Abstract
The theory of optimal control is concerned with operating a linear dynamic system at a minimum cost. It also provides the best possible performance with respect to given measure of performance index. This paper presents the design of an optimal control law for yaw damper of an aircraft model. This modern controller based on linear quadratic regulator (LQR) technique is stable, robust, and optimized with respect to energy. It is compared and analyzed with classical controller available in the literature. The classical controller uses washout filter which is well known in aircraft control design. The comparative assessment is based on time response specification performance for a yaw control system of an aircraft. The LQR-based controller has effectively taken care of Dutch roll mode which is an area of concern in lateral dynamics of aircraft. The performances of yaw control systems are investigated and analyzed based on common criteria of impulse response in order to identify which control strategy delivers better performance with respect to the desired bank angle and yaw rate. Simulation is carried out for 747 jet aircraft model using MATLAB and Simulink. According to simulation results, LQR controller delivers better performance than classical controller.
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Abbreviations
- x :
-
State-space matrix of aircraft model, [4 × 1]
- u :
-
Input matrix, [2 × 1]; rudder, aileron (radian)
- β, ψ, θ, ϕ:
-
Aircraft states; sideslip angle (radian), yaw rate (rad/sec), roll rate (rad/sec), bank angle (radian)
- y :
-
Output matrix, [2 × 1]; ψ, ϕ
- A, B, C, D :
-
State-space specifications of aircraft model
- J :
-
Performance index/quadratic cost function
- Q, R :
-
Weighting matrices of J
References
Blakelock JH (1990) Automatic control of aircraft and missiles, 2nd ed, A wiley interscience publication
Case study (2011) Design of Yaw damper for 747 Jet aircraft. Mathworks Documentation
Scokaert POM, Rawlings JB (1998) Constrained linear quadratic regulation. IEEE Trans Autom Control 43(8):1163–1169
Triantafyllou MS, Hover FS (2004) Maneuvering and control of marine vehicle. Massachusetts Institute of Technology, Lecture Notes (13.49), 2004
Wahid N, Rahmat MF (2010) Pitch control system using LQR and fuzzy controller. In: Proceedings of IEEE symposium on industrial electronics and applications, 3–5 Oct 2010, pp 389–394
Liu Z, Choukri El Haj Z, Shi H (2010) Control strategy design based on fuzzy logic and LQR for 3-DOF helicopter model. Intelligent control and information processing (ICICIP), pp 262–266
Nasir ANK, Ahmad MA, Rahmat MF (2008) Performance comparison between LQR and PID controller for an inverted pendulum system. In: Proceedings of international conference on power control and optimization, Chiang May, Thailand, 18–20 July
Dinesh Kumar M (2012) Design of modern and classical controllers for navion aircraft pitch control system. In: Proceedings of international conference on computing and control engineering (ICCCE 2012)
Kulczycki EA, Joshi SS, Hess RA (2006) Towards controller design for autonomous airships using SLC and LQR methods. AIAA guidance, navigation and control conference and exhibit, pp 67–78
Wang ZJ, Guo S, Li W (2008) Modeling, simulation and optimal control for an aircraft of aileron-less folding wing. WSEAS Trans Syst Control, 3(10):869–878
Wang ZJ, Li W, Guo S (2008) Lateral control for an aircraft of folding wing. In: Proceedings of 8th WSEAS international conference on simulation, modelling and optimization (SMO ‘08), pp 99–104
Usta MA, Akyazi O, Akpinar AS (2011) Aircraft roll control system using LQR and fuzzy logic controller. In: Proceedings of IEEE international symposium on innovations in intelligent systems and applications (INISTA), pp 223–227
Nair VG, Dileep MV, George VI (2012) Aircraft Yaw control system using LQR and fuzzy logic controller. Int J Comp Appl, 45(9):25–30
Acknowledgment
The authors thank the authorities of BMS Institute of Technology, Reva Institute of Technology and Management, and the Director, R & D Cell, JNTU, Hyderabad, for their encouragements.
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Singh, S., Rama Murthy, T.V. (2014). Design of an Optimal Yaw Damper for 747 Jet Aircraft Model. In: Sridhar, V., Sheshadri, H., Padma, M. (eds) Emerging Research in Electronics, Computer Science and Technology. Lecture Notes in Electrical Engineering, vol 248. Springer, New Delhi. https://doi.org/10.1007/978-81-322-1157-0_81
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DOI: https://doi.org/10.1007/978-81-322-1157-0_81
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