<airframeid="20000"maintainer="Julian Oes <julian@oes.ch> This startup can be used on Pixhawk/Pixfalcon/Pixracer for the passthrough of RC input and PWM output."name="Passthrough mode for Snapdragon">
<class>Tool</class>
<maintainer>Julian Oes <julian@oes.ch>
This startup can be used on Pixhawk/Pixfalcon/Pixracer for the
passthrough of RC input and PWM output.</maintainer>
<short_desc>Circuit breaker for airspeed sensor</short_desc>
<long_desc>Setting this parameter to 162128 will disable the check for an airspeed sensor. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -452,7 +452,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for disabling buzzer</short_desc>
<long_desc>Setting this parameter to 782097 will disable the buzzer audio notification. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -460,7 +460,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for engine failure detection</short_desc>
<long_desc>Setting this parameter to 284953 will disable the engine failure detection. If the aircraft is in engine failure mode the engine failure flag will be set to healthy WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -468,7 +468,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for flight termination</short_desc>
<long_desc>Setting this parameter to 121212 will disable the flight termination action. --> The IO driver will not do flight termination if requested by the FMU WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -476,7 +476,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for GPS failure detection</short_desc>
<long_desc>Setting this parameter to 240024 will disable the GPS failure detection. If this check is enabled, then the sensor check will fail if the GPS module is missing. It will also check for excessive signal noise on the GPS receiver and warn the user if detected. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -484,7 +484,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for rate controller output</short_desc>
<long_desc>Setting this parameter to 140253 will disable the rate controller uORB publication. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -500,7 +500,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for power supply check</short_desc>
<long_desc>Setting this parameter to 894281 will disable the power valid checks in the commander. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -508,7 +508,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for USB link check</short_desc>
<long_desc>Setting this parameter to 197848 will disable the USB connected checks in the commander. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -516,7 +516,7 @@ Set to 2 to use heading from motion capture</short_desc>
<short_desc>Circuit breaker for position error check</short_desc>
<long_desc>Setting this parameter to 201607 will disable the position and velocity accuracy checks in the commander. WARNING: ENABLING THIS CIRCUIT BREAKER IS AT OWN RISK</long_desc>
<min>0</min>
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@@ -702,7 +702,7 @@ Note: ekf2 will limit the delta velocity bias estimate magnitude to be less than
<long_desc>This number is incremented automatically after every flight on disarming in order to remember the next flight UUID. The first flight is 0.</long_desc>
<min>0</min>
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@@ -1434,12 +1434,12 @@ Increasing it makes the multi-rotor wind estimates adjust more slowly</short_des
<short_desc>Learned value of magnetometer X axis bias.
This is the amount of X-axis magnetometer bias learned by the EKF and saved from the last flight. It must be set to zero if the ground based magnetometer calibration is repeated</short_desc>
<min>-0.5</min>
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@@ -1449,7 +1449,7 @@ This is the amount of X-axis magnetometer bias learned by the EKF and saved from
<short_desc>Learned value of magnetometer Y axis bias.
This is the amount of Y-axis magnetometer bias learned by the EKF and saved from the last flight. It must be set to zero if the ground based magnetometer calibration is repeated</short_desc>
<min>-0.5</min>
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@@ -1459,7 +1459,7 @@ This is the amount of Y-axis magnetometer bias learned by the EKF and saved from
<short_desc>Learned value of magnetometer Z axis bias.
This is the amount of Z-axis magnetometer bias learned by the EKF and saved from the last flight. It must be set to zero if the ground based magnetometer calibration is repeated</short_desc>
<min>-0.5</min>
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@@ -3198,13 +3198,13 @@ but also ignore less noise</short_desc>
<short_desc>Total flight time in microseconds</short_desc>
<long_desc>Total flight time of this autopilot. Higher 32 bits of the value. Flight time in microseconds = (LND_FLIGHT_T_HI << 32) | LND_FLIGHT_T_LO.</long_desc>
<short_desc>Total flight time in microseconds</short_desc>
<long_desc>Total flight time of this autopilot. Lower 32 bits of the value. Flight time in microseconds = (LND_FLIGHT_T_HI << 32) | LND_FLIGHT_T_LO.</long_desc>
<min>0</min>
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@@ -3603,6 +3603,46 @@ Used to calculate increased terrain random walk nosie due to movement</short_des