAW_GYRO_OFFSET 1658.0f
#define ToRad(x) radians(x) // *pi/180
// IDG500 Sensitivity (from datasheet) => 2.0mV/degree/s,
// 0.8mV/ADC step => 0.8/3.33 = 0.4
// Tested values : 0.4026, ?, 0.4192
const float AP_InertialSensor_Oilpan::_gyro_gain_x = ToRad(0.4);
const float AP_InertialSensor_Oilpan::_gyro_gain_y = ToRad(0.41);
const float AP_InertialSensor_Oilpan::_gyro_gain_z = ToRad(0.41);
const float AP_InertialSensor_Oilpan::_gyro_gain_x = ToRad(0.4f);
const float AP_InertialSensor_Oilpan::_gyro_gain_y = ToRad(0.41f);
const float AP_InertialSensor_Oilpan::_gyro_gain_z = ToRad(0.41f);
/* ------ Public functions -------------------------------------------*/

14
libraries/AP_Math/AP_Math.cpp
View File

@ -8,13 +8,13 @@ float safe_asin(float v)
if (isnan(v)) {
return 0.0;
}
if (v >= 1.0) {
if (v >= 1.0f) {
return PI/2;
}
if (v <= -1.0) {
if (v <= -1.0f) {
return -PI/2;
}
return asin(v);
return asinf(v);
}
// a varient of sqrt() that checks the input ranges and ensures a
@ -24,7 +24,7 @@ float safe_asin(float v)
// real input should have been zero
float safe_sqrt(float v)
{
float ret = sqrt(v);
float ret = sqrtf(v);
if (isnan(ret)) {
return 0;
}
@ -51,7 +51,7 @@ enum Rotation rotation_combination(enum Rotation r1, enum Rotation r2, bool *fou
tv2(1,2,3);
tv2.rotate(r);
diff = tv1 - tv2;
if (diff.length() < 1.0e-6) {
if (diff.length() < 1.0e-6f) {
// we found a match
if (found) {
*found = true;
@ -101,10 +101,10 @@ float sq(float v) {
// 2D vector length
float pythagorous2(float a, float b) {
return sqrt(sq(a)+sq(b));
return sqrtf(sq(a)+sq(b));
}
// 3D vector length
float pythagorous3(float a, float b, float c) {
return sqrt(sq(a)+sq(b)+sq(c));
return sqrtf(sq(a)+sq(b)+sq(c));
}

8
libraries/AP_Math/AP_Math.h
View File

@ -17,13 +17,13 @@
#include "polygon.h"
#ifndef PI
#define PI 3.141592653589793
#define PI 3.141592653589793f
#endif
#define DEG_TO_RAD 0.017453292519943295769236907684886
#define RAD_TO_DEG 57.295779513082320876798154814105
#define DEG_TO_RAD 0.017453292519943295769236907684886f
#define RAD_TO_DEG 57.295779513082320876798154814105f
// acceleration due to gravity in m/s/s
#define GRAVITY_MSS 9.80665
#define GRAVITY_MSS 9.80665f
#define ROTATION_COMBINATION_SUPPORT 0

2
libraries/AP_Math/examples/eulers/eulers.pde
View File

@ -22,7 +22,7 @@ static float rad_diff(float rad1, float rad2)
if (diff < -PI) {
diff += 2*PI;
}
return fabs(diff);
return fabsf(diff);
}
static void check_result(float roll, float pitch, float yaw,

2
libraries/AP_Math/examples/location/location.pde
View File

@ -85,7 +85,7 @@ static void test_one_offset(struct Location &loc,
brg_error += 360;
}
if (fabs(dist - dist2) > 1.0 ||
if (fabsf(dist - dist2) > 1.0 ||
brg_error > 1.0) {
hal.console->printf("Failed offset test brg_error=%f dist_error=%f\n",
brg_error, dist-dist2);

