params: ensure short description is only a single line

So a UI can display it properly

src/drivers/rpm/pcf8583/parameters.c

@@ -33,7 +33,8 @@
 
 /**
  * PCF8583 rotorfreq (i2c) pool interval
- * How often the sensor is readout.
+ *
+ * Determines how often the sensor is read out.
  *
  * @reboot_required true
  * @group Sensors

src/drivers/telemetry/iridiumsbd/iridiumsbd_params.c

@@ -20,7 +20,8 @@ PARAM_DEFINE_INT32(ISBD_READ_INT, 0);
 PARAM_DEFINE_INT32(ISBD_SBD_TIMEOUT, 60);
 
 /**
- * Time [ms] the Iridium driver will wait for additional mavlink messages to combine them into one SBD message
+ * Time the Iridium driver will wait for additional mavlink messages to combine them into one SBD message
+ *
  * Value 0 turns the functionality off
  *
  * @unit ms

src/lib/parameters/px4params/srcparser.py

@@ -305,6 +305,8 @@ class SourceParser(object):
                     group = "Miscellaneous"
                     if state == "comment-processed":
                         if short_desc is not None:
+                            if '\n' in short_desc:
+                                raise Exception('short description must be a single line (parameter: {:})'.format(name))
                             param.SetField("short_desc", self.re_remove_dots.sub('', short_desc))
                         if long_desc is not None:
                             long_desc = self.re_remove_carriage_return.sub(' ', long_desc)

src/modules/attitude_estimator_q/attitude_estimator_q_params.c

@@ -103,6 +103,7 @@ PARAM_DEFINE_INT32(ATT_MAG_DECL_A, 1);
 
 /**
  * External heading usage mode (from Motion capture/Vision)
+ *
  * Set to 1 to use heading estimate from vision.
  * Set to 2 to use heading from motion capture.
  *
@@ -116,8 +117,7 @@ PARAM_DEFINE_INT32(ATT_MAG_DECL_A, 1);
 PARAM_DEFINE_INT32(ATT_EXT_HDG_M, 0);
 
 /**
- * Acceleration compensation based on GPS
- * velocity.
+ * Acceleration compensation based on GPS velocity.
  *
  * @group Attitude Q estimator
  * @boolean

src/modules/commander/commander_params.c

@@ -341,6 +341,7 @@ PARAM_DEFINE_INT32(COM_LOW_BAT_ACT, 0);
 
 /**
  * Time-out to wait when offboard connection is lost before triggering offboard lost action.
+ *
  * See COM_OBL_ACT and COM_OBL_RC_ACT to configure action.
  *
  * @group Commander
@@ -595,6 +596,7 @@ PARAM_DEFINE_FLOAT(COM_ARM_IMU_GYR, 0.25f);
 
 /**
  * Maximum magnetic field inconsistency between units that will allow arming
+ *
  * Set -1 to disable the check.
  *
  * @group Commander

src/modules/commander/failure_detector/failure_detector_params.c

@@ -107,9 +107,9 @@ PARAM_DEFINE_FLOAT(FD_FAIL_R_TTRI, 0.3);
 PARAM_DEFINE_FLOAT(FD_FAIL_P_TTRI, 0.3);
 
 /**
- * Enable PWM input on AUX5 or MAIN5 (depending on board) for engaging failsafe from an external
- * automatic trigger system (ATS).
+ * Enable PWM input on for engaging failsafe from an external automatic trigger system (ATS).
  *
+ * Enabled on either AUX5 or MAIN5 depending on board.
  * External ATS is required by ASTM F3322-18.
  *
  * @boolean
@@ -132,6 +132,7 @@ PARAM_DEFINE_INT32(FD_EXT_ATS_TRIG, 1900);
 
