Global Sliding-Mode Suspension Control of Bearingless Switched Reluctance Motor under Eccentric Faults to Increase Reliability of Motor

Bearingless motor development is a substitute for magnetic bearing motors owing to several benefits, such as nominal repairs, compactness, lower cost, and no need for high-power amplifiers. Compared to conventional motors, rotor levitation and its steady control is an additional duty in bearingless switched reluctance motors when starting. For high-speed applications, the use of simple proportional integral derivative and fuzzy control schemes are not in effect in suspension control of the rotor owing to inherent parameter variations and external suspension loads. In this paper, a new robust global sliding-mode controller is suggested to control rotor displacements and their positions to ensure fewer eccentric rotor displacements when a bearingless switched reluctance motor is subjected to different parameter variations and loads. Extra exponential fast-decaying nonlinear functions and rotor-tracking error functions have been used in the modeling of the global sliding-mode switching surface. Simulation studies have been conducted under different testing conditions. From the results, it is shown that rotor displacements and suspension forces in X and Y directions are robust and stable. Owing to the proposed control action of the suspension phase currents, the rotor always comes back rapidly to the center position under any uncertainty.


Introduction
Contemporary industry needs high-speed motor drives in aerospace compressors, flywheel technology-based electrical energy storage devices, and electric vehicles [1,2]. However, several difficulties may occur when a conventional mechanical bearing is used to support the shaft of a high-speed electric motor. Mechanical bearings in high-speed applications increase frictional drag and decrease the performance of the machine. This results in decreasing the service life of bearings due to heavy wear and tear, and in turn increases the maintenance requirements of the machine. Magnetic bearing motors have been widely researched to solve the difficulties caused by conventional mechanical bearings. Magnetic bearing have advantages such as friction-free and high-speed operation compared with conventional motors, which also improves the longevity of the drive. Thus, magnetic bearings are widely used in energy transport, the machine processing industry, aerospace, robotics, and other high-tech areas [3][4][5].
Due to these outstanding advantages, magnetic bearing motors have been successfully applied in many areas since the 1970s. However, in application, there are some disadvantages, for example: Based on the above advantages compared with magnetic bearing motors, bearingless motors are more useful in high-power and high-speed fields. Therefore, bearingless technology has been paid more attention by many researchers [6,7]. Currently, the bearingless research emphasis is mainly placed on bearingless induction motors, bearingless permanent magnet motors, bearingless switched reluctance motors (BSRM), and so on. Compared with other types of bearingless motors, research on BSRM has started only recently, and the technology is immature.

Development of BSRM
BSRM has been developed based on switched reluctance motors and magnetic bearing motors. Therefore, BSRMs not only have superior performance within the field of switched reluctance motors, but they also present a useful feature of bearingless motors. Recently, several structures of BSRM have been proposed. Masatsugu Takemoto et al. [8][9][10][11] were the first to successfully realize the suspension of BSRM, and recommended the technique of differential windings of the bearingless motor to the SRM. In this structure, two types of windings are on each stator pole: one is torque winding, and the other is suspending force winding. Moreover, all the BSRM structures, as mentioned earlier, are based on the general SRM structure, in which torque control cannot naturally decouple from suspended force control. Therefore, developing a novel structure for solving the coupling problem between torque and suspended force controls is a critical research direction.
Takemoto et al. [12][13][14] presented the detailed structure and operation principle. However, in this structure, the regions for generating torque and suspended force cannot be fully used, because the operating point has to be selected to compromise between torque and suspended force. At the same time, two suspended force windings from each phase need the capability of bi-directional regulation. Two switches per one suspended force winding should be required, which may cause higher cost. Chen et al. and Hoffman et al. [15][16][17] proposed a hybrid rotor structure, called the Morrison rotor. The Morrison rotor simplifies the stator design, in that it contains only one type of winding. The rotor Energies 2020, 13, 5485 3 of 38 is a hybrid that includes a circular lamination stack for levitation and a multi-pole lamination stack for rotation [18][19][20]. However, because of increases in axial length, the critical speed of the rotor is reduced. Meanwhile to maintain rotor at the center, high reverse torque cannot always be avoided.
Wang, Lee, and Ahn [21][22][23] proposed a method for bearingless SRM with 8/6 type, in which three windings are loaded with different currents in each commutating period. Consequently, three torques and three lateral forces are generated. However, to satisfy suspended force, reverse torque is hard to avoid. This method restricts the increasing of rotor speed. At the same time, for the above two structures, it is very complicated to realize control methods for steady suspension. References [24,25] proposed a new BSRM with hybrid stator poles. In this structure, only half of the stator poles are used for the torque. Therefore, power density is very low. Moreover, in this motor, long flux paths are taken, and flux reversal exists in the stator core, which may increase the magnetic motive force (MMF) requirements and have higher core losses. A single winding design on 10/8 and 12/14 BSRM was proposed in references [18,26,27] to obtain a decoupled nature between suspended force and motor torque. The 12/14 BSRM's stator and the rotor consist of salient poles. There are two types of windings wound on the stator; one is the suspension force winding to produce suspension force, and the other is torque winding to provide reluctance torque [28]. There are no windings on the rotor. Two self-regulated DC supplies are given to the suspension and torque coils to achieve the decoupled performance between net levitation force and motor torque of the 12/14 BSRM. The literature presented is summarized in Table 1.

A Global Sliding-Mode Control (GSMC) Approch for Eccentric Fault Analysis of BSRM
The rotor of the BSRM is not supported on any mechanical bearings. Therefore, the rotor will have an eccentric effect owing to a sudden variation of external loads and parameters of the system. In the case of a proportional integral derivative (PID) and fuzzy controller-based suspension control of BSRM drives, the command current depends significantly on the performance of the controller [29]. Also, a PID controller needs to be re-tuned when the desired suspension force command changes. Therefore, compared with sliding-mode controllers (SMC), the simple PID and fuzzy controller strategies are not capable when the drive is under internal and external eccentric fault disturbances of obtaining a stable mode levitation property [30][31][32]. The basic benefit of SMCs is their robustness [33], and they do not permit parameter variations in the control channel. Furthermore, the SMC permits the BSRM to be unresponsive to parameter variations and eccentric faults. However, in the design of SMC, there needs to be a large magnitude of gain constants to slide the state trajectories of a dynamic system on a pre-determined sliding-mode surface [34]. In addition to this, the SMC at high speeds experiences problems such as chattering due to high switching gains. These particular aspects make the SMC less attractive to bearingless drives even though it offers robust and stable behavior [35].
To escape the conspicuous difficulties of reaching time and chattering in the control scheme of SMC, a new global sliding-mode control (GSMC) has been employed. The GSMC ensures the system state trajectories can be on the sliding-mode surface at an early time only, and the system robustness and disturbance elimination ability will improve [36,37]. A fast-decaying exponential nonlinear function has been added when designing the GSMC method for the linear sliding-mode switching surface equation [38]. Due to the extra exponential nonlinear switching functions, the sliding-mode state trajectory can quickly evolve into the linear sliding-mode surface [39]. The global sliding-mode state trajectory progression rate will be enhanced simply by choosing the exponential decaying function quantities [40].

Objectives
The main contributions of this paper are the design and modeling of a GSMC to minimize the eccentric faults in any quadrant of the rotor position.
A comparison study was undertaken between robust controllers such as SMC and GSMC to obtain minimized eccentric effect under different parameter varying conditions. BSRM mathematical modeling was done, and the assumption is made that an individual phase is magnetically decoupled. The finite element method (FEM) is used to analyze the characteristics of the proposed structure, which includes magnetic flux distribution, inductance, torque, and suspended force. In addition to its decoupled nature, the short flux paths in the stator and eccentric effects are also discussed. The converter-based power electronic operation and its modes of operation, switching rules, switching control strategy, and converter topology are also discussed. A simulation model is set up to validate the proposed methodology. The simulation of the BSRM is systematically characterized into three steps.
As a primary step, the displaced rotor in any one of the four quadrants in the air gap must be successfully pulled back to the center position with the help of the proposed GSMC suspension controller along with the asymmetric converter, hysteresis controller, and rotor displacement sensors. The next step is to run the motor at the rated speed by exciting phase currents. Lastly, to examine the disturbance rejection ability and robustness properties of BSRM, different suspension loads, change of references, and rotor weights are applied separately. With the substantial existence of decoupled behavior between suspension and motor parameters, the suspension and motor loads are applied simultaneously, and the performance properties are shown individually.

Paper Organization
The paper is presented as follows: in Section 2, the Operating Principle and Modeling of 12/14 BSRM is discussed; Section 3 shows the proposed global sliding-mode controller modeling. With the above modellings, dynamic simulation is carried out. Complete, robust behavior and minimized eccentric properties are observed and discussed in Section 4. The proposed controller (GSMC) performance is compared in Section 5 with conventional controller (SMC). Section 6 concludes the work performed and the observations made. From the simulation outputs, the rotor displacements deviate less by the proposed control method as compared to the conventional SMC. The overall system exhibits more robustness to the external disturbances.

