Control para Hexacópteros: Una Comparación de Control por Modo Deslizante y PID
Baldeón J.*; Escorza J.*; Chávez D.*; Camacho O.*,**
· Escuela Politécnica Nacional, Facultad de Ingeniería Eléctrica y Electrónica Quito, Ecuador ( jafet_ec@hotmail.com , jonathan.escorza@gmail.com , danilo.chavez@epn.edu.ec, oscar.camacho@epn.edu.ec ).
** Universidad de Los Andes, Facultad de Ingeniería. Mérida, Venezuela. ocamacho@ula.ve
The objective of this paper is to design and to test the performance of different control strategies for vertical take- off, landing and changes in the three angles with disturbances for a hexacopter. The control strategies to be used are PID and Sliding Mode Control. The Sliding Mode Control can be implemented using a PD controller as the sliding surface. The controllers are tested through simulations. Keywords: Robust control; sliding mode control; hexacopter; performance; PID
Resumen
El objetivo de este artículo es diseñar y probar el funcionamiento de diferentes estrategias de control para el despegue, aterrizaje y cambios en los tres ángulos de un hexacóptero. Las estrategias de control a usarse son el PID y el Control en Modo Deslizante. El control en Modo Deslizante puede ser implementado usando un controlador PD como Superficie deslizante. Los controladores son probados mediante simulaciones.
Palabras clave: Control robusto; control por modo deslizante; hexacóptero; desempeño; PID
]]> The interest for Unmanned Aerial Vehicles (UAVs) is increasing every day. UAV ́s are used in several applications such as: in military, in agricultural tasks, in industrial maintenance, and also may be employed for a wide variety of transportation operations and planning applications: monitor freeway conditions, coordination among a network of traffic signals, traveler information, emergency vehicle guidance, track vehicle movements in an intersection, and so on. [1]UAV ́s are nonlinear and present an interesting dynamics where the uncertainties on physical parameters make them an attractive and challenging control problem [2, 3]. A robust and accurate control system is essential for UAVs to successfully perform different tasks and also compensate for uncertainties and the high nonlinearities present in plane dynamics.
Sliding Mode Control (SMC) is a robust and simple procedure that allows synthesizing controllers for linear and nonlinear processes [4]. The main advantages of using sliding mode control are robustness to parameter
uncertainty, insensitivity to load disturbance and fast dynamics response. Commonly, the design of this controller depends completely on the process model, and the number of tuning parameters are in proportion to the model order. The major drawback of sliding mode control is the so called chattering phenomenon [5, 6]. Various SMC proposal have been used to control UAVs. Mohd et al [7]. M’hammed Guisser and Hicham Medromi [8]. Nader et al [9]. Benallegue et al [10]. This work shows a general and simple SMC strategy that can be applied to hexacopters. The main impact of this work is that the proposed SMC is based on easy concepts. The controller algorithm can be implemented using a classical PD controller as the sliding surface. Therefore, an existing controller structure is utilized, which no need complex calculations, and additionally it presents low computational cost to achieve the control signal. Two different control strategies are tested, in such a way that the system can take-off and land even though disturbances. The control strategies compared are PID and Sliding Mode Control, since PID represents an standard and it is the most used controller in industry. The performance and robustness analysis to tracking and regulation tasks are presented through simulations. This paper is organized as follows. Section 2 presents the hexacopter dynamic model. Section 3 presents the fundamentals and the formulation of the Sliding Mode Control. In section 4 different simulations are developed, and their discussion are presented. Finally, section 5 contains the conclusions. 2. Hexacopter dynamic model The scheme of the hexacopter studied here is shown in Figure 1. The equations of motion are given in [11].
The discontinuous part of these controllers (Figure 2) are calculated in a similar way as in the altitude controller case, and the equations are analogous to equation (26), considering that the sliding surface depends on the error for each case.
4. Simulation results In this section, the proposed approach and the PID controller are tested by simulations, firstly a performance comparison of the SMC against the PID for tracking and regulation tasks is revised, and secondly robustness testing are done: for mass changes, for modelling errors, and finally is considered the effect of noise. The hexacopter nominal parameters are specified in table 1.
The comparison is done in such a way that SMC is compared with the best PID. Tables 4 and 5 show the results with and without disturbances.
Figures 3 represent the system responses for each controller when external disturbances are considered. The SMC presented a better performance than the PID controller for all cases, it reached the desired reference in shorter time and also zero steady-state error, both tracking and regulation tasks are accomplished. For the case of altitude, the PID controller fails to achieve both tasks.
4.2 Robustness testing
One of the main advantages of the SMC is the robustness to modeling errors and uncertainties. In this part, modeling errors in parameters affecting considered are mass and inertia moments in ‘x’, ‘y’ and ‘z’ axes.
4.2.1 Mass changes
The mass is a parameter that directly influences the system and specifically its stability. The mass is modified from its nominal value up to 10 kg. Figures 4 (a) and 6 (b) show how the mass changes can influence the Hexacopter response for each controller.
4.2.2 Modeling errors
In this section errors in the inertia moments of the different axes, are considered. These values are modified around 50% of the original values, the responses have depicted in figure 5. Figure 6 shows that the SMC reaches the desired reference value despite the changes that occurred in inertia moments, the settling time increased, but the results are still satisfactory. Contrasting, the PID controller has oscillations and it has a steady-state error.
Taking into account all the features and advantages that have been presented for the SMC, the next experiment includes changes in angles and altitude. The nominal values are z = 5m, Roll=5° (π/36 rad), Pitch=5° (π/36 rad), Yaw=5° (π /36) and disturbances of 30% for altitude and π/180 for each of the angles are included.
Figure 7 shows the path followed for the hexacopter, it is smooth with a fast response to disturbances, not only in altitude but also in the angles. The proposed control fulfills with flight and landing requirements set at the beginning of this work.
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4.2.3 Effect of noise.
To test the effect of noise on the SMC, a Gaussian noise is added (Figure 8). The test shows that the SMC is sensitive to the presence of noise as it is expected from controller equation. The inclusion of noise increases the settling time.
5. Conclusions
The present work has shown a robust control scheme based on Sliding Mode Control. The control scheme used is based on a classic PD control scheme used as the sliding surface. The example presented indicate that the SMC performance is stable and quite satisfactory in spite of nonlinearities over a wide range of operating conditions.
The simulation results revealed that it is possible to implement the sliding mode control algorithm for hexacopter; the SMC presented a good performance for tracking and also robustness to modeling errors.
The proposed SMC was tested under noisy input signals, a common characteristics of real industrial processes. The SMC showed be tolerant to continuous noisy input signals, keeping a stable response behavior.
The tuning parameters for the SMC were found by trial and error, thence it is recommended to develop a tuning equations set to simplify the implementation.
Acknowledgments
]]> Oscar Camacho thanks to PROMETEO Project of SENESCYT, Republic of Ecuador, for its support for the realization of this work.References
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Recibido el 21 de Septiembre de 2015 En forma revisada 26 de Septiembre de 2016
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