26
libraries/AP_Math/location.cpp
View File

@ -36,7 +36,7 @@ static float longitude_scale(const struct Location *loc)
// the same scale factor.
return scale;
}
scale = cos((fabs((float)loc->lat)/1.0e7) * 0.0174532925);
scale = cosf((fabsf((float)loc->lat)/1.0e7f) * 0.0174532925f);
last_lat = loc->lat;
return scale;
}
@ -53,7 +53,7 @@ float get_distance(const struct Location *loc1, const struct Location *loc2)
return -1;
float dlat = (float)(loc2->lat - loc1->lat);
float dlong = ((float)(loc2->lng - loc1->lng)) * longitude_scale(loc2);
return pythagorous2(dlat, dlong) * 0.01113195;
return pythagorous2(dlat, dlong) * 0.01113195f;
}
// return distance in centimeters to between two locations, or -1 if
@ -68,7 +68,7 @@ int32_t get_bearing_cd(const struct Location *loc1, const struct Location *loc2)
{
int32_t off_x = loc2->lng - loc1->lng;
int32_t off_y = (loc2->lat - loc1->lat) / longitude_scale(loc2);
int32_t bearing = 9000 + atan2(-off_y, off_x) * 5729.57795;
int32_t bearing = 9000 + atan2f(-off_y, off_x) * 5729.57795f;
if (bearing < 0) bearing += 36000;
return bearing;
}
@ -120,17 +120,17 @@ bool location_passed_point(struct Location &location,
*/
void location_update(struct Location *loc, float bearing, float distance)
{
float lat1 = radians(loc->lat*1.0e-7);
float lon1 = radians(loc->lng*1.0e-7);
float lat1 = radians(loc->lat*1.0e-7f);
float lon1 = radians(loc->lng*1.0e-7f);
float brng = radians(bearing);
float dr = distance/RADIUS_OF_EARTH;
float lat2 = asin(sin(lat1)*cos(dr) +
cos(lat1)*sin(dr)*cos(brng));
float lon2 = lon1 + atan2(sin(brng)*sin(dr)*cos(lat1),
cos(dr)-sin(lat1)*sin(lat2));
loc->lat = degrees(lat2)*1.0e7;
loc->lng = degrees(lon2)*1.0e7;
float lat2 = asinf(sinf(lat1)*cosf(dr) +
cosf(lat1)*sinf(dr)*cosf(brng));
float lon2 = lon1 + atan2f(sinf(brng)*sinf(dr)*cosf(lat1),
cosf(dr)-sinf(lat1)*sinf(lat2));
loc->lat = degrees(lat2)*1.0e7f;
loc->lng = degrees(lon2)*1.0e7f;
}
/*
@ -140,8 +140,8 @@ void location_update(struct Location *loc, float bearing, float distance)
void location_offset(struct Location *loc, float ofs_north, float ofs_east)
{
if (ofs_north != 0 || ofs_east != 0) {
float dlat = ofs_north * 89.831520982;
float dlng = (ofs_east * 89.831520982) / longitude_scale(loc);
float dlat = ofs_north * 89.831520982f;
float dlng = (ofs_east * 89.831520982f) / longitude_scale(loc);
loc->lat += dlat;
loc->lng += dlng;
}

16
libraries/AP_Math/matrix3.cpp
View File

@ -140,12 +140,12 @@ void Matrix3<T>::rotation(enum Rotation r)
template <typename T>
void Matrix3<T>::from_euler(float roll, float pitch, float yaw)
{
float cp = cos(pitch);
float sp = sin(pitch);
float sr = sin(roll);
float cr = cos(roll);
float sy = sin(yaw);
float cy = cos(yaw);
float cp = cosf(pitch);
float sp = sinf(pitch);
float sr = sinf(roll);
float cr = cosf(roll);
float sy = sinf(yaw);
float cy = cosf(yaw);
a.x = cp * cy;
a.y = (sr * sp * cy) - (cr * sy);
@ -167,10 +167,10 @@ void Matrix3<T>::to_euler(float *roll, float *pitch, float *yaw)
*pitch = -safe_asin(c.x);
}
if (roll != NULL) {
*roll = atan2(c.y, c.z);
*roll = atan2f(c.y, c.z);
}
if (yaw != NULL) {
*yaw = atan2(b.x, a.x);
*yaw = atan2f(b.x, a.x);
}
}