Operating Principle and Modeling of BSRM
The stator and the rotor of the BSRM consist of salient poles. There are two types of windings on the stator-one is the suspension force winding to produce suspension force, and the other is torque winding to produce the reluctance torque. There are no windings on the rotor. The regulated DC voltages are applied to the stator torque coils and suspension coils individually to achieve decoupled performance among net radial suspension force and resultant torque. The coordinately placed suspension winding coils Is1 and Is3, and Is2 and Is4 on the stator produces the radial forces in Y and X directions, respectively. Is2 and Is1 produce the positive suspension forces, and Is4 and Is3 poles produce the negative suspension forces to make uniform and equilibrium stable levitation action. The remaining stator main-phase coils, known as Phase-A and Phase-B, will produce the resultant rotational torque. The operating parameters and ratings of the 12/14 BSRM are given in Table 2. The basic 12/14 BSRM construction and its winding arrangement is shown in Figure 1.

FEM Analysis
In switched reluctance machines, the motor torque profile is always in a nonlinear relationship to the operating current and rotor position due to its switching operation [41][42][43]. At present, FEMbased simulations offer the best accurate machine models. The FEM numerical data can be used directly in any controller and observer designs [44,45].
The suspension winding's flux pattern, when all the coils are excited, is shown in Figure 2. Similarly, the individual flux distribution pattern of the main windings is shown in Figure 3a

FEM Analysis
In switched reluctance machines, the motor torque profile is always in a nonlinear relationship to the operating current and rotor position due to its switching operation [41][42][43]. At present, FEM-based simulations offer the best accurate machine models. The FEM numerical data can be used directly in any controller and observer designs [44,45].
The suspension winding's flux pattern, when all the coils are excited, is shown in Figure 2. Similarly, the individual flux distribution pattern of the main windings is shown in Figure 3a

FEM Analysis
In switched reluctance machines, the motor torque profile is always in a nonlinear relationship to the operating current and rotor position due to its switching operation [41][42][43]. At present, FEMbased simulations offer the best accurate machine models. The FEM numerical data can be used directly in any controller and observer designs [44,45].
The suspension winding's flux pattern, when all the coils are excited, is shown in Figure 2. Similarly, the individual flux distribution pattern of the main windings is shown in Figure 3a    Similarly, as shown in Figure 5, due to the pole arc of the suspension pole being more significant than one rotor pole pitch, the inductance profile of the suspension winding is almost constant, and it does not vary with rotor position.  Similarly, as shown in Figure 5, due to the pole arc of the suspension pole being more significant than one rotor pole pitch, the inductance profile of the suspension winding is almost constant, and it does not vary with rotor position.  The main torque profiles of BSRM regarding rotor position and at different phase current values shows the nonlinear relationship between torque and phase currents, as shown in Figure 6.

Rotor Modeling (Suspension Control)
To levitate the rotor from a standstill position, the total suspension force (Fs) is obtained by adding both x-and y-directional suspension forces, given in Equation (1).
The desired rotor displacement tracking states are written and shown in Equation (3) by choosing displacement states X1, X2, Y1, and Y2 as state variables from Equations (1) and (2). Similarly, as shown in Figure 5, due to the pole arc of the suspension pole being more significant than one rotor pole pitch, the inductance profile of the suspension winding is almost constant, and it does not vary with rotor position.
The main torque profiles of BSRM regarding rotor position and at different phase current values shows the nonlinear relationship between torque and phase currents, as shown in Figure 6. The main torque profiles of BSRM regarding rotor position and at different phase current values shows the nonlinear relationship between torque and phase currents, as shown in Figure 6.

Rotor Modeling (Suspension Control)
To levitate the rotor from a standstill position, the total suspension force (Fs) is obtained by adding both x-and y-directional suspension forces, given in Equation (1).
The desired rotor displacement tracking states are written and shown in Equation (3) by choosing displacement states X1, X2, Y1, and Y2 as state variables from Equations (1) and (2).

