Fixed-wing Attitude Controller for VTOL Aircraft

Hi everyone,

I have some questions on the Fixed-wing Attitude Controller.

Question 1:
Where could I find P in a script and the parameter definition in https://dev.px4.io/v1.9.0/en/advanced/parameter_reference.html?

Question 2:
What are the equations in the “Turn coordination block”?

Question 3:
Could somebody spell out the Jacobian Matrix?

Hi, here you go:

  1. The P controller has separate gains for Roll and Pitch, and they are actually inverted (time constants): FW_R_TC and FW_P_TC

  2. It’s about how much the vehicle need to yaw to achieve a coordinated turn. This is the most common formula thereimage
    In PX4 there is also taken the pitch into account for this, see https://github.com/PX4/ecl/blob/9b4b24ee71902c6a4289170e8fb1ca3306c1d9c4/attitude_fw/ecl_yaw_controller.cpp#L105

  3. image

Feel free to ask if stuff is still unclear!

Thank you very much for your response.
I have another question about the Fixed-Wing Mixer block in the diagram above.
I’m trying to find the equations used in the Mixer block. Would you be able to spell out the equations in the block?

See here. For a Fw vehicle the mixer is quite straight forward, eg
elevator_deflection = trim + pitching_rate_sp * scale
Did that help already?

Thank you very much for your help.
I’m looking for the codes for the expression below in a script.
elevator_deflection = trim + pitching_rate_sp * scale
Could you point out the location of the codes?

This is the mixer for fixed-wing vehicles (it’s called simple mixer because all axis are decoupled, not because the code itself is very simple ^^)

And this is en example of a configuration file for a standard FW vehicle: