# Nonlinear Output Regulation with Input Delay and Application in AHV Attitude Control

Authors: Liang Cai; Qingxian Wu
Journal: International Journal of Aerospace Engineering
 (2017)

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## Abstract

Time delay phenomena exist almost everywhere in the actual world and are especially important in the control of an AHV. The small time delay usually ignored in control may cause quite obvious errors in the flight trajectory tracking, because of the extremely high flight speed. In this paper, a new framework of solving a nonlinear input delay regulation problem is proposed for the first time, which is comprised of nonlinear damping controllers, nonlinear disturbance observers, and a nonlinear time delay predictor-based compensator, under the proved separation principle. Then the attitude tracking control of an AHV with a known time-varying input delay is studied based on the proposed design framework. Simulation results show the advantage of the proposed control method.


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## Body

## 1. Introduction

Tracking and disturbance rejection, usually coexisting as the aims of system control, can be treated uniformly in the output regulation problem framework [1]. This has been studied for decades [2]. For linear systems, Francis [3] illustrates that the output regulation problem could be solved based on the internal model principle. In [3], it is found that the solvability of the regulation problem is equal to that of a set of linear equations named the regulation equations. Since the 1990s, the research of output regulation of nonlinear systems has been concentrated on. In [4], Isidori and Byrnes show the equivalency between the solvability of nonlinear output regulation problems and that of a set of partial differential equations, called the regulation equations in nonlinear form or Francis-Isidori-Byrnes (FIB) equations. Recently, a general framework for output regulation problems is proposed and some general results are obtained in [5]. Depending on different research focuses, regulation problems can be divided into several types [6]: output regulation without robust [7], locally robust output regulation [8], globally robust output regulation [9, 10], and semiglobally robust output regulation [11]. Output regulation problems have also been developed by broadening the range of systems, not only from linear systems to nonlinear ones but also from the ones with uncertainties just in the controlled system to those with uncertainties both in the controlled system and in the exosystem, even including some other types such as time-varying systems or distributed systems [12, 13]. When the uncertainty only exists in controlled systems, as long as an effective internal model has already been constructed [14], well-developed robust techniques, such as the small gain theory and the sliding mode control, can be used to treat the uncertainty. When there are uncertainties in the exosystem, many valuable attempts have been done in [15–17]. Dynamic high gains and self-tuning regulators can be used to treat the uncertainties with unknown upper bound and parameter uncertainties in the exosystem [18, 19]. If the direction of control is unknown, the Nussbaum gain method [20, 21] is suitable to use. Treating uncertainties in the output regulation problem usually involve the estimation of unknown parameters. It is a quite important and difficult issue to assure the estimation value reaching the parameters’ actual value. A research on this topic is given in [22]. Besides uncertainties, other terms, such as time delay, could also be brought into the systems.Time delay phenomena exist almost everywhere in the actual world, such as actuator and sensor delays, but fall outside the scope of the standard finite-dimensional systems. In the analysis and synthesis of time delay linear systems, quite a lot of results have been given in [23, 24]. Mainly used methods for the analysis and synthesis include character roots distribution in the frequency field [25], robust stabilization based on the small gain theory [26], the Lyapunov-Krasovskii functional theorem [27], the Lyapunov-Razumikhin function theorem [28], and the free weighting matrices technique [29] based on model transforming [30]. To treat cross-terms in the derivatives of the Lyapunov functions or functionals, several inequations are used, such as the standard inequation (Young’s inequation), Park’s inequation [31], Moon’s inequation [32], and Jasen’s integral inequation [33]. With the developing of nonlinear system theories, expanding the scope of delayed systems to nonlinear systems has aroused great interests. There are some results for specific nonlinear systems [34–37], and they are mainly focused on analysis and control design of retard delay systems. For linear systems with input delay, they can be treated by transforming the input delay into the state delay and then giving the controllers in the form of LMIs. It is much more difficult to treat nonlinear systems with input delay. For nonlinear delay systems, it is impossible to cancel out nonlinear terms using a delayed input and difficult to solve NMIs to assure the stability of the closed loop. Only recently, a few methods exist in dealing with stabilization of nonlinear systems with input delay [38–46]. Among them, the predictor-based compensation method [41–46] is particularly useful, because compensators can be well combined with controllers to achieve multiple control targets.To our knowledge, the nonlinear output regulation problem with input time delay has been little studied. When the nonlinear regulation equations contain delay terms, it is impossible to get an analytic solution. In order to bypass solving regulation equations, observers can be used as a special kind of internal models [47, 48]. There are only a few papers on the output regulation problem of delay systems, both for linear systems and nonlinear systems with delay [49, 50], and none of them deals with input delay. The main novelty in this article is a new framework of solving a nonlinear input delay regulation problem for the first time, which consists of nonlinear damping controllers, nonlinear disturbance observers, and a nonlinear time delay compensator, under the proved separation principle.Recently, the flight control of air-breathing hypersonic vehicles (AHVs) attracts more and more research interests. There are some results on the topic, such as the flight control based on the dynamic inversion, the adaptive control, the sliding mode control, and the backstepping method [51, 52]. Some features which are not so significant for common aircrafts become quite important for AHVs, such as nonlinearity and time delay. Small time delays usually ignored in control may cause quite obvious errors in the flight trajectory tracking, because of the extremely high flight speed. In this paper, the attitude tracking control of an AHV with input delay is studied for the first time, which is not seen elsewhere. The attitude tracking controller is derived based on the proposed design framework. The problem description is presented in the Section 2, and then the input delay compensation method is given in Section 3. In Section 4, the design of a time delay compensation controller for a class of nonlinear systems is presented and the controller’s performance is summarized as theorems. Then, in Section 5, the controller is applied to the attitude control of an AHV, and simulation results show that the disturbance rejection and input time delay compensation controller for the AHV attitude tracking is effective.