Rotor Modeling (Suspension Control)
To levitate the rotor from a standstill position, the total suspension force (F s ) is obtained by adding both x-and y-directional suspension forces, given in Equation (1).
Energies 2020, 13, 5485 9 of 38 The desired rotor displacement tracking states are written and shown in Equation (3) by choosing displacement states X 1 , X 2 , Y 1 , and Y 2 as state variables from Equations (1) and (2).
The electrical equivalent suspension forces in terms of suspension currents are given by Equation (4).
where K X = diag Kxxp Kxyp Kxxn kxyn , K Y = diag K yxp K yyp K yxn K yyn , and I x = For the rotor displacements, the equivalent desired tracking state-space equations are given by

Modeling of BSRM for Motor Control
The motor states Ψ ph , w, and θ are considered to be state variables for the state-space representation of BSRM, as shown in Equation (8).

Switching Control Strategy
The BSRM needs six hysteresis current controllers overall to controlling both suspension force and net torque. Out of six, two are for individual torque-winding current controllers and the remaining four are for suspension force current controllers. According to the operating principle discussed in the above section, the six-phase 12/14 BSRM needs 12 power switches. As a result, eight power switches are essential for controlling the four-phase suspension windings and four power switches for two-phase torque windings. Figure 7 shows the four switching states of the asymmetric converter, which are used in BSRM for independent control of each phase. Mode 1 is a magnetization mode in which positive DC-link voltage is applied to the winding; Modes 2 and 3 are freewheeling modes in which the winding has short-circuited through an IGBT and a diode; Mode 4 is a demagnetization mode where the negative DC-link voltage is applied.
remaining four are for suspension force current controllers. According to the operating principle discussed in the above section, the six-phase 12/14 BSRM needs 12 power switches. As a result, eight power switches are essential for controlling the four-phase suspension windings and four power switches for two-phase torque windings. Figure 7 shows the four switching states of the asymmetric converter, which are used in BSRM for independent control of each phase. Mode 1 is a magnetization mode in which positive DC-link voltage is applied to the winding; Modes 2 and 3 are freewheeling modes in which the winding has short-circuited through an IGBT and a diode; Mode 4 is a demagnetization mode where the negative DC-link voltage is applied. The selection of suspended force windings is mentioned in Table 3, where the switching state 1 indicates magnetization mode; the switching state 0 means freewheeling mode. Figure 8 shows the switching block diagram of suspension control. Table 3. Hysteresis current control switching states for BSRM. The selection of suspended force windings is mentioned in Table 3, where the switching state 1 indicates magnetization mode; the switching state 0 means freewheeling mode. Figure 8 shows the switching block diagram of suspension control. If F x ≥ 0, F y ≥ o Is1 and Is2

Asymmetric converter
Where suffix n and prefers to negative and positive respectively Figure 8. Switching block diagram for suspension control.

Modeling of Global Sliding-Mode Controller
The rotor displacement error functions and new global sliding-mode switching equations are expressed by Equations (9) and (10).
x d e =x-x , y d e =y-y The derived GSMC equations for rotor displacements are given by Similarly, the motor speed tracking error function, the new global sliding-mode switching function for speed tracking and control equations are defined by Equations (14)- (16). .
The design and implementation procedure of GSMC are shown in Figure 9. The simple block diagram and the stepwise procedure of GSMC-based control of BSRM are shown in Figure 9a,b, respectively.

Modeling of Global Sliding-Mode Controller
The rotor displacement error functions and new global sliding-mode switching equations are expressed by Equations (9) and (10).
S y = · e y + C y S y − S y (0)e −D y t C y > 0 The derived GSMC equations for rotor displacements are given by Similarly, the motor speed tracking error function, the new global sliding-mode switching function for speed tracking and control equations are defined by Equations (14)- (16).
The design and implementation procedure of GSMC are shown in Figure 9. The simple block diagram and the stepwise procedure of GSMC-based control of BSRM are shown in Figure 9a,b, respectively.
The complete sensor-based eccentric control block diagram of BSRM is presented in Figure 10. The actual rotor X and Y displacements are taken as feedback from displacement sensors and are added negatively to the reference displacements (Xref = 0 and Yref = 0). The controlled outputs F x * Energies 2020, 13, 5485 12 of 38 and F y * are produced from the GSMC controller according to the given displacement error signal. The controlled forces are then applied to the current hysteresis controller, which generates eight suitable switching signals to the four-phase asymmetric converter. The four-phase suspension asymmetric converters excite the suspension windings with controlled phase voltages. The resultant suspension phase currents produce the suspension force to levitate the rotor to the desired location.    added negatively to the reference displacements (Xref = 0 and Yref = 0). The controlled outputs Fx* and Fy* are produced from the GSMC controller according to the given displacement error signal. The controlled forces are then applied to the current hysteresis controller, which generates eight suitable switching signals to the four-phase asymmetric converter. The four-phase suspension asymmetric converters excite the suspension windings with controlled phase voltages. The resultant suspension phase currents produce the suspension force to levitate the rotor to the desired location.

