# Comparative Analysis of Three Structures of Second-Order Generalized Integrator and Its Application to Phase-Locked Loop of Linear Kalman Filter

Authors: Bo Zeng; Yuxiang Sun; Shaojun Xie
Journal: Wireless Communications and Mobile Computing
 (2022)

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## Abstract

The present work explores the power quality problems of a microgrid in the aviation field, such as frequency offset or waveform distortion, caused by voltage imbalance and nonlinear load, to ensure the efficient and stable flight of aircraft, unmanned aerial vehicles, and other aircraft. There are many problems such as excessive harmonics, voltage imbalance, and direct current (DC) component in aviation variable frequency power supply voltage in microgrid under different conditions. Therefore, three kinds of second-order generalized integrators (SOGIs) with different structures are combined with linear Kalman filter phase-locked loops (PLLs). Besides, intelligent sensors are utilized for signal processing. Finally, simulation experiments are conducted to compare three SOGIs. The results show that the system is stable when the parametersk1 = 738.9553, k2 = 1092108.98405, k3 = 1477.91, and Ts = 0.000125 s and k ranges in [0.5, 3]. The angular frequency of PLL output is very low under the problems of many harmonics, three-phase voltage imbalance, and DC component ωg. The angular frequency ωg output by the PLL finally changes linearly with a change rate of 400 πrad/s2, so that the output phase angle θg reaches a stable state. Thus, the proposed steady-state linear Kalman filter phase locking can accurately phase-lock the aviation variable frequency power supply. It provides an important reference for the power supply module in the microgrid to select the appropriate second-order generalized integrator to realize the accurate phase locking of the phase-locked loop under different conditions.


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## Body

## 1. Introduction

Electricity is one of the essential elements for the normal operation of modern society. Most of the world uses coal, oil, or other nonrenewable energy as the main fuel to provide electricity, which makes the depletion of nonrenewable energy and environmental pollution increasingly serious. Therefore, using clean renewable energy instead of traditional energy has gradually become an inevitable trend. In this context, microgrid uses diversified and clean new energy, attracting increasingly more attention from all countries in the world as an environmentally friendly, efficient, decentralized, and flexible power generation way. It has become a critical path to solve the contradiction between energy and the environment. The emergence of microgrid, a distributed generation (DG) method, furnishes the large power grid with a powerful supplement. Large-scale access to power grids has realized the coordination between main power grids, local power grids, and microgrids, making transmission modes more flexible [1]. In this kind of power supply structure, the interaction between users and the grid makes the power quality and the reliability of the power supply increase significantly [2]. In aviation, variable frequency power supply is an important part of the aircraft power supply system, which has the advantages of high-power generation efficiency and no need for constant installation and converter [3, 4]. The aviation variable frequency power supply is used as the power supply of the microgrid and is integrated into the power grid through the converter as the power interface; meanwhile, the phase-locked loop (PLL) is used to realize the high-power factor operation of the aviation rectifier. The wide operating frequency range of aviation variable frequency power supply (typically 360∼800 Hz) puts forward high requirements for PLL.The steady-state linear Kalman filter PLL [5–8] (SSLKF-PLL) is a common PLL used in multi-electric aircraft converters. SSLKF-PLL provides excellent phase-locking performance for aviation variable frequency power supplies with a wide operating frequency range. SSLKF-PLL is an adaptive phase-frequency estimation algorithm based on a third-order linear steady observation model and a predictive correction model. It employs three different control units to estimate the phase angle, angular frequency, and angular frequency acceleration, respectively [9,10]. Therefore, compared with conventional synchronous coordinate system software PLL and the PLL based on discrete Fourier transformation [11], SSLKF-PLL has the advantages of fast dynamic response, high phase-locked accuracy, and good filtering performance. However, in the presence of high-voltage harmonics, three-phase voltage imbalance, and a direct current (DC) component in aviation inverter power supplies, the phase angle output by SSLKF-PLL contains a high-frequency component, which can affect phase-locking accuracy. Therefore, using intelligent sensors for alternating current (AC) voltage signal processing is also excessively significant. The aviation frequency conversion power supply has many voltage harmonics, three-phase voltage imbalance, and DC components. Therefore, to realize the fast and accurate phase locking of SSLKF, when using intelligent sensors to process the AC voltage in the frequency conversion power supply, a second-order generalized integrator (SOGI) can be added to the front stage of SSLKF-PLL. SOGI is a common second-order filter, which can generate two mutually orthogonal signals at the same time, and its transfer function has infinite gain at a specific frequency. Different SOGIs with different structures are applied to PLL, and different results can be obtained under different supply voltages [12–14]. The literature [15] proposed three kinds of SOGIs with different structures and applied them to the common three-phase synchronous coordinate PLL. The authors gained different results of phase locking and different adaptability to the power grid when the three-phase input voltage was the constant frequency and the three-phase input voltage contained harmonics, subharmonics, and interharmonics. It provides an important reference for selecting different second-order generalized integrator structures for phase-locked loop under different input voltage conditions in aviation variable frequency power supply.Here, based on the linear Kalman filter PLL, the intelligent sensor is used to process the AC voltage in the frequency conversion power supply, and SOGIs of different structures mentioned in reference [15] are added. The central angular frequency of the SOGI is obtained by feedback from the linear Kalman filter PLL. Moreover, the central angular frequency is a variable with time, so a high-order PLL system with strong nonlinearity is formed. In the existing literature, PLL is mostly applied to the linear analysis of the small-signal model, but for the nonlinear systems, a large deviation from the small-signal linear model is neglected in the case of large signal input [16,17]. Therefore, it is essential to conduct a nonlinear analysis of PLL. There are few studies on higher-order nonlinear systems. In the literature [16–20], the stability of the system is judged by the convergence of the solution of differential equations, which provides a reference for the analysis of higher-order nonlinear systems. In view of the method proposed in reference [20], the innovation is that, firstly, the structure of linear Kalman filter PLL with second-order generalized integrator is proposed, the state equation of the system is derived, and then the stability region is obtained by solving the state equation. Secondly, the second-order generalized integrators with different structures mentioned in the literature are applied to SSLKF and compared. Different phase-locked results are obtained under different input voltage conditions, important conclusions are drawn, and the application occasions of the second-order generalized integrators applied to SSLKF are pointed out under three different aviation variable frequency power supply conditions.


## 2. Structure of the Linear Kalman Filter PLL with SOGI in the Microgrid

In the present work, the linear Kalman filter PLL is adopted, and SOGI is added to the microgrid. The central angular frequency of the SOGI is output by the Kalman filter PLL obtained by feedback. Figure1 displays the structure of PLL [21, 22].Figure 1
Structure of PLL.


### 2.1. Structure of the Linear Kalman Filter PLL

The structure of the Kalman filter PLL is given in reference [8], as shown in Figure 2.Figure 2
Structure of the Kalman filter PLL.The time-domain equation between the phase angleθg output by the Kalman filter PLL as well as the angular frequency ωg and the three-phase grid voltages va, vb, and vc after synchronous coordinate transformation can be expressed as follows:(1)ωg=∫k2vq+∫k1vqdtdt,θg=∫ωg+k3vq−Ts2∫k1vqdtdt,where k1, k2, and k3 are coefficients and Ts denotes the sampling period.


### 2.2. SOGIs of Three Structures

#### 2.2.1. Structure of A-Type SOGI

Figure3 reveals the structure of A-type SOGI, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL [23,24]. The time-domain equation of A-type SOGI can be written as follows.where k represents the damping coefficient of the SOGI and q refers to the q axis in the dq coordinate system.Figure 3
Structure of A-type SOGI.(2)v′=∫v−v′k−qv′ω′dt,qv′=ω′∫v′dt,ω′=ωg,


#### 2.2.2. Structure of B-Type SOGI

Figure4 indicates the structure of B-type SOGI, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL [25]. The time-domain equation of B-type SOGI is shown in the following equation.Figure 4
Structure of B-type SOGI.(3)v′=∫v−v′k−qv′ω′dt,qv′=∫ω′v′dt,ω′=ωg.Comparing equations (2) and (3), when the central angular frequency is fixed, the structures of A-type SOGI and B-type SOGI are the same. However, the research condition reported here is frequency conversion, so the structures of A-type SOGI and B-type SOGI are different.