## 2. Problem Formulation

Consider a class of strict feedback MIMO nonlinear system with a time-varying input delay described as below:(1)x˙1=f1x1+g1x1x2+g1dx1d,⋮x˙i=fix1,…,xi+gix1,…,xixi+1+gidx1,…,xid,⋮x˙n=fnx1,x2,…,xn+gnx1,x2,…,xnut-Dt+gndx1,x2,…,xnd,e=x1-yr,where the state vector xi∈Rk, the whole state vector x=[x1,…,xn]∈Rnk, the input u∈Rk, a reference signal yr∈Rk, the time delay function Dt is accurately known, and fix1,…,xi, gix1,…,xi, and gidx1,…,xi are all known and locally Lipschitz. The unknown disturbance d∈Rm is produced by the autonomous exosystem(2)ξ˙=Aξ,d=Cξ,where the state vector ξ∈Rm and eigenvalues of the matrix A are all on the imaginary axis, which means the system is neutrally stable. Matrices C,A are known and observable. Here, the disturbances in different subsystems are the same. Actually, different disturbances can be combined into the same form by appropriately choosing the matrix gidx1,…,xi.The control object is to make the closed loop system internally stable and the regulation outputlimt→∞⁡e→0.For system (1), in order to continue with analysis and design, some assumptions are described as below.Assumption 1.
(1) The states x are all measurable.
(2) In the field of definition, the control or virtual control gain matrix gix1,x2,…,xi is always invertible.Assumption 2 (see [41]).
The open loop system, formulated as (1), when Dt≡0, is strongly forward complete.Assumption 3 (see [41]).
The time functionϕ(t)=t-D(t) has these properties: when t≥0, ϕ(t)≤t and ϕ′(t)>0.Remark 4.
(1) The forward completeness in Assumption 2 is used to keep the open loop system out of the systems with the finite time escape property. In order to achieve effective control, the feedback signal from the controller must reach the system in time, which is impossible for systems with finite time escape property.
(2) In Assumption 3, the property ϕ(t)≤t makes the system delay function always having positive value, and the property ϕ′(t)>0 makes the signals sequentially injected into the system via input ports, which means that there are no feedback state values taken by the controller earlier but injected into the system later.


## 3. Input Time Delay Compensation

Consider an input delay nonlinear system, where the delay value is time varying and known asD(t), described as below:(3)x˙t=fopxt,ut-Dt.In the system, states x∈Rn, the control input u∈Rm, t∈R+, and the differentiable function fop go through the origin.In order to adopt delay compensation, besides satisfying Assumptions2 and 3, the open loop system without input delay needs to be asymptotically stabilizable, which is guaranteed by the following assumption in a stronger form.Assumption 5 (see [41]).
There exists a bounded feedback controllerk∈C1(R+×Rn,Rm), which makes the nondelay (when D(t)≡0) closed loop system x˙(t)=fop(xt,k(t,x(t))+ω(t)) ISS stable with respect to the additional input ω(t).With system (3) satisfying Assumptions 2 and 3 and a controller u(t)=k(t,x) satisfying Assumption 5, a delay compensating controller for system (3) is given as(4)ut=kϕ-1t,Pt,where P(t) makes the following equation hold:(5)Pt=ϕ-1t-t∫01fopPϕt+yϕ-1t-t,uϕt+yϕ-1t-tdy+xt=∫ϕttfopPσ,uσdσϕ′ϕ-1σ+xt.The delay compensation control method is described as above and its performance is summarized as Lemma 6.Lemma 6 (see [41]).
With system (3), satisfying Assumptions 2 and 3, and a controller satisfying Assumption 5, a delay compensation controller ((4), (5)) makes the following inequation hold, where α is a KL function:(6)xt+supϕt≤θ≤t⁡uθ≤αx0+supϕt≤θ≤0⁡uθ,t,t≥0.


