Implements a better method of determining when to switch from velocity to altitude control to keep height limit from being exceeded.
This method removes the overshoot and transients in height caused by the switching of the previous algorithm.
The correction for stopping distance applied to the maximum altitude limiter uses the vertical velocity estimate and gives the same offset for both positive (down) and negative (up) velocity.
This calculation has been corrected and simplified and variable names changes to make the functionality clearer.
Since assertions lead to crashes, we need better failure handling. In all
the cases in this patch, the assert is not required.
All the ones with the task id should be replaced with the module base
class.
Ah yes, and this reduces flash space, since the ASSERT macro will expand to
a printf that contains the source file name.
With the new position control architercture manual mode and
potition mode run through the same logic and as a result
it had a throttle thershold for smooth takeoff also in
manual mode. This is fixed by by ignoring the threshold for
any mode which doesn't control the climb rate.
individual commit for the indentation because otherwise
the diff gets unreadable. this indentation is made because
afterwards the entire legacy position control functionality
is in an else case.
- On initialization _v_att_sp got filled with zeros
leaving invalid quaternions
- While not armed mc_pos_control did not publish any
attitude setpoint which makes no sense
- The attitude control just uses the data in _v_att_sp
if it was (ever) updated or not
This causes severe oscillations in aggressive maneuvers with high tilt
angles. It's an issue on VTOL's too, but the modification is specifically
for VTOL's and VTOL's typically do not fly with such high tilt angles
(>50 deg).
See also: https://github.com/PX4/Firmware/issues/7949
Stops vertical velocity bias errors preventing the vehicle from landing.
Use of the vertical derivative is blended in so that for zero vertical velocity set point, the local_position.vz is used and when the magnitude of the vertical velocity setpoint exceeds the landing speed, the local_position.z_deriv is used.
This change limits all mission items to the maximum flight altitude. The mission will still be executed and flown,
but the vehicle will never exceed the mission altitude. This ensures the vehicle can always reach the mission
items. Wether or not the entire mission should be rejected if it falls outside of the fenced area is enforced
in the mission feasibility checker function.
This commit is an attempt to fix a race condition happening on takeoff
between the land detector and the multicopter position controller.
Previously, an auto-takeoff leads to the following events:
1. A takeoff setpoint is given.
2. The thrust setpoint spikes because we don't enter smooth takeoff yet.
3. The land detector detects a takeoff because of the high thrust.
4. The position controller sees the landed state transition and
initiates the smooth takeoff. Thrust goes back down.
5. Depending on control gains the takeoff is successful or fails
if the smoothing takes too long which causes thrust to be too low, so
the land detector detects land again.
The two obvious problems with this are:
- The intermittent spike.
- The failed takeoff because of the smoothing leads to a delay..
With this change, the logic for a takeoff detection is moved from the
land detector to the position controller.
The events are now:
1. A takeoff setpoint is given.
2. The position controller detects the takeoff setpoint and initiates
the smooth takeoff.
3. As thrust ramps up, the land detector detects the take off.
In the same way, we now detect the intent to takeoff in manual,
altitude, control, position control in the position controller instead
of in the land detector.
Martina