#### 2.2.3. Structure of C-Type SOGI

In reference [15], a C-type SOGI is proposed, as shown in Figure 5, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL. The time-domain equation of C-type SOGI is shown in the following equation.Figure 5
Structure of C-type SOGI.(4)v′=∫v−v′k−∫v′ω′dtω′dt,qv′=∫ω′v′dt−kv−v′,ω′=ωg.


## 2.1. Structure of the Linear Kalman Filter PLL

The structure of the Kalman filter PLL is given in reference [8], as shown in Figure 2.Figure 2
Structure of the Kalman filter PLL.The time-domain equation between the phase angleθg output by the Kalman filter PLL as well as the angular frequency ωg and the three-phase grid voltages va, vb, and vc after synchronous coordinate transformation can be expressed as follows:(1)ωg=∫k2vq+∫k1vqdtdt,θg=∫ωg+k3vq−Ts2∫k1vqdtdt,where k1, k2, and k3 are coefficients and Ts denotes the sampling period.


## 2.2. SOGIs of Three Structures

### 2.2.1. Structure of A-Type SOGI

Figure3 reveals the structure of A-type SOGI, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL [23,24]. The time-domain equation of A-type SOGI can be written as follows.where k represents the damping coefficient of the SOGI and q refers to the q axis in the dq coordinate system.Figure 3
Structure of A-type SOGI.(2)v′=∫v−v′k−qv′ω′dt,qv′=ω′∫v′dt,ω′=ωg,


### 2.2.2. Structure of B-Type SOGI

Figure4 indicates the structure of B-type SOGI, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL [25]. The time-domain equation of B-type SOGI is shown in the following equation.Figure 4
Structure of B-type SOGI.(3)v′=∫v−v′k−qv′ω′dt,qv′=∫ω′v′dt,ω′=ωg.Comparing equations (2) and (3), when the central angular frequency is fixed, the structures of A-type SOGI and B-type SOGI are the same. However, the research condition reported here is frequency conversion, so the structures of A-type SOGI and B-type SOGI are different.


### 2.2.3. Structure of C-Type SOGI

In reference [15], a C-type SOGI is proposed, as shown in Figure 5, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL. The time-domain equation of C-type SOGI is shown in the following equation.Figure 5
Structure of C-type SOGI.(4)v′=∫v−v′k−∫v′ω′dtω′dt,qv′=∫ω′v′dt−kv−v′,ω′=ωg.


## 2.2.1. Structure of A-Type SOGI

Figure3 reveals the structure of A-type SOGI, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL [23,24]. The time-domain equation of A-type SOGI can be written as follows.where k represents the damping coefficient of the SOGI and q refers to the q axis in the dq coordinate system.Figure 3
Structure of A-type SOGI.(2)v′=∫v−v′k−qv′ω′dt,qv′=ω′∫v′dt,ω′=ωg,


## 2.2.2. Structure of B-Type SOGI

Figure4 indicates the structure of B-type SOGI, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL [25]. The time-domain equation of B-type SOGI is shown in the following equation.Figure 4
Structure of B-type SOGI.(3)v′=∫v−v′k−qv′ω′dt,qv′=∫ω′v′dt,ω′=ωg.Comparing equations (2) and (3), when the central angular frequency is fixed, the structures of A-type SOGI and B-type SOGI are the same. However, the research condition reported here is frequency conversion, so the structures of A-type SOGI and B-type SOGI are different.


## 2.2.3. Structure of C-Type SOGI

In reference [15], a C-type SOGI is proposed, as shown in Figure 5, where the central angular frequency is fed back by the angular frequency ωg of the Kalman filter PLL. The time-domain equation of C-type SOGI is shown in the following equation.Figure 5
Structure of C-type SOGI.(4)v′=∫v−v′k−∫v′ω′dtω′dt,qv′=∫ω′v′dt−kv−v′,ω′=ωg.