 /**
  * Enable checks on ESCs that report their arming state.
+ *
  * If enabled, failure detector will verify that all the ESCs have successfully armed when the vehicle has transitioned to the armed state.
  * Timeout for receiving an acknowledgement from the ESCs is 0.3s, if no feedback is received the failure detector will auto disarm the vehicle.
  *

src/modules/ekf2/ekf2_params.c

@@ -41,6 +41,7 @@
 
 /**
  * Minimum time of arrival delta between non-IMU observations before data is downsampled.
+ *
  * Baro and Magnetometer data will be averaged before downsampling, other data will be point sampled resulting in loss of information.
  *
  * @group EKF2
@@ -89,6 +90,7 @@ PARAM_DEFINE_FLOAT(EKF2_GPS_DELAY, 110);
 
 /**
  * Optical flow measurement delay relative to IMU measurements
+ *
  * Assumes measurement is timestamped at trailing edge of integration period
  *
  * @group EKF2
@@ -493,6 +495,7 @@ PARAM_DEFINE_INT32(EKF2_MAG_TYPE, 0);
 
 /**
  * Horizontal acceleration threshold used by automatic selection of magnetometer fusion method.
+ *
  * This parameter is used when the magnetometer fusion method is set automatically (EKF2_MAG_TYPE = 0). If the filtered horizontal acceleration is greater than this parameter value, then the EKF will use 3-axis magnetomer fusion.
  *
  * @group EKF2
@@ -505,6 +508,7 @@ PARAM_DEFINE_FLOAT(EKF2_MAG_ACCLIM, 0.5f);
 
 /**
  * Yaw rate threshold used by automatic selection of magnetometer fusion method.
+ *
  * This parameter is used when the magnetometer fusion method is set automatically (EKF2_MAG_TYPE = 0). If the filtered yaw rate is greater than this parameter value, then the EKF will use 3-axis magnetomer fusion.
  *
  * @group EKF2
@@ -945,7 +949,9 @@ PARAM_DEFINE_FLOAT(EKF2_EV_POS_Y, 0.0f);
 PARAM_DEFINE_FLOAT(EKF2_EV_POS_Z, 0.0f);
 
 /**
-* Airspeed fusion threshold. A value of zero will deactivate airspeed fusion. Any other positive
+* Airspeed fusion threshold.
+*
+* A value of zero will deactivate airspeed fusion. Any other positive
 * value will determine the minimum airspeed which will still be fused. Set to about 90% of the vehicles stall speed.
 * Both airspeed fusion and sideslip fusion must be active for the EKF to continue navigating after loss of GPS.
 * Use EKF2_FUSE_BETA to activate sideslip fusion.
@@ -1122,6 +1128,7 @@ PARAM_DEFINE_FLOAT(EKF2_EVV_GATE, 3.0f);
 
 /**
  * Gate size for vision position fusion
+ *
  * Sets the number of standard deviations used by the innovation consistency test.
  * @group EKF2
  * @min 1.0
@@ -1132,7 +1139,8 @@ PARAM_DEFINE_FLOAT(EKF2_EVP_GATE, 5.0f);
 
 /**
  * Specific drag force observation noise variance used by the multi-rotor specific drag force model.
- * Increasing it makes the multi-rotor wind estimates adjust more slowly.
+ *
+ * Increasing this makes the multi-rotor wind estimates adjust more slowly.
  *
  * @group EKF2
  * @min 0.5
@@ -1144,6 +1152,7 @@ PARAM_DEFINE_FLOAT(EKF2_DRAG_NOISE, 2.5f);
 
 /**
  * X-axis ballistic coefficient used by the multi-rotor specific drag force model.
+ *
  * This should be adjusted to minimise variance of the X-axis drag specific force innovation sequence.
  *
  * @group EKF2
@@ -1156,6 +1165,7 @@ PARAM_DEFINE_FLOAT(EKF2_BCOEF_X, 25.0f);
 
 /**
  * Y-axis ballistic coefficient used by the multi-rotor specific drag force model.
+ *
  * This should be adjusted to minimise variance of the Y-axis drag specific force innovation sequence.
  *
  * @group EKF2
@@ -1179,6 +1189,7 @@ PARAM_DEFINE_FLOAT(EKF2_ASPD_MAX, 20.0f);
 
