US 12,420,910 B2
Trim tab control
Onur Albostan, Kahramankazan/Ankara (TR)
Assigned to TUSAS- TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI, Kahramankazan/Ankara (TR)
Appl. No. 18/694,368
Filed by TUSAS-TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI, Kahramankazan/Ankara (TR)
PCT Filed Jun. 28, 2022, PCT No. PCT/TR2022/050674
§ 371(c)(1), (2) Date Mar. 21, 2024,
PCT Pub. No. WO2023/055320, PCT Pub. Date Apr. 6, 2023.
Claims priority of application No. 2021/015234 (TR), filed on Sep. 29, 2021.
Prior Publication US 2024/0400196 A1, Dec. 5, 2024
Int. Cl. B64C 13/18 (2006.01)
CPC B64C 13/18 (2013.01) 9 Claims
OG exemplary drawing
 
1. A trim tab control (1) comprising:
a sensor unit (2) located on an air vehicle which enables the measurement of air speed, engine torque and lateral acceleration of the air vehicle;
a flight control computer (3) s configured to enable a first adjustment command (F) to be generated using the air speed and engine torque data measured by the sensor unit (2);
a controller (4) wherein gain coefficient (K) of the controller (4) is determined by the flight control computer (3) based on the air speed measured by the sensor unit (2);
a rudder (5) located on the air vehicle;
a secondary trim tab (6) located on the rudder (5) which moves in a rotatable manner according to the final adjustment command (TC) transmitted;
an actuator (7) that enables the secondary trim tab (6) to be moved by rotating around the axis to which it is attached to the rudder (5); and
wherein the controller (4) run in the flight control computer (3), which is configured to enable a second adjustment command(S) to be generated using the lateral acceleration data, wherein the flight control computer (3) collects the first adjustment command (F) and the second adjustment command(S) generated by the controller (4), such that it generates a final adjustment command (TC), and wherein the flight control computer (3) is configured to detect a change in speed of the air vehicle according to the amount of change in the value of the first adjustment command (F), and enable determination of the gain coefficient (K) of the second adjustment command(S) generated by the controller (4) to prevent reverse-slip by the air vehicle according to the detected change in the speed and the air speed value measured by the sensor unit (2).