Levitation Control of BSRM
In accordance with the switching state instructions of the hysteresis current controller, the stator suspending force winding currents Is1, Is2, Is3, and Is4 produce the controlled levitation forces to keep the rotor at the center when the rotor is displaced by −100 and +100 micrometers in x and y directions, respectively, from the origin. The suspension-controlled voltages and currents are presented in Figure 11a,b, respectively. At the time of starting of the motor, the suspension windings draw maximum currents to overcome their own inertia of the rotor weight. The net levitation forces and actual displacements of the rotor are presented in Figure 11c-e. Figure 11e shows that the eccentric displacement errors in two directions quickly come to zero, which implies that if the rotor is in any of the four quadrants, the proposed GSMC suspension controller will put the rotor at the center position in less than 0.01 s.

Levitation Control of BSRM
In accordance with the switching state instructions of the hysteresis current controller, the stator suspending force winding currents Is1, Is2, Is3, and Is4 produce the controlled levitation forces to keep the rotor at the center when the rotor is displaced by −100 and +100 micrometers in x and y directions, respectively, from the origin. The suspension-controlled voltages and currents are presented in Figure 11a,b, respectively. At the time of starting of the motor, the suspension windings draw maximum currents to overcome their own inertia of the rotor weight. The net levitation forces and actual displacements of the rotor are presented in Figure 11c-e. Figure 11e shows that the eccentric displacement errors in two directions quickly come to zero, which implies that if the rotor is in any of the four quadrants, the proposed GSMC suspension controller will put the rotor at the center position in less than 0.01 s.

Accelerating the Rotor to the Desired Speed
The BSRM operates in a single pulse mode, which means the only positive voltage is excited at conduction (magnetization) mode. Similarly, the reverse voltage is excited at the time of the demagnetization mode. From Figure 12a, it can be observed that the process of getting the desired speed of 9000 rpm on the 12/14 BSRM is same as that of general SRM. The output torque phase currents seem to be steady, and the torque currents show practically very little effect on the suspending force, as shown in Figure 12b-d when the steadily suspended rotor rotates at 9000 rpm at the center position. From Figure 12e, the ripples in the net output torque are comparatively more since here no optimal methods are used to reduce the ripples in actual torque. The sliding-mode speed trajectory is shown in Figure 12f.

Accelerating the Rotor to the Desired Speed
The BSRM operates in a single pulse mode, which means the only positive voltage is excited at conduction (magnetization) mode. Similarly, the reverse voltage is excited at the time of the demagnetization mode. From Figure 12a, it can be observed that the process of getting the desired speed of 9000 rpm on the 12/14 BSRM is same as that of general SRM. The output torque phase currents seem to be steady, and the torque currents show practically very little effect on the suspending force, as shown in Figure 12b-d when the steadily suspended rotor rotates at 9000 rpm at the center position. From Figure 12e, the ripples in the net output torque are comparatively more since here no optimal methods are used to reduce the ripples in actual torque. The sliding-mode speed trajectory is shown in Figure 12f.

Variation of Suspension Loads
When the rotor is initially placed in any of the four quadrants, to observe and confirm the robustness and fast-tracking control properties of the proposed GSMC to the BSRM, different loads and parameter variation cases are considered. Before applying the suspension loads, the rotor is initially placed at an eccentric distance of (±100 µm, ±100 µm) and the reference displacements of (0, 0) are kept at origin, respectively.
The displacements of rotor and the overall suspension forces both in X and Y directions are presented in Figure 13a-c, when the rotor is initially placed in the first quadrant (+100 µm, +100 µm) and subjected to a suspension load disturbances of 10 N at 0.015 s, −10 N at 0.03 s, and 0 N at 0.045 s in both X-and Y-axis, respectively. Similarly, the suspension forces and rotor displacements are shown in Figure 14a-c, when the rotor is placed in an eccentric distance off (+100 µm, −100 µm) from the origin, i.e., in the second quadrant, and subjected to suspension loads.