## 3. System Stability Analysis and Parameter Design

According to the system chart in Figure1, the real-time angular frequency output by the microgrid system is fed back to the SOGI. Since the frequency of the aviation variable frequency power supply changes in real time, the whole system forms a high-order nonlinear structure.vα and vβ are the linear transformations of three-phase input voltages va, vb, and vc, so they can be regarded as the input of the system. When SOGI in Figure 1 is an A-type SOGI, from Figure 1 and equation (2), there are(5)vα′=∫kvα−vα′−qvα′ωgdt,(6)qvα′=ωg∫vα′dt,(7)vβ′=∫kvβ−vβ′−qvβ′ωgdt,(8)qvβ′=ωg∫vβ′dt.According to the transformation formula fromαβ axis to dq axis, the relationship between the output phase angle of the microgrid system and each quantity can be presented by(9)vq=vβ′+qvα′cosθg−vα′−qvβ′sinθg.Therefore, according to equations (1) and (5)–(9), the time-domain equation of the whole system combining SSLKF with A-type SOGI can be expressed as follows:(10)vα′=∫kvα−vα′−qvα′ωgdt,qvα′=ωg∫vα′dt,vβ′=∫kvβ−vβ′−qvβ′ωgdt,qvβ′=ωg∫vβ′dt,vq=vβ′+qvα′cosθg−vα′−qvβ′sinθg,ωg=∫k2vq+∫k1vqdtdt,θg=∫ωg+k3vq−Ts2∫k1vqdtdt.State variables are selected as follows:(11)xp1=vα′,xp2=qvα′ωg,xp3=vβ′,xp4=qvβ′ωg,xp5=∫vqdt,xp6=ωg,xp7=θg.Equation (12) is an equation of the state of equation (10).(12)x˙p1=kvαxp6−kxp1xp6−xp2xp62,x˙p2=xp1,x˙p3=kvβxp6−kxp3xp6−xp4xp62,x˙p4=xp3,x˙p5=xp3+xp2xp6cosxp7−xp1−xp4xp6sinxp7,x˙p6=k2xp3+xp2xp6cosxp7−k2xp1−xp4xp6sinxp7+k1xp5,x˙p7=xp6+k3xp3+xp2xp6cosxp7−k3xp1−xp4xp6sinxp7−Ts2k1xp5.Similarly, the time-domain equation of the whole system integrating SSLKF and B-type SOGI is shown in equation (13), and the equation of that combining SSLKF and C-type SOGI is written as equation (14).(13)vα′=∫kvα−vα′−qvα′ωgdt,qvα′=∫ωgvα′dt,vβ′=∫kvβ−vβ′−qvβ′ωgdt,qvβ′=∫ωgvβ′dt,vq=vβ′+qvα′cosθg−vα′−qvβ′sinθg,ωg=∫k2vq+∫k1vqdtdt,θg=∫ωg+k3vq−Ts2∫k1vqdtdt,(14)vα′=∫kvα−vα′−∫ωgvα′dtωgdt,qvα′=∫ωgvα′dt−kvα−vα′,vβ′=∫kvβ−vβ′−∫ωgvβ′dtωgdt,qvβ′=∫ωgvβ′dt−kvβ−vβ′,vq=vβ′+qvα′cosθg−vα′−qvβ′sinθg,ωg=∫k2vq+∫k1vqdtdt,θg=∫ωg+k3vq−Ts2∫k1vqdtdt.For equations (13) and (14), the following state variables are selected:(15)xo1=vα′,xo2=qvα′,xo3=vβ′,xo4=qvβ′,xo5=∫vqdt,xo6=ωg,xo7=θg,(16)xr1=vα′,xr2=qvα′,xr3=vβ′,xr4=qvβ′,xr5=∫vqdt,xr6=ωg,xr7=θg.Then, equations (13) and (14) are written as equations of state as shown in equations (17) and (18).(17)x˙o1=kvαxo6−kxo1xo6−xo2xo6,x˙o2=xo1xo6,x˙o3=kvβxo6−kxo3xo6−xo4xo6,x˙o4=xo3xo6,x˙o5=xo3+xo2cosxo7−xo1−xo4sinxo7,x˙o6=k2xo3+xo2cosxo7−k2xo1−xo4sinxo7+k1xo5,x˙o7=xo6+k3xo3+xo2cosxo7−k3xo1−xo4sinxo7−Ts2k1xo5,(18)x˙r1=−xr2xr6,x˙r2=−kdvαdt+xr1xr6−xr2xr6,x˙r3=−xr4xr6,x˙r4=−kdvβdt+xr3xr6−xr4xr6,x˙r5=xr3+xr2cosxr7−xr1−xr4sinxr7,x˙r6=k2xr3+xr2cosxr7−k2xr1−xr4sinxr7+k1xr5,x˙r7=xr6+k3xr3+xr2cosxr7−k3xr1−xr4sinxr7−Ts2k1xr5.According to equations (12), (17), and (18), this system is a seventh-order nonlinear system, and the stability of the system is determined by the parameters k, k1, k2, k3, and Ts. Hence, it is essential to first determine the value of k1, k2, k3, and Ts to select the bandwidth of the Kalman filter PLL. After this procedure, the stability of the system only depends on the value of k.Reference [8] provides the small-signal processing model of the intelligent sensor for the linear Kalman filter PLL, as shown in Figure 6. Equation (19) describes the closed-loop transfer function of the linear Kalman filter PLL.(19)Gs=ω˜gsωgs=k2s+k1s3+k3s2+k2s+k1.Figure 6
Small-signal model of the linear Kalman filter PLL.To ensure the stability of the linear Kalman filter PLL, the roots of the characteristic equation of its closed-loop transfer function are set as a negative real root and a pair of negative real part conjugate roots:(20)s0=−wnR,s1,2=−wnExp±jϕ,where wn>0,R>0, and 0<ϕ<π/2.Substitute equation (20) into the characteristic equation, and there is(21)k1=Rwn3,k2=1+2Rcosϕwn2,k3=R+2cosϕwn.Substituting equation (21) into equation (19), equation (19) can be written as follows:(22)Gs=1+2Rcosϕwn2s+Rwn3s3+R+2cosϕwns2+1+2Rcosϕwn2s+Rwn3.The bandwidthfb of the linear Kalman filter PLL is decided by the parameters R, wn, and ϕ [26–28].According to the definition of bandwidth, there is(23)20lgGj2πfb=20lgGj0−20lg2.Then, the relation between bandwidth and each parameter can be presented as follows:(24)wn2R2wn2+2Rcosϕ+122πfb22πfb2−wn22+4wn2cos2ϕ2πfb2R2wn2+2πfb2=12.According to the literature [7], the change in parameter wn has a significant influence on the bandwidth. Therefore, let R = 1 and ϕ = π/3, and fb is determined by the parameter wn. The bandwidth is set to 100 Hz, 200 Hz, and 300 Hz, respectively, and the values of parameter wn are summarized in Table 1.Table 1
