Aircraft Pitch Control Design using Observer-State Feedback Control

Aircraft Pitch Control Design using Observer-State Feedback Control

Hanum Arrosida, Mohammad Erik Echsony


Pitch is a movement of an aircraft achieved by tilting the elevator control which makes the nose of aircraft ascend or descend. This research will design a control system that controls the slope of the x-axis or pitch with the observer-state feedback to keep the aircraft always in the position setpoint, the stabilization of the pitch angle at the value of 0 radians. The applied controller is tested under three different conditions based on the variation of the gain value of Q and R that will affect the observed gain matrix (L gain) and the matrix state-feedback gain (K gain). The variation with the gain value of Q = 10 and R = 0.1 is the best result of the three kinds of testing performed with the fastest stabilization processing time, that is 7 seconds, to reach a steady state condition and the minimum pitch angle deviation value is 0.08 radians. The use of the observer has a significant influence on the pitch angle deviation of the aircraft. When using the observer, the pitch angle deviation value is 0.08 radians, and 0.2 radians without the observer. The larger result of pitch deviation angle will affect the stability of the aircraft's motion and cause the slope of the movement on the x-axis become greater so that the aircraft is prone to fall.


Pitch control, Aircraft, Observer, State Feedback.

Full Text:



[1] Z. He and W. Xie, “Control of Non-Linear Switched Systems With Average Dwell Time: Interval Observer-Based Framework,” IET Control Theory & Application, Vol. 10, No. 1, Pp. 10–16, Jan. 2016.

[2] A. Tewari, "Advanced Control of Aircraft, Spacecraft and Rockets." Wiley, 2011.

[3] V. V. Klemas, “Coastal and Environmental Remote Sensing from Unmanned Aerial Vehicles: An Overview,” Journal of Coastal Research, Vol. 315, No. 5, Pp. 1260–1267, Sep. 2015.

[4] M. Polas and A. Fekih, “A Multi-Gain Sliding Mode Based Controller For The Pitch Angle Control of A Civil Aircraft,” 2010 42nd Southeastern Symposium on System Theory (SSST 2010), No. 2, Pp. 96–101, Mar. 2010.

[5] X. Liu, Sheng Sun, Pengjie Lan, and Lifu Du, “Dynamic Surface Attack Angle Control For Aircraft Considering Actuator Position Saturation,” in 2016 IEEE Chinese Guidance, Navigation and Control Conference (CGNCC), 2016, Pp. 20–24.

[6] F. T.Johnson, E. T. N, and N. J. Yu, “Thirty years of development and application of CFD at Boeing Commercial Airplanes, Seattle,” Computers & Fluids, Vol. 34, No. 10, Pp. 1115–1151, Dec. 2005.

[7] M. V. Cook, "Flight Dynamics Principles : A Linear Systems Approach To Aircraft Stability And Control." Butterworth-Heinemann, 2013.

[8] X.-J. Li and G.-H. Yang, “Dynamic Observer-Based Robust Control and Fault Detection For Linear Systems,” IET Control Theory & Application, Vol. 6, No. 17, Pp. 2657–2666, Nov. 2012.

[9] D. Xue and N. H. El-Farra, “Output Feedback-Based Event-Triggered Control of Distributed Processes with Communication Constraints,” in 2016 IEEE 55th Conference on Decision and Control (CDC), 2016, Pp. 4296–4301.

[10] K. Ogata, “Modern Control Engineering,” Vol. 17, 2010.


  • There are currently no refbacks.

Referencing Software:

Checked by:

Supervised by:


View My Stats

Creative Commons License Kinetik : Game Technology, Information System, Computer Network, Computing, Electronics, and Control by is licensed under a Creative Commons Attribution-ShareAlike 4.0 International License.