 /**
  * Static pressure position error coefficient for the positive X axis
+ *
  * This is the ratio of static pressure error to dynamic pressure generated by a positive wind relative velocity along the X body axis.
  * If the baro height estimate rises during forward flight, then this will be a negative number.
  *
@@ -1191,6 +1202,7 @@ PARAM_DEFINE_FLOAT(EKF2_PCOEF_XP, 0.0f);
 
 /**
  * Static pressure position error coefficient for the negative X axis.
+ *
  * This is the ratio of static pressure error to dynamic pressure generated by a negative wind relative velocity along the X body axis.
  * If the baro height estimate rises during backwards flight, then this will be a negative number.
  *
@@ -1203,6 +1215,7 @@ PARAM_DEFINE_FLOAT(EKF2_PCOEF_XN, 0.0f);
 
 /**
  * Pressure position error coefficient for the positive Y axis.
+ *
  * This is the ratio of static pressure error to dynamic pressure generated by a wind relative velocity along the positive Y (RH) body axis.
  * If the baro height estimate rises during sideways flight to the right, then this will be a negative number.
  *
@@ -1215,6 +1228,7 @@ PARAM_DEFINE_FLOAT(EKF2_PCOEF_YP, 0.0f);
 
 /**
  * Pressure position error coefficient for the negative Y axis.
+ *
  * This is the ratio of static pressure error to dynamic pressure generated by a wind relative velocity along the negative Y (LH) body axis.
  * If the baro height estimate rises during sideways flight to the left, then this will be a negative number.
  *
@@ -1227,6 +1241,7 @@ PARAM_DEFINE_FLOAT(EKF2_PCOEF_YN, 0.0f);
 
 /**
  * Static pressure position error coefficient for the Z axis.
+ *
  * This is the ratio of static pressure error to dynamic pressure generated by a wind relative velocity along the Z body axis.
  *
  * @group EKF2
@@ -1237,7 +1252,9 @@ PARAM_DEFINE_FLOAT(EKF2_PCOEF_YN, 0.0f);
 PARAM_DEFINE_FLOAT(EKF2_PCOEF_Z, 0.0f);
 
 /**
- * Accelerometer bias learning limit. The ekf delta velocity bias states will be limited to within a range equivalent to +- of this value.
+ * Accelerometer bias learning limit.
+ *
+ * The ekf delta velocity bias states will be limited to within a range equivalent to +- of this value.
  *
  * @group EKF2
  * @min 0.0
@@ -1249,6 +1266,7 @@ PARAM_DEFINE_FLOAT(EKF2_ABL_LIM, 0.4f);
 
 /**
  * Maximum IMU accel magnitude that allows IMU bias learning.
+ *
  * If the magnitude of the IMU accelerometer vector exceeds this value, the EKF delta velocity state estimation will be inhibited.
  * This reduces the adverse effect of high manoeuvre accelerations and IMU nonlinerity and scale factor errors on the delta velocity bias estimates.
  *
@@ -1262,6 +1280,7 @@ PARAM_DEFINE_FLOAT(EKF2_ABL_ACCLIM, 25.0f);
 
 /**
  * Maximum IMU gyro angular rate magnitude that allows IMU bias learning.
+ *
  * If the magnitude of the IMU angular rate vector exceeds this value, the EKF delta velocity state estimation will be inhibited.
  * This reduces the adverse effect of rapid rotation rates and associated errors on the delta velocity bias estimates.
  *
@@ -1275,6 +1294,7 @@ PARAM_DEFINE_FLOAT(EKF2_ABL_GYRLIM, 3.0f);
 
 /**
  * Time constant used by acceleration and angular rate magnitude checks used to inhibit delta velocity bias learning.
+ *
  * The vector magnitude of angular rate and acceleration used to check if learning should be inhibited has a peak hold filter applied to it with an exponential decay.
  * This parameter controls the time constant of the decay.
  *
@@ -1342,6 +1362,7 @@ PARAM_DEFINE_INT32(EKF2_SYNT_MAG_Z, 0);
 
 /**
  * Default value of true airspeed used in EKF-GSF AHRS calculation.
+ *
  * If no airspeed measurements are avalable, the EKF-GSF AHRS calculation will assume this value of true airspeed when compensating for centripetal acceleration during turns. Set to zero to disable centripetal acceleration compensation during fixed wing flight modes.
  *
  * @group EKF2

src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c

@@ -321,6 +321,7 @@ PARAM_DEFINE_FLOAT(FW_LND_TLALT, -1.0f);
 