Values ofwn at different bandwidths.
R = 1ϕ = π/3fb = 100 Hzfb = 200 Hzfb = 300 Hzwn369.478738.9551108.433Firstly, the bandwidth of the linear Kalman filter PLL is selected. By adding the A-type SOGI, the filtering performance and dynamic performance of the linear Kalman filter PLL under three different bandwidths are compared, to select the appropriate Kalman filter phase-locked parameters.In the three-phase balanced microgrid system, A-phase voltage can be expressed as follows:(25)va=1152cosωt+15cos5ωt+18∘+8cos7ωt+15∘+5cos11ωt+12∘.The fundamental frequency is set to 400 Hz, the fundamental voltage ofva is denoted as vafund, and the effective value is 115 V. Besides, the total voltage distortion rate is 10.8%, the maximum single voltage distortion rate is 9.2%, and the parameter k of A-type SOGI is 1. Then, the simulation results of the linear Kalman filter PLL under the above three bandwidths are compared.As shown in Figure7, the angular frequency ωg output by the PLL attains a steady-state value of 800 πrad/s in all three bandwidths. Moreover, the dynamic response of bandwidth at 300 Hz is better, but the oscillation time before entering a steady state is longer. The bandwidth at 100 Hz has the slowest dynamic response.Figure 7
Simulation results under three bandwidths.As shown in Figure8, the PLL output cosθg enlarged 100 times is compared with va and vafund. Under these three bandwidths, the voltage amplitudes of cosθg, va,vafund remain unchanged with the increase of bandwidth. The voltage amplitude of cosθg is maintained at about 100 V, the vibration period has no change trend with the expansion of band width multiple, the time required for the period is 0.0025 s, and the phase-locked accuracy is high. THD of cosθg of PLL output under the three bandwidths is 0.97%, 0.98%, and 1.01%, respectively, which have good filtering effect.Figure 8
Simulation results of cosθg under three bandwidths: (a) fb = 100 Hz; (b) fb = 200 Hz; (c) fb = 300 Hz.
(a)(b)(c)Considering the dynamic response and filtering effect of the PLL, the bandwidth of the linear Kalman filter PLL is set to 200 Hz. Correspondingly, the parameters areR = 1, ϕ = π/3, and wn = 738.955.According to equation (13), k1 = 738.9553, k2 = 1,092,108.98,405, and k3 = 1,477.91.In [29], the solution of differential equations is used to judge the stability of the microgrid system. Since the stability of the system is independent of the input, let vα be 1 V, vα be 1 V, and sampling period Ts be 0.000,125 s. The Ode23tb function in Matlab is used to solve the solution of differential equations.Figure9 presents the solutions of the differential equations under different values of parameter k of A-type SOGI.Figure 9
Solutions of A-type SOGI differential equations: (a)k = 0.5; (b) k = 1; (c) k = 2; (d) k = 3; (e) k = 5.
(a)(b)(c)(d)(e)Figure10 provides the solutions of the differential equations when parameter k of B-type SOGI has different values.Figure 10
Solutions of the differential equations of B-type SOGI: (a)k = 0.5; (b) k = 1; (c) k = 2; (d) k = 3; (e) k = 5.
(a)(b)(c)(d)(e)Figure11 indicates the solutions of differential equations when parameter k of C-type SOGI has different values.Figure 11
Solutions of the differential equations of C-type SOGI: (a)k = 0.5; (b) k = 1; (c) k = 2; (d) k = 3; (e) k = 5.
(a)(b)(c)(d)(e)From Figures9–11, when k = 0.5, k = 1, k = 2, k = 3, and k = 5, x1∼x6 converge over time, while x7 diverges. However, x7 = θg, and it is a time-dependent variable, and x5 = 0. Besides, vq is a bounded quantity, as well as a margin of error, so the system is stable. It can be seen from Figure 10 that the transformation of all state variables converges with time, so the microgrid system is stable. Since the stability region of the system is a sufficient condition for the stability of the system, a conservative stability region can be selected, and k is stable at [0.5, 3]. Thus, the damping coefficient k of the three SOGIs is stable at [0.5, 3].