22
libraries/AP_Math/quaternion.cpp
View File

@ -58,12 +58,12 @@ void Quaternion::earth_to_body(Vector3f &v)
// create a quaternion from Euler angles
void Quaternion::from_euler(float roll, float pitch, float yaw)
{
float cr2 = cos(roll*0.5);
float cp2 = cos(pitch*0.5);
float cy2 = cos(yaw*0.5);
float sr2 = sin(roll*0.5);
float sp2 = sin(pitch*0.5);
float sy2 = sin(yaw*0.5);
float cr2 = cosf(roll*0.5f);
float cp2 = cosf(pitch*0.5f);
float cy2 = cosf(yaw*0.5f);
float sr2 = sinf(roll*0.5f);
float sp2 = sinf(pitch*0.5f);
float sy2 = sinf(yaw*0.5f);
q1 = cr2*cp2*cy2 + sr2*sp2*sy2;
q2 = sr2*cp2*cy2 - cr2*sp2*sy2;
@ -75,15 +75,15 @@ void Quaternion::from_euler(float roll, float pitch, float yaw)
void Quaternion::to_euler(float *roll, float *pitch, float *yaw)
{
if (roll) {
*roll = (atan2(2.0*(q1*q2 + q3*q4),
1 - 2.0*(q2*q2 + q3*q3)));
*roll = (atan2f(2.0f*(q1*q2 + q3*q4),
1 - 2.0f*(q2*q2 + q3*q3)));
}
if (pitch) {
// we let safe_asin() handle the singularities near 90/-90 in pitch
*pitch = safe_asin(2.0*(q1*q3 - q4*q2));
*pitch = safe_asin(2.0f*(q1*q3 - q4*q2));
}
if (yaw) {
*yaw = atan2(2.0*(q1*q4 + q2*q3),
1 - 2.0*(q3*q3 + q4*q4));
*yaw = atan2f(2.0f*(q1*q4 + q2*q3),
1 - 2.0f*(q3*q3 + q4*q4));
}
}

6
libraries/AP_Math/vector2.h
View File

@ -167,19 +167,19 @@ struct Vector2
// computes the angle between 2 arbitrary vectors
T angle(const Vector2<T> &v1, const Vector2<T> &v2)
{
return (T)acos((v1*v2) / (v1.length()*v2.length()));
return (T)acosf((v1*v2) / (v1.length()*v2.length()));
}
// computes the angle between this vector and another vector
T angle(const Vector2<T> &v2)
{
return (T)acos(((*this)*v2) / (this->length()*v2.length()));
return (T)acosf(((*this)*v2) / (this->length()*v2.length()));
}
// computes the angle between 2 normalized arbitrary vectors
T angle_normalized(const Vector2<T> &v1, const Vector2<T> &v2)
{
return (T)acos(v1*v2);
return (T)acosf(v1*v2);
}
};

2
libraries/AP_Math/vector3.cpp
View File

@ -19,7 +19,7 @@
#include "AP_Math.h"
#define HALF_SQRT_2 0.70710678118654757
#define HALF_SQRT_2 0.70710678118654757f
// rotate a vector by a standard rotation, attempting
// to use the minimum number of floating point operations

6
libraries/AP_Math/vector3.h
View File

@ -193,19 +193,19 @@ public:
// computes the angle between 2 arbitrary vectors
T angle(const Vector3<T> &v1, const Vector3<T> &v2)
{
return (T)acos((v1*v2) / (v1.length()*v2.length()));
return (T)acosf((v1*v2) / (v1.length()*v2.length()));
}
// computes the angle between this vector and another vector
T angle(const Vector3<T> &v2)
{
return (T)acos(((*this)*v2) / (this->length()*v2.length()));
return (T)acosf(((*this)*v2) / (this->length()*v2.length()));
}
// computes the angle between 2 arbitrary normalized vectors
T angle_normalized(const Vector3<T> &v1, const Vector3<T> &v2)
{
return (T)acos(v1*v2);
return (T)acosf(v1*v2);
}
// check if any elements are NAN