 /**
  * Landing heading hold horizontal distance.
+ *
  * Set to 0 to disable heading hold.
  *
  * @unit m

src/modules/fw_pos_control_l1/runway_takeoff/runway_takeoff_params.c

@@ -62,6 +62,7 @@ PARAM_DEFINE_INT32(RWTO_HDG, 0);
 
 /**
  * Altitude AGL at which we have enough ground clearance to allow some roll.
+ *
  * Until RWTO_NAV_ALT is reached the plane is held level and only
  * rudder is used to keep the heading (see RWTO_HDG). This should be below
  * FW_CLMBOUT_DIFF if FW_CLMBOUT_DIFF > 0.
@@ -77,7 +78,8 @@ PARAM_DEFINE_FLOAT(RWTO_NAV_ALT, 5.0);
 
 /**
  * Max throttle during runway takeoff.
- * (Can be used to test taxi on runway)
+ *
+ * Can be used to test taxi on runway
  *
  * @unit norm
  * @min 0.0
@@ -90,6 +92,7 @@ PARAM_DEFINE_FLOAT(RWTO_MAX_THR, 1.0);
 
 /**
  * Pitch setpoint during taxi / before takeoff airspeed is reached.
+ *
  * A taildragger with steerable wheel might need to pitch up
  * a little to keep its wheel on the ground before airspeed
  * to takeoff is reached.
@@ -105,6 +108,7 @@ PARAM_DEFINE_FLOAT(RWTO_PSP, 0.0);
 
 /**
  * Max pitch during takeoff.
+ *
  * Fixed-wing settings are used if set to 0. Note that there is also a minimum
  * pitch of 10 degrees during takeoff, so this must be larger if set.
  *
@@ -119,6 +123,7 @@ PARAM_DEFINE_FLOAT(RWTO_MAX_PITCH, 20.0);
 
 /**
  * Max roll during climbout.
+ *
  * Roll is limited during climbout to ensure enough lift and prevents aggressive
  * navigation before we're on a safe height.
  *
@@ -132,7 +137,8 @@ PARAM_DEFINE_FLOAT(RWTO_MAX_PITCH, 20.0);
 PARAM_DEFINE_FLOAT(RWTO_MAX_ROLL, 25.0);
 
 /**
- * Min. airspeed scaling factor for takeoff.
+ * Min airspeed scaling factor for takeoff.
+ *
  * Pitch up will be commanded when the following airspeed is reached:
  * FW_AIRSPD_MIN * RWTO_AIRSPD_SCL
  *

src/modules/local_position_estimator/params.c

@@ -175,6 +175,7 @@ PARAM_DEFINE_FLOAT(LPE_GPS_Z, 3.0f);
 
 /**
  * GPS xy velocity standard deviation.
+ *
  * EPV used if greater than this value.
  *
  * @group Local Position Estimator
@@ -316,6 +317,7 @@ PARAM_DEFINE_FLOAT(LPE_PN_T, 0.001f);
 
 /**
  * Terrain maximum percent grade, hilly/outdoor (100 = 45 deg), flat/Indoor (0 = 0 deg)
+ *
  * Used to calculate increased terrain random walk nosie due to movement.
  *
  * @group Local Position Estimator
@@ -339,7 +341,8 @@ PARAM_DEFINE_FLOAT(LPE_FGYRO_HP, 0.001f);
 
 /**
  * Enable publishing of a fake global position (e.g for AUTO missions using Optical Flow)
- * by initializing the estimator to the LPE_LAT/LON parameters when global information is unavailable
+ *
+ * By initializing the estimator to the LPE_LAT/LON parameters when global information is unavailable
  *
  * @group Local Position Estimator
  * @min 0

src/modules/mc_att_control/mc_att_control_params.c

@@ -148,6 +148,7 @@ PARAM_DEFINE_FLOAT(MC_YAWRATE_MAX, 200.0f);
 