## 4. Simulation and Experimental Verification

The previous section concludes that the system parametersk1 = 738.9553, k2 = 1,092,108.98,405, k3 = 1,477.91, and Ts = 0.000,125 s, and k is stable within the range of [0.5, 3]. Then, Simulink is adopted to conduct the comparative simulation of A-type, B-type, and C-type SOGIs combined with linear Kalman filter PLLs.


### 4.1. Voltage Containing Harmonics of the Aviation Frequency Conversion Power Supply

In the three-phase balanced microgrid system, the A-phase voltage is represented by equation (25), the total voltage distortion rate is 10.8%, and the maximum single voltage distortion rate is 9.2%. Moreover, the fundamental wave frequency is 360∼800 Hz, and the change rate is a linear change of 200 Hz/s according to the standard of DO-160G.Whenk1 = 738.9553, k2 = 1,092,108.98,405, k3 = 1,477.91, and Ts = 0.000,125 s, the parameter k of three kinds of SOGIs is 1. Figure 12 illustrates the comparison of angular frequency and phase angle of the linear Kalman filter PLL without SOGI, PLL with A-type SOGI, PLL with B-type SOGI, and PLL with C-type SOGI.Figure 12
Simulation results of aviation frequency conversion power supply containing harmonics: (a)ωg; (b)θg (S represents SSLKF; K represents A-SOGI-SSLKF; M represents B-SOGI-SSLKF; N stands for C-SOGI-SSLKF).
(a)(b)Through Figure12, the angular frequency ωg output by the PLL ultimately changes linearly at a rate of 400 πrad/s2, and the phase angle θg also reaches a stable state. The PLLs with A-type SOGI and B-type SOGI achieve better linearity of the phase angle and a better restraining effect on the harmonic content of aviation frequency conversion power supply. In addition, the linear Kalman filter PLL with B type has better dynamic performance than that with A type.


