# A Robust Control for an Aerial Robot Quadrotor under Wind Gusts

Authors: Li Ding; Zhenwei Wang
Journal: Journal of Robotics
 (2018)

---

## Abstract

A robust flight controller based on linear active disturbance rejection control (LADRC) is proposed for stability control of an aerial robot quadrotor under wind gusts. The nonlinear dynamical model of the quadrotor, considering the wind disturbance, is firstly established through Newton-Euler method. Subsequently, a robust LADRC technique is proposed to design the controllers for the inner loop and outer loop of the aircraft. In this control scheme, the linear extended state observer (LESO) serves as a compensator which can effectively reject the wind gusts. Then, a method of parameter tuning is introduced to obtain the optimized control performance. Finally, the effectiveness and advantages of the proposed controller are demonstrated through series of simulation case.


---

## Body

## 1. Introduction

Quadrotor is the most popular configuration of multirotor unmanned aerial robot, extensively for civilian applications [1, 2]. In recent years, significant growth of interest is witnessed towards the academic research of the quadrotor. This is possibly attributed to their certain features, such as simple mechanical structure, hovering, and agile maneuverability. With the increasing requirement of autonomous flight under different conditions, control of the quadrotor is an important challenge. Complex rotation and translation operations are also commonly encountered in the mathematical model, resulting in complex equations that have to be taken into account when designing control laws. On the other hand, the position control and attitude control of the quadrotor are extremely sensitive to external disturbance, such as wind gusts. Particularly, robustness issues may be critical for the control of quadrotor since they are subjected to the complicated dynamics and external disturbances. Several proper control methodologies for the quadrotor have been reported in the literatures, such as proportion integration differentiation (PID) control [3], backstepping control [4], sliding mode control [5], and model predictive control [6]. Nevertheless, there are a few researches about the robust control of the quadrotor, especially under the wind gusts.In order to weaken the effect of wind gusts, some authors have proposed complicated control techniques to achieve stability. In the literatures [7, 8], adaptive controllers of different structures were verified by simulations and experiments on test bench. For control of a multirotor aircraft, Salazar et al. [9] proposed a novel mathematical model of the wind gusts and designed a simple nonlinear control law to resist the wind disturbance. The effect of wind disturbance was discussed towards the issue of (unmanned air vehicle) UAV path planning in the literatures [10, 11]. From the analysis, compensation control for the aircraft may be an effective method. Dong et al. [12] designed a flight controller with disturbance observer (DOB) to guarantee the high-performance trajectory tracking of a quadrotor. The DOB-based controller is robust to wind gusts without the use of high control gain or extensive computational power.Our team has proposed in previous articles, like [13], the use of LADRC to control a small-scale unmanned helicopter. This control strategy is rooted in active disturbance rejection control (ADRC) which was firstly proposed by Han [14]. LADRC is a simplified implementation of the ADRC, in which bandwidth is the only adjustable parameter of the control performance. A previous contribution from our team presented the parameter tuning towards the LADRC based on the artificial bee colony algorithm [15]. Detailed background and principles on the ABC can be found in the literatures [16, 17], and the authors analyzed the performance of the ABC on optimization problem.The content is organized in the following manner: Section2 presents the mathematical model of the quadrotor under the wind gusts. In Section 3, the robust controller is described using the LADRC strategy. And the proof of the stability analysis for the proposed controller is given in Section 4. A method of parameter tuning is applied in Section 5, to optimize the performance of our proposed controller. The control law with wind gusts is simulated and illustrated in Section 6. Finally, our conclusions and contributions are discussed in Section 7.


