diff --git a/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml b/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml index f2cf72a..012ddc2 100644 --- a/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml +++ b/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml @@ -763,22 +763,6 @@ Distance based, on command (Survey mode) - - Camera trigger pin - Selects which FMU pin is used (range: AUX1-AUX8 on Pixhawk controllers with an I/O board, MAIN1-MAIN8 on controllers without an I/O board). The PWM interface takes two pins per camera, while relay triggers on every pin individually. Example: Value 56 would trigger on pins 5 and 6. For GPIO mode Pin 6 will be triggered followed by 5. With a value of 65 pin 5 will be triggered followed by 6. Pins may be non contiguous. I.E. 16 or 61. In GPIO mode the delay pin to pin is < .2 uS. - 1 - 12345678 - 0 - true - - - Camera trigger pin extended - This Bit mask selects which FMU pin is used (range: AUX9-AUX32) If the value is not 0 it takes precedence over TRIG_PINS. If bits above 8 are set that value is used as the selector for trigger pins. greater then 8. 0x00000300 Would be Pins 9,10. If the value is - 0 - 2147483647 - 0 - true - Camera trigger polarity This parameter sets the polarity of the trigger (0 = active low, 1 = active high ) @@ -4634,14 +4618,6 @@ Roll/Pitch/Yaw - - Motor Ordering - Determines the motor ordering. This can be used for example in combination with a 4-in-1 ESC that assumes a motor ordering which is different from PX4. ONLY supported for Quads. When changing this, make sure to test the motor response without props first. - - PX4 - Betaflight / Cleanflight - - @@ -8933,11 +8909,6 @@ - - Barometer offset in meters - Absolute value superior to 10000 will disable barometer - m - distance sensor maximum range 0.0 @@ -8959,11 +8930,6 @@ Absolute value superior to 10000 will disable distance sensor m - - Number of GPS satellites used - 0 - 50 - Vehicle inertia about X axis The inertia is a 3 by 3 symmetric matrix. It represents the difficulty of the vehicle to modify its angular rate. @@ -9048,33 +9014,6 @@ 1800000000 deg*1e7 - - North magnetic field at the initial location - This value represents the North magnetic field at the initial location. A magnetic field calculator can be found on the NOAA website Note, the values need to be converted from nano Tesla to Gauss LAT0, LON0, H0, MU_X, MU_Y, and MU_Z should ideally be consistent among each others to represent a physical ground location on Earth. - -1.0 - 1.0 - gauss - 2 - 0.001 - - - East magnetic field at the initial location - This value represents the East magnetic field at the initial location. A magnetic field calculator can be found on the NOAA website Note, the values need to be converted from nano Tesla to Gauss LAT0, LON0, H0, MU_X, MU_Y, and MU_Z should ideally be consistent among each others to represent a physical ground location on Earth. - -1.0 - 1.0 - gauss - 2 - 0.001 - - - Down magnetic field at the initial location - This value represents the Down magnetic field at the initial location. A magnetic field calculator can be found on the NOAA website Note, the values need to be converted from nano Tesla to Gauss LAT0, LON0, H0, MU_X, MU_Y, and MU_Z should ideally be consistent among each others to represent a physical ground location on Earth. - -1.0 - 1.0 - gauss - 2 - 0.001 - Pitch arm length This is the arm length generating the pitching moment This value can be measured with a ruler. This corresponds to half the distance between the front and rear motors. @@ -9091,21 +9030,6 @@ 2 0.05 - - magnetometer X offset in Gauss - Absolute value superior to 10000 will disable magnetometer - gauss - - - magnetometer Y offset in Gauss - Absolute value superior to 10000 will disable magnetometer - gauss - - - magnetometer Z offset in Gauss - Absolute value superior to 10000 will disable magnetometer - gauss - Vehicle mass This value can be measured by weighting the quad on a scale. @@ -9238,11 +9162,6 @@ Temperature calibration for each sensor will ignore data if the temperature is lower than the value set by SYS_CAL_TMIN. celcius - - Enable Dynamic Control Allocation - If disabled, the existing mixing implementation is used. If enabled, dynamic control allocation with runtime configuration of the mixing and output functions is used. - true - Dataman storage backend true @@ -9311,7 +9230,7 @@ Enable stack checking - + Set usage of IO board Can be used to use a configure the use of the IO board. true @@ -10139,16 +10058,25 @@ 20000 1000000 - - Enable RTCM pub/sub - 1 - UAVCAN Node ID Read the specs at http://uavcan.org to learn more about Node ID. 1 125 + + Enable MovingBaselineData publication + true + + + Enable MovingBaselineData subscription + 1 + true + + + Enable RTCM subscription + true + CAN built-in bus termination 1 @@ -10173,10 +10101,6 @@ Sensors and Actuators (ESCs) Automatic Config - - UAVCAN ESC will spin at idle throttle when armed, even if the mixer outputs zero setpoints - true - UAVCAN ANTI_COLLISION light operating mode This parameter defines the minimum condition under which the system will command the ANTI_COLLISION lights on 0 - Always off 1 - When autopilot is armed 2 - When autopilot is prearmed 3 - Always on @@ -10530,13 +10454,6 @@ 0.0 200.0 - - The channel number of motors that must be turned off in fixed wing mode - 0 - 12345678 - 0 - 1 - QuadChute Max Pitch Maximum pitch angle before QuadChute engages Above this the vehicle will transition back to MC mode and enter failsafe RTL @@ -10573,31 +10490,12 @@ 30.0 s - - Idle speed of VTOL when in multicopter mode - 900 - 2000 - us - 0 - 1 - Minimum pitch angle during hover landing Overrides VT_PITCH_MIN when the vehicle is in LAND mode (hovering). During landing it can be beneficial to allow lower minimum pitch angles as it can avoid the wings generating too much lift and preventing the vehicle from sinking at the desired rate. -10.0 45.0 - - Enable the usage of AUX outputs for hover motors - Set this parameter to true if the vehicle's hover motors are connected to the FMU (AUX) port. Not required for boards that only have a FMU, and no IO. Only applies for standard VTOL and tiltrotor. - - - The channel number of motors which provide lift during hover - 0 - 12345678 - 0 - 1 - Minimum pitch angle during hover Minimum pitch angle during hover flight. If the desired pitch angle is is lower than this value then the fixed-wing forward actuation can be used to compensate for the missing thrust in forward direction (see VT_FW_TRHUST_EN)