### 4.2. Three-Phase Voltage Imbalance of Aviation Frequency Conversion Power Supply

The three-phase voltage is expressed as follows:(26)va=162.63cosωt,vb=187.03cosωt−120∘,vc=138.24cosωt+120∘.The voltage amplitude of the B phase increases by 15% compared with that of the A phase, and the voltage amplitude of the C phase decreases by 15% compared with that of the A phase. The fundamental wave frequency is 360∼800 Hz. According to the standard of DO-160G, the change rate is a linear change of 200 Hz/s.Figure13 shows that the angular frequency ωg output by the PLL ultimately changes linearly at a rate of 400 πrad/s2, and the phase angle θg also attains a stable state. Furthermore, the linear Kalman filter PLLs added three kinds of SOGIs that can restrain the three-phase voltage imbalance of aviation frequency conversion power supply.Figure 13
Simulation results of three-phase voltage imbalance of aviation inverter power: (a)ωg; (b)θg (S represents SSLKF; K represents A-SOGI-SSLKF; M represents B-SOGI-SSLKF; N stands for C-SOGI-SSLKF).
(a)(b)


### 4.3. The Three-Phase Voltage of Aviation Variable Frequency Power Supply Contains DC Component

The three-phase voltage is expressed as follows:(27)va=162.63cosωt+10,vb=162.63cosωt−120∘−10,vc=162.63cosωt+120∘−10.The aviation variable frequency power supply contains a DC component as shown in equation (27). The fundamental wave frequency is 360∼800 Hz, and the change rate is a linear change of 200 Hz/s according to DO-160G standard. The whole system parameters are shown in Section 4.1, and the simulation waveform is shown in Figure 14.Figure 14
Simulation results of three-phase voltage with DC component of aviation frequency converter: (a)ωg; (b)θg (S represents SSLKF; K represents A-SOGI-SSLKF; M represents B-SOGI-SSLKF; N stands for C-SOGI-SSLKF).
(a)(b)According to Figure14, the angular frequency ωg output by the PLL ultimately changes linearly at a rate of 400 πrad/s2, and the phase angle θg also attains a stable state. Besides, the linearity of the phase angle is excellent. However, the linear Kalman filter PLL with C-type SOGI fails to realize phase locking. This result indicates that the C-type SOGI has no inhibitory effect on the DC component. On the contrary, the linear Kalman filter PLL has a brilliant inhibitory effect on the DC component of the aviation frequency conversion power supply, and the A-type SOGI and B-type SOGI also have a practical inhibitory effect on the DC component.From the above simulation, it can be seen that A-type SOGI and B-type SOGI combined with the linear Kalman filter PLL can inhibit the high harmonic content, three-phase voltage imbalance, and DC component of the aviation variable frequency power supply voltage. Moreover, B-type SOGI has better dynamic performance. C-type SOGI can only suppress the three-phase voltage imbalance. In addition, the linear Kalman filter PLL can restrain the DC component.


## 4.1. Voltage Containing Harmonics of the Aviation Frequency Conversion Power Supply

In the three-phase balanced microgrid system, the A-phase voltage is represented by equation (25), the total voltage distortion rate is 10.8%, and the maximum single voltage distortion rate is 9.2%. Moreover, the fundamental wave frequency is 360∼800 Hz, and the change rate is a linear change of 200 Hz/s according to the standard of DO-160G.Whenk1 = 738.9553, k2 = 1,092,108.98,405, k3 = 1,477.91, and Ts = 0.000,125 s, the parameter k of three kinds of SOGIs is 1. Figure 12 illustrates the comparison of angular frequency and phase angle of the linear Kalman filter PLL without SOGI, PLL with A-type SOGI, PLL with B-type SOGI, and PLL with C-type SOGI.Figure 12
Simulation results of aviation frequency conversion power supply containing harmonics: (a)ωg; (b)θg (S represents SSLKF; K represents A-SOGI-SSLKF; M represents B-SOGI-SSLKF; N stands for C-SOGI-SSLKF).
(a)(b)Through Figure12, the angular frequency ωg output by the PLL ultimately changes linearly at a rate of 400 πrad/s2, and the phase angle θg also reaches a stable state. The PLLs with A-type SOGI and B-type SOGI achieve better linearity of the phase angle and a better restraining effect on the harmonic content of aviation frequency conversion power supply. In addition, the linear Kalman filter PLL with B type has better dynamic performance than that with A type.