## 2. Mathematical Model

The free body diagram and coordinate systems for the quadrotor are given in Figure1. It is controlled by the angular speeds of four electric motors. Each motor produces a thrust and a torque mi  (i=1,2,3,4), whose combination generates the main thrust input U1, pitch input U2, roll input U3, and yaw input U4. Two reference frames are subjected to the quadrotor, namely, the earth-fixed frame {OEXEYEZE} and the body-fixed frame {OBXBYBZB}. The position (x,y,z), attitude (pitch θ, roll ϕ and yaw ψ), and motion can be achieved through the two frames. According to Newton-Euler method. The six-degrees-of-freedom dynamics of the quadrotor are modeled as [18](1)x¨=U1cψsθcϕ+sψsϕmy¨=U1sψsθcϕ-cψsϕmz¨=U1cϕcθm-gϕ¨=U2Ixx+θ˙ψ˙Iyy-IzzIxxθ¨=U3Iyy+ϕ˙ψ˙Izz-IxxIyyψ¨=U4Izz+ϕ˙θ˙Ixx-IyyIzzwhere Ixx, Iyy, and Izz are the moment of inertia, m is the mass, and g is the gravitational acceleration. And sα and cα are the abbreviations for cos⁡α and sin⁡α.Figure 1
Free body diagram of quadrotor.The thrust of each propeller is calculated byfmi=ktωi2  (i=1,2,3,4) with kt being the thrust coefficient and ωi being the angular speeds. The relationship between the four inputs and angular speed is expressed by(2)U1U2U3U4=ktktktkt0-ktl0ktl-ktl0ktl0-kmkm-kmkmω12ω22ω32ω42where l denotes the distance from the center of mass to the center of the propeller and km is termed as antitorque coefficient.In the outdoor flight, the quadrotor is generally exposed to lateral wind gusts. The aircraft will be yawed or overturned if it is subjected to the lateral wind gusts. Stating precisely, this leads to additional lateral air flow acting on the propeller, as shown in Figure2. Hence, the total thrust fTi=fmi+fwi  (i=1,2,3,4) could be described as [19](3)fTi=2ρAV^Vpwhere ρ is the air density and A is the propeller area. Vp is the induced wind speed of the propeller and V^ is the total wind induced speed of the rotor. The relationship between them is given by(4)V^=Vwcos⁡α+Vp2+Vwsin⁡α21/2where α represents the angle between the propeller axis and the lateral wind gusts. Since the latter is perpendicular to the former, α = 90°. At this moment, the additional lateral forces are expressed by(5)fwi=2ρAVp21+Vw2Vp21/2-fmiFigure 2
Analysis of the main and lateral thrusts.Moreover, the aerodynamics drag is defined asmdrag=ρAVw2/2=kdragVw2, where kdrag>0 is a constant depending on the parameter ρ, shape of the blade, and other factors. When the aircraft is disturbed by the lateral wind gusts, the additional torques acting on the propellers are represented by(6)mwϕmwθmwψ=fw4-fw2lfw3-fw1l∑i=14mdragiUsing (1), (5), and (6), the integrated quadrotor dynamical model can be rewritten as (7)x¨=U1cψsθcϕ+sψsϕm+∑i=14fwimy¨=U1sψsθcϕ-cψsϕm+∑i=14fwimz¨=U1cϕcθm-g+∑i=14fwimϕ¨=U2Ixx+θ˙ψ˙Iyy-IzzIxx+mwϕIxxθ¨=U3Iyy+ϕ˙ψ˙Izz-IxxIyy+mwθIyyψ¨=U4Izz+ϕ˙θ˙Ixx-IyyIzz+mwψIzz


## 3. Robust Controller Design

According to (7), the input and output of each control channel present second-order derivative relation. Thus, we use the second-order system in the following form for describing the LADRC:(8)x¨s=fsxs,x˙s,ws,t+btuys=xswhere u and ys denote input and output, respectively. fs is the external disturbance. xs is state variables and b(t) is the control function.Supposeb0 is the approximate value of b(t), and (8) is written equivalently as(9)x¨s=fsxs,x˙s,ws,t+b0u=fs+b0uys=xsBy rewriting the above equation in the form of differential equation, one has(10)x˙s1=xs2x˙s2=xs3+b0ux˙s3=hys=xs1with xs3=fs added as an augmented state and h=f˙s as unknown disturbance. Now fs can be estimated through a state observer based on a state space model:(11)x˙=Ax+Bu+Ehy=Cxwhere(12)A=010001000,B=0b00,C=100,E=001The LESO of (11) can be constructed as(13)z˙=Az+Bu+Ly-y^y^=Czwhere L is the observer gain. It is calculated as [17](14)L=l1l2l3=α1ωoα2ωo2α3ωo3where ωo>0 is the observer bandwidth. It results in the characteristic polynomial of (13) being(15)λs=s3+α1s2+α2s+α3=s+ωo3From the polynomial, one obtains(16)α1=3,α2=3,α3=1The observer can track the state variables with well-tuned observer bandwidth and yieldz1(t)→y^(t),  z2(t)→y^˙(t), and  z3(t)→fs.With the estimate offs, the LADRC can actively compensate for effect of the external disturbance in real time as(17)u=u0-z3b0The closed-loop control system is converted into a unit double integral plant. And the control law is [20, 21](18)y¨=f-z3+u0≈u0=λ1re-z1-λ2z2where re is the reference signal.The transfer function of the second-order plant is given as(19)G2=λ1s2+λ2s+λ1Here, the gains can be calculated as [17](20)λ1=ωc2,λ2=2ωc


## 4. Stability Analysis

Define the error as(21)e=x-zSubtracting (13) from (11), the error equation is obtained as(22)e˙=Aee+Ehwhere(23)Ae=A-LC=-l110-l201-l300Obviously, the LESO is bounded-input bounded-output (BIBO) stable if the roots of the characteristic polynomial, namely (15), are all in the left half plane and h is bounded.Theorem 1.
The design of LADRC from (13) to (18) yields a BIBO stable closed-loop system if the LESO and the control law for the unit double integral plant are stable.Proof.
According to (17) and (18), one has(24)u=1b0-λ1-λ2-1z1-rez2z3=Qz-1b0re00=Qz-Gwhere(25)Q=1b0-λ1-λ2-1
The closed-loop control system is rewritten as(26)x˙=Ax+Bu+Eh=Ax+BQz-BG+Eh(27)z˙=Az+Bu+Ly-y^=LCx+A-LC+BQz-BG
Using the state space equation to represent the closed-loop control system, one gets(28)x˙z˙=ABQLCA-LC+BQxz+-BE-B0Gh
Similarly, the control system is BIBO stable if the eigenvalues of (28) are in the left half plane. Since the reference signal re is always bounded, with the condition that the disturbance fs satisfies differentiable, h is bounded.