Variation of Suspension Loads
When the rotor is initially placed in any of the four quadrants, to observe and confirm the robustness and fast-tracking control properties of the proposed GSMC to the BSRM, different loads and parameter variation cases are considered. Before applying the suspension loads, the rotor is initially placed at an eccentric distance of (±100 μm, ±100 μm) and the reference displacements of (0, 0) are kept at origin, respectively.
The displacements of rotor and the overall suspension forces both in X and Y directions are presented in Figure 13a-c, when the rotor is initially placed in the first quadrant (+100 μm, +100 μm) and subjected to a suspension load disturbances of 10 N at 0.015 s, −10 N at 0.03 s, and 0 N at 0.045 s in both X-and Y-axis, respectively. Similarly, the suspension forces and rotor displacements are shown in Figure 14a-c, when the rotor is placed in an eccentric distance off (+100 μm, −100 μm) from the origin, i.e., in the second quadrant, and subjected to suspension loads.  Figures 15a-c and 16a-c show the rotor suspension forces and displacements when the rotor is in the third and fourth quadrants when the rotor is subjected to suspension loads. From the results, it is observed that the proposed suspension controller rapidly tracks the rotor displacements and positions, and keeps the rotor in the center due to its robust response to external forces.

Change of Input Reference Displacements
In this section, the study of the rotor response to the reference command input, its performance characteristics, and the stable levitation properties of a suspended rotor in all quadrants are carried out. The large change in reference value makes a large error input signal to the controller. Therefore, reference values are changed in all four quadrants when the rotor is placed initially at an eccentric physical distance of (+100 μm, −100 μm) in both X and Y directions from the origin, respectively. The simple eccentric displacement of the rotor from the center position is displayed in Figure 17.

Change of Input Reference Displacements
In this section, the study of the rotor response to the reference command input, its performance characteristics, and the stable levitation properties of a suspended rotor in all quadrants are carried out. The large change in reference value makes a large error input signal to the controller. Therefore, reference values are changed in all four quadrants when the rotor is placed initially at an eccentric physical distance of (+100 µm, −100 µm) in both X and Y directions from the origin, respectively. The simple eccentric displacement of the rotor from the center position is displayed in Figure 17.
As a first step, the reference values are changed within the first quadrant, i.e., at the time of starting the reference value is kept at (+100 µm, +100 µm) and is changed to (+50 µm, −50 µm) at 0.02 s. Finally, it is varied to the desired location of (0 µm, 0 µm) at 0.04 s in both X and Y directions, respectively. The displacements of rotor and suspension forces in X and Y directions are shown in Figure 18a-c. From Figure 18, it can be observed that the rotor is steadily suspended and steadily rotates at the desired speed, even though there is a large error signal. The proposed controller moves the tracking error of both Xand Y-axis displacements to zero in less time. As a first step, the reference values are changed within the first quadrant, i.e., at the time of starting the reference value is kept at (+100 μm, +100 μm) and is changed to (+50 μm, −50 μm) at 0.02 s. Finally, it is varied to the desired location of (0 μm, 0 μm) at 0.04 s in both X and Y directions, respectively. The displacements of rotor and suspension forces in X and Y directions are shown in Figure 18a-c. From Figure 18, it can be observed that the rotor is steadily suspended and steadily rotates at the desired speed, even though there is a large error signal. The proposed controller moves the tracking error of both Xand Y-axis displacements to zero in less time.
Similarly, the remaining three quadrant reference value changes are shown in Table 4, and the corresponding performance characteristics are shown in Figures 19-21. (a) As a first step, the reference values are changed within the first quadrant, i.e., at the time of starting the reference value is kept at (+100 μm, +100 μm) and is changed to (+50 μm, −50 μm) at 0.02 s. Finally, it is varied to the desired location of (0 μm, 0 μm) at 0.04 s in both X and Y directions, respectively. The displacements of rotor and suspension forces in X and Y directions are shown in Figure 18a-c. From Figure 18, it can be observed that the rotor is steadily suspended and steadily rotates at the desired speed, even though there is a large error signal. The proposed controller moves the tracking error of both Xand Y-axis displacements to zero in less time.
Similarly, the remaining three quadrant reference value changes are shown in Table 4, and the corresponding performance characteristics are shown in Figures 19-21. (a)  Similarly, the remaining three quadrant reference value changes are shown in Table 4, and the corresponding performance characteristics are shown in Figures 19-21.    From the above analysis, the rotor displacements, positions, and suspension forces change slightly at the instant of change of reference and immediately those reach the steady state according to the command signal given in both in X and Y directions. The controller can quickly track the rotor displacements in less than 0.001 s, even though there is a large change in reference from ±100 µm to ±50 µm at 0.02 s, and from ±50 µm to 0 µm at 0.04 s.

