TY - GEN
T1 - Design of an aircraft pitch control experimental test bench
AU - Villarreal-Valderrama, F.
AU - Takano De La Cruz, L.
AU - Alvarez, U.
AU - Amezquita-Brooks, L.
AU - Liceaga-Castro, E.
N1 - Publisher Copyright:
© 2018 IEEE.
PY - 2018/7/2
Y1 - 2018/7/2
N2 - Aircraft pitch control is fundamental to improve the performance of unmanned aerial vehicles. This paper presents the instrumentation and modeling process of an experimental platform for aircraft pitch control. A complementary filter is designed to improve the angular position estimation based on inertial measurements. The platform was used for the implementation of different controllers in a wind tunnel facility: a Ziegler-Nichols PID and a loop shaping compensator. The test bench allows the implementation of typical continuous-time linear and non-linear controllers. The plant identification process is designed to compute the parameters that meet the open loop time domain characteristics and the closed loop frequency characteristics. The time delay in the control loop is computed through an experiment and used for the loop shaping design process. The controllers are implemented and compared according to its time domain performance. The best suited control is then analyzed in terms of perturbation rejection and more demanding tests. The article shows that the resulting test bench is suitable for the experimental evaluation of typical pitch angle control strategies. Due to the integration with a wind tunnel, the test bench is able to simulate a wide range of flight conditions. Including extreme conditions that would not be safe in real flight experiments.
AB - Aircraft pitch control is fundamental to improve the performance of unmanned aerial vehicles. This paper presents the instrumentation and modeling process of an experimental platform for aircraft pitch control. A complementary filter is designed to improve the angular position estimation based on inertial measurements. The platform was used for the implementation of different controllers in a wind tunnel facility: a Ziegler-Nichols PID and a loop shaping compensator. The test bench allows the implementation of typical continuous-time linear and non-linear controllers. The plant identification process is designed to compute the parameters that meet the open loop time domain characteristics and the closed loop frequency characteristics. The time delay in the control loop is computed through an experiment and used for the loop shaping design process. The controllers are implemented and compared according to its time domain performance. The best suited control is then analyzed in terms of perturbation rejection and more demanding tests. The article shows that the resulting test bench is suitable for the experimental evaluation of typical pitch angle control strategies. Due to the integration with a wind tunnel, the test bench is able to simulate a wide range of flight conditions. Including extreme conditions that would not be safe in real flight experiments.
KW - Aircraft pitch control
KW - Control performance evaluation
KW - Experimental control implementation
KW - Experimental test bench design
UR - http://www.scopus.com/inward/record.url?scp=85063919813&partnerID=8YFLogxK
U2 - 10.1109/ROPEC.2018.8661430
DO - 10.1109/ROPEC.2018.8661430
M3 - Contribución a la conferencia
AN - SCOPUS:85063919813
T3 - 2018 IEEE International Autumn Meeting on Power, Electronics and Computing, ROPEC 2018
BT - 2018 IEEE International Autumn Meeting on Power, Electronics and Computing, ROPEC 2018
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2018 IEEE International Autumn Meeting on Power, Electronics and Computing, ROPEC 2018
Y2 - 14 November 2018 through 16 November 2018
ER -