So I've been battling to establish a simple method in mimicking rc control inputs during a sustained or coordinated turn of the aircraft.
This is quite important as it's not the same as stabilizing controller which reacts to dynamic events while having a static reference.
A coordinated turn has a dynamic reference which is coupled to the turn rate experienced which directly related to the speed and the roll command inputs.
But since the turn rate of the aircraft can be extracted from the gyroscope measurements, it can be stated that post processing of these signals (using a low pass filter) should give an indication of whether such method can be used alongside a stabilizing controller.
This is such that once a coordinated turn can be achieved even in adverse weather, waypoint tracking is closer to being realised.
Amendment 15/1/2015:
It was found after careful analysis of the flight dynamics of a simple aircraft that gyroscope measurements was not a fool-proof way of computing the turn rate as the signal to noise ratio in a low turn would destabilize the control system. It was also found that the rudder to elevator mixing needed during a coordinated turn is independent of flight path speed which in turn allows a direct input into the elevator trim value based on a roll command. The code was uploaded on the chip and benched tested. Only a flight test could confirm the final values used.
This is quite important as it's not the same as stabilizing controller which reacts to dynamic events while having a static reference.
A coordinated turn has a dynamic reference which is coupled to the turn rate experienced which directly related to the speed and the roll command inputs.
But since the turn rate of the aircraft can be extracted from the gyroscope measurements, it can be stated that post processing of these signals (using a low pass filter) should give an indication of whether such method can be used alongside a stabilizing controller.
This is such that once a coordinated turn can be achieved even in adverse weather, waypoint tracking is closer to being realised.
Amendment 15/1/2015:
It was found after careful analysis of the flight dynamics of a simple aircraft that gyroscope measurements was not a fool-proof way of computing the turn rate as the signal to noise ratio in a low turn would destabilize the control system. It was also found that the rudder to elevator mixing needed during a coordinated turn is independent of flight path speed which in turn allows a direct input into the elevator trim value based on a roll command. The code was uploaded on the chip and benched tested. Only a flight test could confirm the final values used.
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