 /**
  * Manual tilt input filter time constant
+ *
  * Setting this parameter to 0 disables the filter
  *
  * @unit s

src/modules/mc_pos_control/mc_pos_control_params.c

@@ -299,6 +299,7 @@ PARAM_DEFINE_FLOAT(MPC_XY_ERR_MAX, 2.0f);
 
 /**
  * Maximum horizontal velocity setpoint for manual controlled mode
+ *
  * If velocity setpoint larger than MPC_XY_VEL_MAX is set, then
  * the setpoint will be capped to MPC_XY_VEL_MAX
  *
@@ -364,6 +365,7 @@ PARAM_DEFINE_FLOAT(MPC_LAND_SPEED, 0.7f);
 
 /**
  * Maximum horizontal position mode velocity when close to ground/home altitude
+ *
  * Set the value higher than the otherwise expected maximum to disable any slowdown.
  *
  * @unit m/s
@@ -423,6 +425,7 @@ PARAM_DEFINE_FLOAT(MPC_MAN_Y_MAX, 150.0f);
 
 /**
  * Manual yaw rate input filter time constant
+ *
  * Setting this parameter to 0 disables the filter
  *
  * @unit s

src/modules/mc_rate_control/mc_rate_control_params.c

@@ -283,6 +283,7 @@ PARAM_DEFINE_FLOAT(MC_YAWRATE_K, 1.0f);
 
 /**
  * Max acro roll rate
+ *
  * default: 2 turns per second
  *
  * @unit deg/s
@@ -296,6 +297,7 @@ PARAM_DEFINE_FLOAT(MC_ACRO_R_MAX, 720.0f);
 
 /**
  * Max acro pitch rate
+ *
  * default: 2 turns per second
  *
  * @unit deg/s
@@ -309,6 +311,7 @@ PARAM_DEFINE_FLOAT(MC_ACRO_P_MAX, 720.0f);
 
 /**
  * Max acro yaw rate
+ *
  * default 1.5 turns per second
  *
  * @unit deg/s

src/modules/navigator/follow_target_params.c

@@ -78,6 +78,7 @@ PARAM_DEFINE_INT32(NAV_FT_FS, 1);
 
 /**
  * Dynamic filtering algorithm responsiveness to target movement
+ *
  * lower numbers increase the responsiveness to changing long lat
  * but also ignore less noise
  *

src/modules/rover_pos_control/rover_pos_control_params.c

@@ -262,6 +262,7 @@ PARAM_DEFINE_FLOAT(GND_SPEED_MAX, 10.0f);
 
 /**
  * Maximum turn angle for Ackerman steering.
+ *
  * At a control output of 0, the steering wheels are at 0 radians.
  * At a control output of 1, the steering wheels are at GND_MAX_ANG radians.
  *

src/modules/sensors/sensor_params_flow.c

@@ -87,6 +87,7 @@ PARAM_DEFINE_FLOAT(SENS_FLOW_MAXHGT, 3.0f);
 
 /**
  * Magnitude of maximum angular flow rate reliably measurable by the optical flow sensor.
+ *
  * Optical flow data will not fused by the estimators if the magnitude of the flow rate exceeds this value and
  * control loops will be instructed to limit ground speed such that the flow rate produced by movement over ground
  * is less than 50% of this value.

src/modules/sensors/sensor_params_mag0.c

@@ -195,9 +195,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG0_YODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG0_ZODIAG, 0.0f);
 
 /**
+* X Axis throttle compensation for Mag 0
+*
 * Coefficient describing linear relationship between
 * X component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -207,9 +209,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG0_ZODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG0_XCOMP, 0.0f);
 
 /**
+* Y Axis throttle compensation for Mag 0
+*
 * Coefficient describing linear relationship between
 * Y component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -219,9 +223,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG0_XCOMP, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG0_YCOMP, 0.0f);
 
 /**
+* Z Axis throttle compensation for Mag 0
+*
 * Coefficient describing linear relationship between
 * Z component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *

src/modules/sensors/sensor_params_mag1.c

@@ -195,9 +195,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG1_YODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG1_ZODIAG, 0.0f);
 
 /**
+* X Axis throttle compensation for Mag 1
+*
 * Coefficient describing linear relationship between
 * X component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -207,9 +209,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG1_ZODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG1_XCOMP, 0.0f);
 
 /**
+* Y Axis throttle compensation for Mag 1
+*
 * Coefficient describing linear relationship between
 * Y component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -219,9 +223,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG1_XCOMP, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG1_YCOMP, 0.0f);
 
 /**
+* Z Axis throttle compensation for Mag 1
+*
 * Coefficient describing linear relationship between
 * Z component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *

src/modules/sensors/sensor_params_mag2.c

@@ -195,9 +195,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG2_YODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG2_ZODIAG, 0.0f);
 
 /**
+* X Axis throttle compensation for Mag 2
+*
 * Coefficient describing linear relationship between
 * X component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -207,9 +209,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG2_ZODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG2_XCOMP, 0.0f);
 
 /**
+* Y Axis throttle compensation for Mag 2
+*
 * Coefficient describing linear relationship between
 * Y component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -219,9 +223,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG2_XCOMP, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG2_YCOMP, 0.0f);
 
 /**
+* Z Axis throttle compensation for Mag 2
+*
 * Coefficient describing linear relationship between
 * Z component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *

src/modules/sensors/sensor_params_mag3.c

@@ -195,9 +195,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG3_YODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG3_ZODIAG, 0.0f);
 
 /**
+* X Axis throttle compensation for Mag 3
+*
 * Coefficient describing linear relationship between
 * X component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -207,9 +209,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG3_ZODIAG, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG3_XCOMP, 0.0f);
 
 /**
+* Y Axis throttle compensation for Mag 3
+*
 * Coefficient describing linear relationship between
 * Y component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *
@@ -219,9 +223,11 @@ PARAM_DEFINE_FLOAT(CAL_MAG3_XCOMP, 0.0f);
 PARAM_DEFINE_FLOAT(CAL_MAG3_YCOMP, 0.0f);
 
 /**
+* Z Axis throttle compensation for Mag 3
+*
 * Coefficient describing linear relationship between
 * Z component of magnetometer in body frame axis
-* and either current or throttle depending on value of CAL_MAG_COMP_TYP
+* and either current or throttle depending on value of CAL_MAG_COMP_TYP.
 * Unit for throttle-based compensation is [G] and
 * for current-based compensation [G/kA]
 *

src/modules/sih/sih_params.c

@@ -418,6 +418,7 @@ PARAM_DEFINE_FLOAT(SIH_DISTSNSR_MAX, 100.0f);
 
 /**
  * if >= 0 the distance sensor measures will be overrided by this value
+ *
  * Absolute value superior to 10000 will disable distance sensor
  *
  * @unit m

src/modules/simulator/battery_simulator/battery_simulator_params.c

@@ -44,8 +44,9 @@
 PARAM_DEFINE_FLOAT(SIM_BAT_DRAIN, 60);
 
 /**
- * Simulator Battery minimal percentage. Can be used to alter
- * the battery level during SITL- or HITL-simulation on the fly.
+ * Simulator Battery minimal percentage.
+ *
+ * Can be used to alter the battery level during SITL- or HITL-simulation on the fly.
  * Particularly useful for testing different low-battery behaviour.
  *
  * @min 0

src/modules/vmount/vmount_params.c

@@ -94,6 +94,7 @@ PARAM_DEFINE_INT32(MNT_MAV_COMPID, 154);
 
 /**
 * Mixer value for selecting normal mode
+*
 * if required by the gimbal (only in AUX output mode)
 *
 * @min -1.0
@@ -105,6 +106,7 @@ PARAM_DEFINE_FLOAT(MNT_OB_NORM_MODE, -1.0f);
 
 /**
 * Mixer value for selecting a locking mode
+*
 * if required for the gimbal (only in AUX output mode)
 *
 * @min -1.0
@@ -163,9 +165,11 @@ PARAM_DEFINE_INT32(MNT_MAN_PITCH, 0);
 PARAM_DEFINE_INT32(MNT_MAN_YAW, 0);
 