Rotor Weight Is Changed
The value of rotor weight plays an important role in the levitation control of the rotor. Practically, there is a possibility of sudden change of rotor weights due to mechanical addition and removal of loads from the load end. The sudden change of rotor weights may lead to the failure of rotation and levitation with the absence of proper control action. In this section, the rotor performance and stability analysis are studied when the rotor is subjected to change of rotor weights with the use of the proposed GSMC controller. In this study, initially, the rotor is kept in the 1st quadrant at a physical eccentric displacement off (+100 µm, +100 µm) from origin in X and Y directions, respectively, and the rotor weight is changed to 1.5 times the original at 0.015 s, at 0.030 s the rotor weight changed to 0.5 times the original, and finally at 0.045 s the rotor is free from extra weights. Figure 22 shows the rotor displacements and suspension forces when the rotor is subjected to a change of weights in both X and Y directions, respectively. Figure 22a-c show that there is no significant change in the rotor X-directional displacement and its suspension force. This means that the rotor dynamics in the X direction are more robust to the change in rotor weights due to the control action. The rotor displacement and suspension forces in the Y direction are changed due to rotor weights, but the dynamics quickly come to a stable position and maintain a steady levitation due to the proposed control action.  From the above analysis, the rotor displacements, positions, and suspension forces change slightly at the instant of change of reference and immediately those reach the steady state according to the command signal given in both in X and Y directions. The controller can quickly track the rotor displacements in less than 0.001 s, even though there is a large change in reference from ±100 μm to ±50 μm at 0.02 s, and from ±50 μm to 0 μm at 0.04 s.

Rotor Weight Is Changed
The value of rotor weight plays an important role in the levitation control of the rotor. Practically, there is a possibility of sudden change of rotor weights due to mechanical addition and removal of loads from the load end. The sudden change of rotor weights may lead to the failure of rotation and levitation with the absence of proper control action. In this section, the rotor performance and stability analysis are studied when the rotor is subjected to change of rotor weights with the use of the proposed GSMC controller. In this study, initially, the rotor is kept in the 1st quadrant at a physical eccentric displacement off (+100 μm, +100 μm) from origin in X and Y directions, respectively, and the rotor weight is changed to 1.5 times the original at 0.015 s, at 0.030 s the rotor weight changed to 0.5 times the original, and finally at 0.045 s the rotor is free from extra weights. Figure 22 shows the rotor displacements and suspension forces when the rotor is subjected to a change of weights in both X and Y directions, respectively. Figure 22a-c show that there is no significant change in the rotor X-directional displacement and its suspension force. This means that the rotor dynamics in the X direction are more robust to the change in rotor weights due to the control action. The rotor displacement and suspension forces in the Y direction are changed due to rotor weights, but the dynamics quickly come to a stable position and maintain a steady levitation due to the proposed control action.

Change in Input Voltages
Rotor behavior is observed in this section when the input voltage excitations are changed suddenly. Due to faults of converters and the excitation system, there is a chance of sudden change in voltage. In this study, initially, the rotor is kept in the first-quadrant at an eccentric physical displacement of (+100 μm, +100 μm) from an origin in X and Y directions, respectively, and the phase voltage is varied from 250 v to 300 v at 0.015 s, from 300 v to 200 v at 0.03 s, and from 200 v to 250 v at 0.045 s. Figure 23a-d show the suspension phase's voltage profile when the suspension system is subjected to a change of voltages, rotor Xand Y-directional displacements and suspension forces, respectively. From the above figures, it can be observed that there is no significant change in rotor X-

Change in Input Voltages
Rotor behavior is observed in this section when the input voltage excitations are changed suddenly. Due to faults of converters and the excitation system, there is a chance of sudden change in voltage. In this study, initially, the rotor is kept in the first-quadrant at an eccentric physical displacement of (+100 µm, +100 µm) from an origin in X and Y directions, respectively, and the phase voltage is varied from 250 v to 300 v at 0.015 s, from 300 v to 200 v at 0.03 s, and from 200 v to 250 v at 0.045 s. Figure 23a-d show the suspension phase's voltage profile when the suspension system is subjected to a change of voltages, rotor Xand Y-directional displacements and suspension forces, respectively. From the above figures, it can be observed that there is no significant change in rotor X-and Y-directional displacements and its suspension forces because of a disturbance rejection property of control action. and Y-directional displacements and its suspension forces because of a disturbance rejection property of control action.