42
libraries/AP_Motors/AP_MotorsHeli.cpp
View File

@ -330,14 +330,14 @@ void AP_MotorsHeli::reset_swash()
if( swash_type == AP_MOTORS_HELI_SWASH_CCPM ) { //CCPM Swashplate, perform servo control mixing
// roll factors
_rollFactor[CH_1] = cos(radians(servo1_pos + 90 - phase_angle));
_rollFactor[CH_2] = cos(radians(servo2_pos + 90 - phase_angle));
_rollFactor[CH_3] = cos(radians(servo3_pos + 90 - phase_angle));
_rollFactor[CH_1] = cosf(radians(servo1_pos + 90 - phase_angle));
_rollFactor[CH_2] = cosf(radians(servo2_pos + 90 - phase_angle));
_rollFactor[CH_3] = cosf(radians(servo3_pos + 90 - phase_angle));
// pitch factors
_pitchFactor[CH_1] = cos(radians(servo1_pos - phase_angle));
_pitchFactor[CH_2] = cos(radians(servo2_pos - phase_angle));
_pitchFactor[CH_3] = cos(radians(servo3_pos - phase_angle));
_pitchFactor[CH_1] = cosf(radians(servo1_pos - phase_angle));
_pitchFactor[CH_2] = cosf(radians(servo2_pos - phase_angle));
_pitchFactor[CH_3] = cosf(radians(servo3_pos - phase_angle));
// collective factors
_collectiveFactor[CH_1] = 1;
@ -363,10 +363,10 @@ void AP_MotorsHeli::reset_swash()
}
// set roll, pitch and throttle scaling
_roll_scaler = 1.0;
_pitch_scaler = 1.0;
_collective_scalar = ((float)(_rc_throttle->radio_max - _rc_throttle->radio_min))/1000.0;
_stab_throttle_scalar = 1.0;
_roll_scaler = 1.0f;
_pitch_scaler = 1.0f;
_collective_scalar = ((float)(_rc_throttle->radio_max - _rc_throttle->radio_min))/1000.0f;
_stab_throttle_scalar = 1.0f;
// we must be in set-up mode so mark swash as uninitialised
_swash_initialised = false;
@ -391,25 +391,25 @@ void AP_MotorsHeli::init_swash()
collective_mid = constrain(collective_mid, collective_min, collective_max);
// calculate throttle mid point
throttle_mid = ((float)(collective_mid-collective_min))/((float)(collective_max-collective_min))*1000.0;
throttle_mid = ((float)(collective_mid-collective_min))/((float)(collective_max-collective_min))*1000.0f;
// determine roll, pitch and throttle scaling
_roll_scaler = (float)roll_max/4500.0;
_pitch_scaler = (float)pitch_max/4500.0;
_collective_scalar = ((float)(collective_max-collective_min))/1000.0;
_stab_throttle_scalar = ((float)(stab_col_max - stab_col_min))/100.0;
_roll_scaler = (float)roll_max/4500.0f;
_pitch_scaler = (float)pitch_max/4500.0f;
_collective_scalar = ((float)(collective_max-collective_min))/1000.0f;
_stab_throttle_scalar = ((float)(stab_col_max - stab_col_min))/100.0f;
if( swash_type == AP_MOTORS_HELI_SWASH_CCPM ) { //CCPM Swashplate, perform control mixing
// roll factors
_rollFactor[CH_1] = cos(radians(servo1_pos + 90 - phase_angle));
_rollFactor[CH_2] = cos(radians(servo2_pos + 90 - phase_angle));
_rollFactor[CH_3] = cos(radians(servo3_pos + 90 - phase_angle));
_rollFactor[CH_1] = cosf(radians(servo1_pos + 90 - phase_angle));
_rollFactor[CH_2] = cosf(radians(servo2_pos + 90 - phase_angle));
_rollFactor[CH_3] = cosf(radians(servo3_pos + 90 - phase_angle));
// pitch factors
_pitchFactor[CH_1] = cos(radians(servo1_pos - phase_angle));
_pitchFactor[CH_2] = cos(radians(servo2_pos - phase_angle));
_pitchFactor[CH_3] = cos(radians(servo3_pos - phase_angle));
_pitchFactor[CH_1] = cosf(radians(servo1_pos - phase_angle));
_pitchFactor[CH_2] = cosf(radians(servo2_pos - phase_angle));
_pitchFactor[CH_3] = cosf(radians(servo3_pos - phase_angle));
// collective factors
_collectiveFactor[CH_1] = 1;

4
libraries/AP_Motors/AP_MotorsMatrix.cpp
View File

@ -353,8 +353,8 @@ void AP_MotorsMatrix::add_motor(int8_t motor_num, float angle_degrees, int8_t di
// call raw motor set-up method
add_motor_raw(
motor_num,
cos(radians(angle_degrees + 90)), // roll factor
cos(radians(angle_degrees)), // pitch factor
cosf(radians(angle_degrees + 90)), // roll factor
cosf(radians(angle_degrees)), // pitch factor
(float)direction, // yaw factor
testing_order);