 /**
-* Stabilize the mount (set to true for servo gimbal, false for passthrough).
-* (This is required for a gimbal which is not capable of stabilizing itself
-* and relies on the IMU's attitude estimation.)
+* Stabilize the mount
+*
+* Set to true for servo gimbal, false for passthrough.
+* This is required for a gimbal which is not capable of stabilizing itself
+* and relies on the IMU's attitude estimation.
 *
 * @value 0 Disable
 * @value 1 Stabilize all axis
@@ -238,6 +242,7 @@ PARAM_DEFINE_FLOAT(MNT_OFF_YAW, 0.0f);
 
 /**
  * Angular pitch rate for manual input in degrees/second.
+ *
  * Full stick input [-1..1] translats to [-pitch rate..pitch rate].
  *
  * @min 1.0
@@ -248,6 +253,7 @@ PARAM_DEFINE_FLOAT(MNT_RATE_PITCH, 30.0f);
 
 /**
  * Angular yaw rate for manual input in degrees/second.
+ *
  * Full stick input [-1..1] translats to [-yaw rate..yaw rate].
  *
  * @min 1.0

src/modules/vtol_att_control/standard_params.c

@@ -42,6 +42,7 @@
 
 /**
  * Enable/disable usage of fixed-wing actuators in hover to generate forward force (instead of pitching down).
+ *
  * This technique can be used to avoid the plane having to pitch down in order to move forward.
  * This prevents large, negative lift values being created when facing strong winds.
  * Fixed-wing forward actuators refers to puller/pusher (standard VTOL), or forward-tilt (tiltrotor VTOL).
@@ -62,7 +63,8 @@ PARAM_DEFINE_INT32(VT_FWD_THRUST_EN, 0);
 
 /**
  * Maximum allowed angle the vehicle is allowed to pitch down to generate forward force
- * when fixed-wing forward actuation is active (seeVT_FW_TRHUST_EN).
+ *
+ * When fixed-wing forward actuation is active (see VT_FW_TRHUST_EN).
  * If demanded down pitch exceeds this limmit, the fixed-wing forward actuators are used instead.
  *
  * @min 0.0
@@ -98,6 +100,7 @@ PARAM_DEFINE_FLOAT(VT_B_TRANS_RAMP, 3.0f);
 
 /**
  * Output on airbrakes channel during back transition
+ *
  * Used for airbrakes or with ESCs that have reverse thrust enabled on a seperate channel
  * Airbrakes need to be enables for your selected model/mixer
  *
@@ -112,6 +115,7 @@ PARAM_DEFINE_FLOAT(VT_B_REV_OUT, 0.0f);
 
 /**
  * Delay in seconds before applying back transition throttle
+ *
  * Set this to a value greater than 0 to give the motor time to spin down.
  *
  * unit s
@@ -124,6 +128,8 @@ PARAM_DEFINE_FLOAT(VT_B_REV_OUT, 0.0f);
 PARAM_DEFINE_FLOAT(VT_B_REV_DEL, 0.0f);
 
 /**
+ * Pusher throttle ramp up window
+ *
  * Defines the time window during which the pusher throttle will be ramped up linearly to VT_F_TRANS_THR during a transition
  * to fixed wing mode. Zero or negative values will produce an instant throttle rise to VT_F_TRANS_THR.
  *

src/modules/vtol_att_control/vtol_att_control_params.c

@@ -116,7 +116,9 @@ PARAM_DEFINE_FLOAT(VT_B_TRANS_DUR, 4.0f);
 
 /**
  * Target throttle value for the transition to fixed wing flight.
+ *
  * standard vtol: pusher
+ *
  * tailsitter, tiltrotor: main throttle
  *
  * @min 0.0
@@ -129,7 +131,9 @@ PARAM_DEFINE_FLOAT(VT_F_TRANS_THR, 1.0f);
 
 /**
  * Target throttle value for the transition to hover flight.
+ *
  * standard vtol: pusher
+ *
  * tailsitter, tiltrotor: main throttle
  *
  * Note for standard vtol: