From d3d15472ac163e602007769d748aea50a1f1d03c Mon Sep 17 00:00:00 2001 From: PX4BuildBot Date: Wed, 17 Oct 2018 16:54:59 +0000 Subject: [PATCH] Update PX4 Firmware metadata Wed Oct 17 16:54:59 UTC 2018 --- .../PX4/AirframeFactMetaData.xml | 39 +++++++++---------- .../PX4/PX4ParameterFactMetaData.xml | 8 ++-- 2 files changed, 23 insertions(+), 24 deletions(-) diff --git a/src/AutoPilotPlugins/PX4/AirframeFactMetaData.xml b/src/AutoPilotPlugins/PX4/AirframeFactMetaData.xml index b4c1e6efc..d048de005 100644 --- a/src/AutoPilotPlugins/PX4/AirframeFactMetaData.xml +++ b/src/AutoPilotPlugins/PX4/AirframeFactMetaData.xml @@ -535,6 +535,24 @@ feed-through of RC AUX3 channel + + + Plane + Friedrich Beckmann <friedrich.beckmann@hs-augsburg.de> + Plane V-Tail + aileron right + aileron left + v-tail right + v-tail left + throttle + wheel + flaps right + flaps left + feed-through of RC AUX1 channel + feed-through of RC AUX2 channel + feed-through of RC AUX3 channel + + Plane @@ -579,27 +597,6 @@ feed-through of RC AUX3 channel - - - Plane -The Mini Talon does not have a wheel and -no flaps. I leave them here because the mixer -computes also wheel and flap controls. - Friedrich Beckmann <friedrich.beckmann@hs-augsburg.de> - Plane V-Tail - aileron right - aileron left - v-tail right - v-tail left - throttle - wheel - flaps right - flaps left - feed-through of RC AUX1 channel - feed-through of RC AUX2 channel - feed-through of RC AUX3 channel - - Rover diff --git a/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml b/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml index d407fa35f..72ca0682f 100644 --- a/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml +++ b/src/FirmwarePlugin/PX4/PX4ParameterFactMetaData.xml @@ -1033,9 +1033,9 @@ This parameter controls the time constant of the decay Integer bitmask controlling data fusion and aiding methods - Set bits in the following positions to enable: 0 : Set to true to use GPS data if available 1 : Set to true to use optical flow data if available 2 : Set to true to inhibit IMU bias estimation 3 : Set to true to enable vision position fusion 4 : Set to true to enable vision yaw fusion 5 : Set to true to enable multi-rotor drag specific force fusion 6 : set to true if the EV observations are in a non NED reference frame and need to be rotated before being used + Set bits in the following positions to enable: 0 : Set to true to use GPS data if available 1 : Set to true to use optical flow data if available 2 : Set to true to inhibit IMU bias estimation 3 : Set to true to enable vision position fusion 4 : Set to true to enable vision yaw fusion. Cannot be used if bit position 7 is true. 5 : Set to true to enable multi-rotor drag specific force fusion 6 : set to true if the EV observations are in a non NED reference frame and need to be rotated before being used 7 : Set to true to enable GPS yaw fusion. Cannot be used if bit position 4 is true. 0 - 127 + 255 true use GPS @@ -1045,6 +1045,7 @@ This parameter controls the time constant of the decay vision yaw fusion multi-rotor drag fusion rotate external vision + GPS yaw fusion @@ -1458,7 +1459,7 @@ This parameter is used when the magnetometer fusion method is set automatically Type of magnetometer fusion - Integer controlling the type of magnetometer fusion used - magnetic heading or 3-component vector. The fuson of magnetomer data as a three component vector enables vehicle body fixed hard iron errors to be learned, but requires a stable earth field. If set to 'Automatic' magnetic heading fusion is used when on-ground and 3-axis magnetic field fusion in-flight with fallback to magnetic heading fusion if there is insufficient motion to make yaw or magnetic field states observable. If set to 'Magnetic heading' magnetic heading fusion is used at all times If set to '3-axis' 3-axis field fusion is used at all times. If set to 'VTOL custom' the behaviour is the same as 'Automatic', but if fusing airspeed, magnetometer fusion is only allowed to modify the magnetic field states. This can be used by VTOL platforms with large magnetic field disturbances to prevent incorrect bias states being learned during forward flight operation which can adversely affect estimation accuracy after transition to hovering flight. If set to 'MC custom' the behaviour is the same as 'Automatic, but if there are no earth frame position or velocity observations being used, the magnetometer will not be used. This enables vehicles to operate with no GPS in environments where the magnetic field cannot be used to provide a heading reference. Prior to flight, the yaw angle is assumed to be constant if movement tests controlled by the EKF2_MOVE_TEST parameter indicate that the vehicle is static. This allows the vehicle to be placed on the ground to learn the yaw gyro bias prior to flight. + Integer controlling the type of magnetometer fusion used - magnetic heading or 3-component vector. The fuson of magnetomer data as a three component vector enables vehicle body fixed hard iron errors to be learned, but requires a stable earth field. If set to 'Automatic' magnetic heading fusion is used when on-ground and 3-axis magnetic field fusion in-flight with fallback to magnetic heading fusion if there is insufficient motion to make yaw or magnetic field states observable. If set to 'Magnetic heading' magnetic heading fusion is used at all times If set to '3-axis' 3-axis field fusion is used at all times. If set to 'VTOL custom' the behaviour is the same as 'Automatic', but if fusing airspeed, magnetometer fusion is only allowed to modify the magnetic field states. This can be used by VTOL platforms with large magnetic field disturbances to prevent incorrect bias states being learned during forward flight operation which can adversely affect estimation accuracy after transition to hovering flight. If set to 'MC custom' the behaviour is the same as 'Automatic, but if there are no earth frame position or velocity observations being used, the magnetometer will not be used. This enables vehicles to operate with no GPS in environments where the magnetic field cannot be used to provide a heading reference. Prior to flight, the yaw angle is assumed to be constant if movement tests controlled by the EKF2_MOVE_TEST parameter indicate that the vehicle is static. This allows the vehicle to be placed on the ground to learn the yaw gyro bias prior to flight. If set to 'None' the magnetometer will not be used under any circumstance. Other sources of yaw may be used if selected via the EKF2_AID_MASK parameter. true Automatic @@ -1466,6 +1467,7 @@ This parameter is used when the magnetometer fusion method is set automatically 3-axis VTOL customn MC custom + None -- 2.22.0