Comparisons of Suspension Forces and Displacements with Conventional SMC
The comparisons of suspension forces and rotor displacements of the proposed GSMC with conventional SMC are shown in Figures 24a,b and 25a,b, under the variations of suspension loads and rotor weights, respectively. From Figures 24 and 25, it can be shown that by using the proposed controller, the rotor reached its steady position quickly, and both the controllers maintain robust behavior against change in the parameters. There is an eccentric displacement in the rotor when the loads are applied, but the rotor can be dragged back to the midpoint position quickly by the proposed controller, and the eccentric direction of the rotor is controlled in both in X and Y directions. Based on the aforementioned analysis, when the suspension parameters are varied, speed and torques are not altered, which means that the suspension force control is decoupled from the torque and speed. Furthermore, regardless of whether the rotor has eccentricity or not, the rotor can be steadily suspended and reach its center position steadily, which verifies the validity of the structure.

Comparisons of Suspension Forces and Displacements with Conventional SMC
The comparisons of suspension forces and rotor displacements of the proposed GSMC with conventional SMC are shown in Figure 24a,b and Figure 25a,b, under the variations of suspension loads and rotor weights, respectively. From Figures 24 and 25, it can be shown that by using the proposed controller, the rotor reached its steady position quickly, and both the controllers maintain robust behavior against change in the parameters. There is an eccentric displacement in the rotor when the loads are applied, but the rotor can be dragged back to the midpoint position quickly by the proposed controller, and the eccentric direction of the rotor is controlled in both in X and Y directions. Based on the aforementioned analysis, when the suspension parameters are varied, speed and torques are not altered, which means that the suspension force control is decoupled from the torque and speed. Furthermore, regardless of whether the rotor has eccentricity or not, the rotor can be steadily suspended and reach its center position steadily, which verifies the validity of the structure. . Rotor X-and Y-directional displacements when rotor weights are changed.

Conclusions
To align the rotor position at the center and maintain fewer eccentric rotor displacements when BSRM is subjected to different suspension loads, a GSMC is proposed and discussed in this paper. The stabled, robust suspension forces and rotor displacements of the proposed controller are compared with conventional sliding-mode control. The proposed control scheme is employed using MATLAB/Simulink Software.


First, the operating principle and mathematical modeling of BSRM is discussed.  When the suspension load is applied in the opposite direction, i.e., in the negative, the rotor eccentric direction is also in the opposite, and finally, the rotor dragged back to the center position with the proposed controller.  The rotor displacements, positions, and suspension forces are changed slightly at the instant of change of references, and immediately those reached the steady state according to the command signal.

Conclusions
To align the rotor position at the center and maintain fewer eccentric rotor displacements when BSRM is subjected to different suspension loads, a GSMC is proposed and discussed in this paper. The stabled, robust suspension forces and rotor displacements of the proposed controller are compared with conventional sliding-mode control. The proposed control scheme is employed using MATLAB/Simulink Software.

•
First, the operating principle and mathematical modeling of BSRM is discussed.

•
When the suspension load is applied in the opposite direction, i.e., in the negative, the rotor eccentric direction is also in the opposite, and finally, the rotor dragged back to the center position with the proposed controller.

•
The rotor displacements, positions, and suspension forces are changed slightly at the instant of change of references, and immediately those reached the steady state according to the command signal.

•
When the rotor weight is varied suddenly, there is no significant change in rotor displacement and its suspension force. However, in very little time, the rotor reaches a stable position and maintains steady operation due to the proposed control action. • When the suspension system is subjected to a variation of voltages, there is no significant change in rotor X-and Y-directional displacements, and its suspension forces because of the disturbance rejection property of the control action.
With promising performance characteristics obtained from the simulation results, the application of the proposed method can be extended to its implementation in real-time BSRM applications.

Conflicts of Interest:
The authors declare no conflict of interest.

Nomenclature Variable Name
Description m Rotor mass, kg g Gravity (9.8) Fx and Fy X-and Y-directional suspension forces respectively K X and K Y Suspension Force constant matrices K xxp , K yyp K xyp , K yxp and K xxn , K yyn , K xyn and K yxn Corresponding Suspension force constants in both positive and negative directions I x and I Y X-and Y-directional suspension current matrices respectively i xp ,i yp ,i xn ,i yn Suspension currents, amp ψ ph Flux linkage of torque winding R ph Resistance of windings, ohms N Phase inductance reversal matrix θ Position of the rotor per phase, deg V Phase voltage vector, volts w Speed of the rotor, rpm T e and T l Total electromagnetic torque developed and external applied load torque B, J, J new & ∆J Damping coefficient, actual moment of inertia of rotor and J new =