2
libraries/AP_Motors/AP_MotorsTri.cpp
View File

@ -80,7 +80,7 @@ void AP_MotorsTri::output_armed()
_rc_throttle->calc_pwm();
_rc_yaw->calc_pwm();
int roll_out = (float)_rc_roll->pwm_out * .866;
int roll_out = (float)_rc_roll->pwm_out * 0.866f;
int pitch_out = _rc_pitch->pwm_out / 2;
//left front

4
libraries/AP_Motors/AP_Motors_Class.cpp
View File

@ -97,8 +97,8 @@ bool AP_Motors::setup_throttle_curve()
int16_t min_pwm = _rc_throttle->radio_min;
int16_t max_pwm = _rc_throttle->radio_max;
int16_t mid_throttle_pwm = (max_pwm + min_pwm) / 2;
int16_t mid_thrust_pwm = min_pwm + (float)(max_pwm - min_pwm) * ((float)_throttle_curve_mid/100.0);
int16_t max_thrust_pwm = min_pwm + (float)(max_pwm - min_pwm) * ((float)_throttle_curve_max/100.0);
int16_t mid_thrust_pwm = min_pwm + (float)(max_pwm - min_pwm) * ((float)_throttle_curve_mid/100.0f);
int16_t max_thrust_pwm = min_pwm + (float)(max_pwm - min_pwm) * ((float)_throttle_curve_max/100.0f);
bool retval = true;
// some basic checks that the curve is valid

42
libraries/AP_Mount/AP_Mount.cpp
View File

@ -346,21 +346,21 @@ void AP_Mount::update_mount_position()
// allow pilot speed position input to come directly from an RC_Channel
if (_roll_rc_in && (rc_ch[_roll_rc_in-1])) {
//_roll_control_angle += angle_input(rc_ch[_roll_rc_in-1], _roll_angle_min, _roll_angle_max) * 0.00001 * _joystick_speed;
_roll_control_angle += rc_ch[_roll_rc_in-1]->norm_input() * 0.00001 * _joystick_speed;
if (_roll_control_angle < radians(_roll_angle_min*0.01)) _roll_control_angle = radians(_roll_angle_min*0.01);
if (_roll_control_angle > radians(_roll_angle_max*0.01)) _roll_control_angle = radians(_roll_angle_max*0.01);
_roll_control_angle += rc_ch[_roll_rc_in-1]->norm_input() * 0.00001f * _joystick_speed;
if (_roll_control_angle < radians(_roll_angle_min*0.01f)) _roll_control_angle = radians(_roll_angle_min*0.01f);
if (_roll_control_angle > radians(_roll_angle_max*0.01f)) _roll_control_angle = radians(_roll_angle_max*0.01f);
}
if (_tilt_rc_in && (rc_ch[_tilt_rc_in-1])) {
//_tilt_control_angle += angle_input(rc_ch[_tilt_rc_in-1], _tilt_angle_min, _tilt_angle_max) * 0.00001 * _joystick_speed;
_tilt_control_angle += rc_ch[_tilt_rc_in-1]->norm_input() * 0.00001 * _joystick_speed;
if (_tilt_control_angle < radians(_tilt_angle_min*0.01)) _tilt_control_angle = radians(_tilt_angle_min*0.01);
if (_tilt_control_angle > radians(_tilt_angle_max*0.01)) _tilt_control_angle = radians(_tilt_angle_max*0.01);
_tilt_control_angle += rc_ch[_tilt_rc_in-1]->norm_input() * 0.00001f * _joystick_speed;
if (_tilt_control_angle < radians(_tilt_angle_min*0.01f)) _tilt_control_angle = radians(_tilt_angle_min*0.01f);
if (_tilt_control_angle > radians(_tilt_angle_max*0.01f)) _tilt_control_angle = radians(_tilt_angle_max*0.01f);
}
if (_pan_rc_in && (rc_ch[_pan_rc_in-1])) {
//_pan_control_angle += angle_input(rc_ch[_pan_rc_in-1], _pan_angle_min, _pan_angle_max) * 0.00001 * _joystick_speed;
_pan_control_angle += rc_ch[_pan_rc_in-1]->norm_input() * 0.00001 * _joystick_speed;
if (_pan_control_angle < radians(_pan_angle_min*0.01)) _pan_control_angle = radians(_pan_angle_min*0.01);
if (_pan_control_angle > radians(_pan_angle_max*0.01)) _pan_control_angle = radians(_pan_angle_max*0.01);
_pan_control_angle += rc_ch[_pan_rc_in-1]->norm_input() * 0.00001f * _joystick_speed;
if (_pan_control_angle < radians(_pan_angle_min*0.01f)) _pan_control_angle = radians(_pan_angle_min*0.01f);
if (_pan_control_angle > radians(_pan_angle_max*0.01f)) _pan_control_angle = radians(_pan_angle_max*0.01f);
}
} else {
#endif
@ -408,9 +408,9 @@ void AP_Mount::update_mount_position()
#endif
// write the results to the servos
move_servo(_roll_idx, _roll_angle*10, _roll_angle_min*0.1, _roll_angle_max*0.1);
move_servo(_tilt_idx, _tilt_angle*10, _tilt_angle_min*0.1, _tilt_angle_max*0.1);
move_servo(_pan_idx, _pan_angle*10, _pan_angle_min*0.1, _pan_angle_max*0.1);
move_servo(_roll_idx, _roll_angle*10, _roll_angle_min*0.1f, _roll_angle_max*0.1f);
move_servo(_tilt_idx, _tilt_angle*10, _tilt_angle_min*0.1f, _tilt_angle_max*0.1f);
move_servo(_pan_idx, _pan_angle*10, _pan_angle_min*0.1f, _pan_angle_max*0.1f);
}
void AP_Mount::set_mode(enum MAV_MOUNT_MODE mode)
@ -449,7 +449,7 @@ void AP_Mount::control_msg(mavlink_message_t *msg)
{
#if MNT_RETRACT_OPTION == ENABLED
case MAV_MOUNT_MODE_RETRACT: // Load and keep safe position (Roll,Pitch,Yaw) from EEPROM and stop stabilization
set_retract_angles(packet.input_b*0.01, packet.input_a*0.01, packet.input_c*0.01);
set_retract_angles(packet.input_b*0.01f, packet.input_a*0.01f, packet.input_c*0.01f);
if (packet.save_position)
{
_retract_angles.save();
@ -458,7 +458,7 @@ void AP_Mount::control_msg(mavlink_message_t *msg)
#endif
case MAV_MOUNT_MODE_NEUTRAL: // Load and keep neutral position (Roll,Pitch,Yaw) from EEPROM
set_neutral_angles(packet.input_b*0.01, packet.input_a*0.01, packet.input_c*0.01);
set_neutral_angles(packet.input_b*0.01f, packet.input_a*0.01f, packet.input_c*0.01f);
if (packet.save_position)
{
_neutral_angles.save();
@ -466,7 +466,7 @@ void AP_Mount::control_msg(mavlink_message_t *msg)
break;
case MAV_MOUNT_MODE_MAVLINK_TARGETING: // Load neutral position and start MAVLink Roll,Pitch,Yaw control with stabilization
set_control_angles(packet.input_b*0.01, packet.input_a*0.01, packet.input_c*0.01);
set_control_angles(packet.input_b*0.01f, packet.input_a*0.01f, packet.input_c*0.01f);
break;
case MAV_MOUNT_MODE_RC_TARGETING: // Load neutral position and start RC Roll,Pitch,Yaw control with stabilization
@ -570,19 +570,19 @@ AP_Mount::angle_input(RC_Channel* rc, int16_t angle_min, int16_t angle_max)
float
AP_Mount::angle_input_rad(RC_Channel* rc, int16_t angle_min, int16_t angle_max)
{
return radians(angle_input(rc, angle_min, angle_max)*0.01);
return radians(angle_input(rc, angle_min, angle_max)*0.01f);
}
void
AP_Mount::calc_GPS_target_angle(struct Location *target)
{
float GPS_vector_x = (target->lng-_current_loc->lng)*cos(ToRad((_current_loc->lat+target->lat)*.00000005))*.01113195;
float GPS_vector_y = (target->lat-_current_loc->lat)*.01113195;
float GPS_vector_x = (target->lng-_current_loc->lng)*cosf(ToRad((_current_loc->lat+target->lat)*0.00000005f))*0.01113195f;
float GPS_vector_y = (target->lat-_current_loc->lat)*0.01113195f;
float GPS_vector_z = (target->alt-_current_loc->alt); // baro altitude(IN CM) should be adjusted to known home elevation before take off (Set altimeter).
float target_distance = 100.0*pythagorous2(GPS_vector_x, GPS_vector_y); // Careful , centimeters here locally. Baro/alt is in cm, lat/lon is in meters.
float target_distance = 100.0f*pythagorous2(GPS_vector_x, GPS_vector_y); // Careful , centimeters here locally. Baro/alt is in cm, lat/lon is in meters.
_roll_control_angle = 0;
_tilt_control_angle = atan2(GPS_vector_z, target_distance);
_pan_control_angle = atan2(GPS_vector_x, GPS_vector_y);
_tilt_control_angle = atan2f(GPS_vector_z, target_distance);
_pan_control_angle = atan2f(GPS_vector_x, GPS_vector_y);
}
/// Stabilizes mount relative to the Earth's frame

12
libraries/AP_OpticalFlow/AP_OpticalFlow.cpp
View File

@ -10,7 +10,7 @@
#include "AP_OpticalFlow.h"
#define FORTYFIVE_DEGREES 0.78539816
#define FORTYFIVE_DEGREES 0.78539816f
// pointer to the last instantiated optical flow sensor. Will be turned into
// a table if we ever add support for more than one sensor
@ -81,8 +81,8 @@ void AP_OpticalFlow::update_conversion_factors()
{
// multiply this number by altitude and pixel change to get horizontal
// move (in same units as altitude)
conv_factor = ((1.0 / (float)(num_pixels * scaler))
* 2.0 * tan(field_of_view / 2.0));
conv_factor = ((1.0f / (float)(num_pixels * scaler))
* 2.0f * tanf(field_of_view / 2.0f));
// 0.00615
radians_to_pixels = (num_pixels * scaler) / field_of_view;
// 162.99
@ -97,8 +97,8 @@ void AP_OpticalFlow::update_position(float roll, float pitch,
// only update position if surface quality is good and angle is not
// over 45 degrees
if( surface_quality >= 10 && fabs(roll) <= FORTYFIVE_DEGREES
&& fabs(pitch) <= FORTYFIVE_DEGREES ) {
if( surface_quality >= 10 && fabsf(roll) <= FORTYFIVE_DEGREES
&& fabsf(pitch) <= FORTYFIVE_DEGREES ) {
altitude = max(altitude, 0);
// calculate expected x,y diff due to roll and pitch change
exp_change_x = diff_roll * radians_to_pixels;
@ -108,7 +108,7 @@ void AP_OpticalFlow::update_position(float roll, float pitch,
change_x = dx - exp_change_x;
change_y = dy - exp_change_y;
float avg_altitude = (altitude + _last_altitude)*0.5;
float avg_altitude = (altitude + _last_altitude)*0.5f;
// convert raw change to horizontal movement in cm
// perhaps this altitude should actually be the distance to the

2
libraries/AP_Param/AP_Param.cpp
View File

@ -696,7 +696,7 @@ bool AP_Param::save(void)
return true;
}
if (phdr.type != AP_PARAM_INT32 &&
(fabs(v1-v2) < 0.0001*fabs(v1))) {
(fabsf(v1-v2) < 0.0001f*fabsf(v1))) {
// for other than 32 bit integers, we accept values within
// 0.01 percent of the current value as being the same
return true;

4
libraries/AP_RangeFinder/AP_RangeFinder_MaxsonarXL.cpp
View File

@ -40,7 +40,7 @@ AP_RangeFinder_MaxsonarXL::AP_RangeFinder_MaxsonarXL(AP_HAL::AnalogSource *sourc
// Public Methods //////////////////////////////////////////////////////////////
float AP_RangeFinder_MaxsonarXL::calculate_scaler(int sonar_type, float adc_refence_voltage)
{
float type_scaler = 1.0;
float type_scaler = 1.0f;
switch(sonar_type) {
case AP_RANGEFINDER_MAXSONARXL:
type_scaler = AP_RANGEFINDER_MAXSONARXL_SCALER;
@ -63,6 +63,6 @@ float AP_RangeFinder_MaxsonarXL::calculate_scaler(int sonar_type, float adc_refe
max_distance = AP_RANGEFINDER_MAXSONARHRLV_MAX_DISTANCE;
break;
}
_scaler = type_scaler * adc_refence_voltage / 5.0;
_scaler = type_scaler * adc_refence_voltage / 5.0f;
return _scaler;
}