## 5. Parameter Tuning

According to the previous analysis, the control structure of the quadrotor is divided into two loops, i.e., inner loop and outer loop. The block diagram of such a structure is schematically shown in Figure3. In the outer loop, the position vector Pr and yaw angle ψr are chosen as the reference signals. In the inner loop, the reference signal (θr,ϕr,ψr) comes from the outer loop. Moreover, the four inputs generated by the two loops are converted into the angular speeds of motors.Figure 3
Control system architecture of the quadrotor.The evaluation function is crucial for the parameter tuning. Consequently, an improved integral of time multiplied by absolute error (IITAE) is employed as performance index. The evaluation function of the performance index is defined as(29)Ft=α1∫0∞tetdt+α2∫0∞ut2dt+α3ts+α4owhere e(t) is the error signal in the time domain, ts is the settling time, os is the overshoot, and α1, α2, α3, and α4 are the weight coefficients. Note that the parameter tuning of the LADRC is conducted by the ABC algorithm, and the exhaustive process is reported in the literature [13], and here repeating is unnecessary.As taking the inner loop as an instance, the reference signal is set to 1 rad, 1 rad, 1 rad. There are three second-order LADRC in the inner loop, i.e.,θ-LADRC, ϕ-LADRC, and ψ-LADRC. The physical parameters of the quadrotor are listed in Table 1. We use the ABC algorithm to tune the unknown control parameters under a unit step response case. The number of the iterations is 100. In addition, the simulation parameters of the wind gusts are given as ρ=1.293g/L, A=0.0016m2, VP=2m/s, and Vw=6m/s. And a white noise with the amplitude of 0.2 rad is added to the measured ports. The simulation time lasts for 6s. Figure 4 displays the evolving curves of the control parameters, which indicates the process of the parameter tuning by ABC. The attitude response is shown in Figure 5. It is obvious that the LADRC has a satisfactory performance of wind resistance, and the steady state error is less than 2%. Furthermore, the responses of the three attitude channels are fast and accurate.Table 1
Physical parameters.
Item Quantity L (m) 0.2053 m (kg) 1.923 I x x (kg⋅m2) 0.094 I y y (kg⋅m2) 0.094 I z z (kg⋅m2) 0.086Figure 4
Evolving curves of the control parameters.Figure 5
Response of the attitude.


## 6. Simulation Results

In order to validate the robustness and wind resistance of the proposed control scheme for stabilizing the quadrotor at trajectory tracking, the simulation is conducted in MATLAB 2017a programming environment on an Intel Core i7-4720 PC running Windows 10. Similarly, random wind gusts are added to the input of the outer loop.As pointed out in Section5, the control parameters of the outer loop controller are also tuned by the ABC algorithm. The tuned parameters are shown in Figure 6 using a unit step response case.Figure 6
Tuned parameters of outer loop controller.Moreover, we introduce a PID controller from the literature [22] as a comparison to test the robustness of our proposed controller. In the comparative simulation, the quadrotor follows a referenced trajectory of z direction as shown in Figure 7. Meanwhile, lateral wind gusts are applied with different wind speeds at a specific time period 8 s-12 s. The PID and LADRC are applied to stabilize the position of the aircraft, respectively. From the result, the response of LADRC is slightly faster than that of PID. As the wind speed increases, the tracking error becomes bigger. Nevertheless, it is obvious that the steady state error of LADRC is smaller than that of PID due to the LESO. In conclusion, the LADRC has a strong ability of wind disturbance compensation.Figure 7
Position response under different wind gusts.
(a)
V w = 4m/s (b)
V w = 10m/sLastly, a visual simulation is run in the MATALB/Simscape environment to display the trajectory tracking of the quadrotor. Note that the Simscape link utility creates a physical modeling XML file that represents the quadrotor’s parts as bodies and maps the constraints between the parts into joints [23]. In this case, the task requires that the quadrotor takes off from the ground and flies in hover. The simulation time lasts for 8s. From the result in Figure 8, the quadrotor has a stable flight performance based on the proposed controller.Figure 8
Hovering control in Simscape environment.
(a)
Time=0s (b)
Time=6s


## 7. Conclusion

A new LADRC control scheme is given for the stability control of an aerial robot quadrotor under wind gusts in this article. The proposed controller roughly has two parts: the LESO part applied to properly estimate and compensate the wind disturbance leading to an attractive model-free feature and a PD part applied to ensure satisfactory control performance. Moreover, corresponding stability of the closed-loop control plant is analyzed and an ABC algorithm is applied for parameter tuning of the LADRC. Finally, all the simulation results show the proposed controller has a better ability of resisting wind gusts comparing to the traditional PID.In the future, more advanced control strategies such as that reported in the literature [24] will be studied to control the movement of the quadrotor under wind gusts.



---

*Source: 5607362-2018-08-01.xml*