## 4.2. Three-Phase Voltage Imbalance of Aviation Frequency Conversion Power Supply

The three-phase voltage is expressed as follows:(26)va=162.63cosωt,vb=187.03cosωt−120∘,vc=138.24cosωt+120∘.The voltage amplitude of the B phase increases by 15% compared with that of the A phase, and the voltage amplitude of the C phase decreases by 15% compared with that of the A phase. The fundamental wave frequency is 360∼800 Hz. According to the standard of DO-160G, the change rate is a linear change of 200 Hz/s.Figure13 shows that the angular frequency ωg output by the PLL ultimately changes linearly at a rate of 400 πrad/s2, and the phase angle θg also attains a stable state. Furthermore, the linear Kalman filter PLLs added three kinds of SOGIs that can restrain the three-phase voltage imbalance of aviation frequency conversion power supply.Figure 13
Simulation results of three-phase voltage imbalance of aviation inverter power: (a)ωg; (b)θg (S represents SSLKF; K represents A-SOGI-SSLKF; M represents B-SOGI-SSLKF; N stands for C-SOGI-SSLKF).
(a)(b)


## 4.3. The Three-Phase Voltage of Aviation Variable Frequency Power Supply Contains DC Component

The three-phase voltage is expressed as follows:(27)va=162.63cosωt+10,vb=162.63cosωt−120∘−10,vc=162.63cosωt+120∘−10.The aviation variable frequency power supply contains a DC component as shown in equation (27). The fundamental wave frequency is 360∼800 Hz, and the change rate is a linear change of 200 Hz/s according to DO-160G standard. The whole system parameters are shown in Section 4.1, and the simulation waveform is shown in Figure 14.Figure 14
Simulation results of three-phase voltage with DC component of aviation frequency converter: (a)ωg; (b)θg (S represents SSLKF; K represents A-SOGI-SSLKF; M represents B-SOGI-SSLKF; N stands for C-SOGI-SSLKF).
(a)(b)According to Figure14, the angular frequency ωg output by the PLL ultimately changes linearly at a rate of 400 πrad/s2, and the phase angle θg also attains a stable state. Besides, the linearity of the phase angle is excellent. However, the linear Kalman filter PLL with C-type SOGI fails to realize phase locking. This result indicates that the C-type SOGI has no inhibitory effect on the DC component. On the contrary, the linear Kalman filter PLL has a brilliant inhibitory effect on the DC component of the aviation frequency conversion power supply, and the A-type SOGI and B-type SOGI also have a practical inhibitory effect on the DC component.From the above simulation, it can be seen that A-type SOGI and B-type SOGI combined with the linear Kalman filter PLL can inhibit the high harmonic content, three-phase voltage imbalance, and DC component of the aviation variable frequency power supply voltage. Moreover, B-type SOGI has better dynamic performance. C-type SOGI can only suppress the three-phase voltage imbalance. In addition, the linear Kalman filter PLL can restrain the DC component.


## 5. Conclusion

Abundant distributed generators need to be connected to the power grid through the converter as the power interface, while the current source converter needs the external power grid to provide a stable reference voltage and synchronize with the power grid voltage through the phase-locked loop. The present work aims to solve the existing problems of aviation frequent conversion power supply in the microgrid, such as excessive harmonics, voltage imbalance, and DC component, to guarantee the efficient and stable flight of the aircraft, unmanned aerial vehicle, and other aircraft. Therefore, SOGIs of three structures are integrated with the linear Kalman filter PLL. Moreover, for the high-order PLL system with strong nonlinearity, the state equations of the whole PLL are derived, and a stable region of the system is obtained by the solution of the state equations. Finally, simulation and experimental verification are carried out in this stable region to select the appropriate SOGI and linear Kalman filter PLL for different aviation power supply voltages to achieve precise phase locking. The different factors and influencing conditions of the studied dynamic high-order PLL system are analyzed after setting fixed parameters based on laboratory equipment. In specific application, it should be combined with the environment and physical limitations of converter in aviation variable frequency power supply, and the corresponding coefficient setting limits need to be further studied.



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*Source: 6703595-2022-02-12.xml*