2
libraries/Filter/LowPassFilter.h
View File

@ -78,7 +78,7 @@ template <class T>
void LowPassFilter<T>::set_cutoff_frequency(float time_step, float cutoff_freq)
{
// calculate alpha
float rc = 1/(2*(float)M_PI*cutoff_freq);
float rc = 1/(2*PI*cutoff_freq);
_alpha = time_step / (time_step + rc);
}

8
libraries/Filter/examples/Derivative/Derivative.pde
View File

@ -21,7 +21,7 @@ void setup(){}
static float noise(void)
{
return ((random() % 100)-50) * 0.001;
return ((random() % 100)-50) * 0.001f;
}
//Main loop where the action takes place
@ -29,12 +29,12 @@ void loop()
{
hal.scheduler->delay(50);
float t = hal.scheduler->millis()*1.0e-3;
float s = sin(t);
float s = sinf(t);
//s += noise();
uint32_t t1 = hal.scheduler->micros();
derivative.update(s, t1);
float output = derivative.slope() * 1.0e6;
hal.console->printf("%f %f %f %f\n", t, output, s, cos(t));
float output = derivative.slope() * 1.0e6f;
hal.console->printf("%f %f %f %f\n", t, output, s, cosf(t));
}
AP_HAL_MAIN();

6
libraries/Filter/examples/LowPassFilter/LowPassFilter.pde
View File

@ -24,8 +24,8 @@ void setup()
hal.console->printf("ArduPilot LowPassFilter test ver 1.0\n\n");
// set-up filter
low_pass_filter.set_time_constant(0.02, 0.015);
//low_pass_filter.set_cutoff_frequency(0.02, 1.0);
low_pass_filter.set_time_constant(0.02f, 0.015f);
//low_pass_filter.set_cutoff_frequency(0.02f, 1.0f);
// Wait for the serial connection
hal.scheduler->delay(500);
@ -44,7 +44,7 @@ void loop()
for( i=0; i<300; i++ ) {
// new data value
new_value = sin((float)i*2*M_PI*5/50.0); // 5hz
new_value = sinf((float)i*2*PI*5/50.0f); // 5hz
// output to user
hal.console->printf("applying: %6.4f", new_value);

9
libraries/PID/PID.cpp
View File

@ -7,6 +7,7 @@
#include "PID.h"
#include <AP_HAL.h>
#include <AP_Math.h>
extern const AP_HAL::HAL& hal;
@ -36,13 +37,13 @@ int32_t PID::get_pid(int32_t error, float scaler)
}
_last_t = tnow;
delta_time = (float)dt / 1000.0;
delta_time = (float)dt / 1000.0f;
// Compute proportional component
output += error * _kp;
// Compute derivative component if time has elapsed
if ((fabs(_kd) > 0) && (dt > 0)) {
if ((fabsf(_kd) > 0) && (dt > 0)) {
float derivative;
if (isnan(_last_derivative)) {
@ -57,7 +58,7 @@ int32_t PID::get_pid(int32_t error, float scaler)
// discrete low pass filter, cuts out the
// high frequency noise that can drive the controller crazy
float RC = 1/(2*M_PI*_fCut);
float RC = 1/(2*PI*_fCut);
derivative = _last_derivative +
((delta_time / (RC + delta_time)) *
(derivative - _last_derivative));
@ -74,7 +75,7 @@ int32_t PID::get_pid(int32_t error, float scaler)
output *= scaler;
// Compute integral component if time has elapsed
if ((fabs(_ki) > 0) && (dt > 0)) {
if ((fabsf(_ki) > 0) && (dt > 0)) {
_integrator += (error * _ki) * scaler * delta_time;
if (_integrator < -_imax) {
_integrator = -_imax;

2
libraries/RC_Channel/RC_Channel.cpp
View File

@ -180,7 +180,7 @@ RC_Channel::calc_pwm(void)
radio_out = (_reverse >= 0) ? (radio_min + pwm_out) : (radio_max - pwm_out);
}else if(_type == RC_CHANNEL_TYPE_ANGLE_RAW) {
pwm_out = (float)servo_out * .1;
pwm_out = (float)servo_out * 0.1f;
radio_out = (pwm_out * _reverse) + radio_trim;
}else{ // RC_CHANNEL_TYPE_ANGLE