## 4. Solution of the Nonlinear Regulation Problem with Input Delay

In this paper, for the signal to be tracked, we adopt the setting of the precise tracking: the signal to be tracked is explicitly known, whose derivations of enough high degrees can be easily obtained. The tracking and disturbance rejection problem is then transformed into the disturbance rejection problem of the tracking error system, which is a special case of the regulation problems.Under the setting of precise tracking, the tracking error system is naturally a time-varying or parameter-varying system. For the tracking error system, in the design process the time-varying terms can always be cancelled out, which makes the Lyapunov function positive definite and its derivative negative definite uniformly with respect to time. According to the LaSalle-Yoshizawa theorem, it makes the design and proof process have no difference from a time-invariant system. So, in this paper, we treat all the systems as time-invariant systems.To solve the output regulation problem, the controller can be divided into two parts, and we design the controller in two steps [6]. If the disturbance d is measured, the steady controller can be directly formulated as a static function cd. When the disturbance d is unmeasurable, after constructing an observer to asymptotically estimate the actual value of disturbance, the regulation problem can be solved by designing an observer-based controller cd^. In other words, a disturbance observer is a qualified candidate for the internal model.


### 4.1. Disturbance Observer

The disturbance observer for nonlinear systems is firstly presented by Chen in [53]. Here, a disturbance observer is presented with a different assumption and observer gain. Consider a nonlinear system:(7)x˙t=fx+guxu+gdxd,y=x,where the states x∈Rn, input u∈Rk, and measured output y∈Rn. The matrices fx, gux, and gdx are all locally Lipschitz. The gain matrix gux is always invertible. The disturbance d comes from exosystem (2). In order to design a disturbance observer, we make the following assumption.Assumption 7.
For system (7), the gain matrix gdx is known and globally invertible in the whole domain of definition.
Then, a disturbance observer is presented as below:(8)z˙=A-lxgdxCz+Apx-lxgdxCpx+fx+guxu,ξ^=z+px,d^=Cξ^,where the term lx satisfies(9)lx=∂px∂x=Kgd-1x.The observer designed above can estimate the disturbance d exponentially as summarized in the following theorem.Theorem 8.
Considering system (7), where the disturbance d is the output of exosystem (2), when Assumption 7 is satisfied, there exist a matrix K and an observer ((8), (9)) whose output is exponentially convergent to the actual disturbance d, uniformly for x.Proof.
Select a candidate for the Lyapunov function:(10)Vo=12eTe=12ξ-ξ^Tξ-ξ^.We have(11)V˙o=eTAξ-z˙-p˙x=eTAξ-A-lxgdxCz-Apx+⋯+eTlxgdxCpx+fx+guxu-∂px∂xx˙=eTAξ-z-px+lxgdxCz+gdxCpx+fx+guxu-lxx˙=eTAe+lxgdxd^+fx+guxu-x˙=eTAe-lxgdxCe=eTA-lxgdxCe.According to Assumption 7 and because C,A is observable, for any negative definite matrix -Q-εI, ε>0, there exists a matrix K making lx=Kgd-1x and the following holds:(12)V˙o=eTA-lxgdxCe=eTA-KCe=eT-Q-εIe<-eTQe.With the customized positive definite matrix Q, we can easily choose Q=ε1I, ε1>0, which makes(13)V˙o<-ε1Vo.Then states of observer ((8), (9)) are exponentially convergent to the exostates of the exosystem, uniformly for x. This also makes the estimation d^ exponentially convergent to the actual disturbance d.Remark 9.
(1) The controller u in system (7) or in observer (8) can be of any form, such as controllers with time delay or a state usually treated as a virtual controller in the backstepping method, as long as it is known.
(2) In Chen’s design [53], the object system needs to be made passive by output feedback, and the observer gain matrix is designed by partial derivate. The design used in this paper needs the actual value of the invertible disturbance gain matrix and does not need any assumption about passivity.


### 4.2. Separation Principle

The separate principle does not hold for general nonlinear systems, and then the controllers and observers must be designed simultaneously using a single Lyapunov function for the augmented system consisting of the controlled system and the observer. Actually, the nonlinear separation principle is available, according to the Lyapunov stability theorem, when observer errors themselves are asymptotically convergent, and their transition processes do not destabilize the systems controlled by estimated-states feedback controllers. Here, we give a sufficient condition for the separation principle when dealing with a class of nonlinear system described as (7).Theorem 10.
For system (7), if the disturbance d is measured and a controller utempx,d can globally asymptotically stabilize the system; then with an additional input v and an estimate d^ of d, there exist a controller ucx,d^ making system (14) ISS with respect to v,d~; furthermore if the estimation d^ is exponentially convergent to the disturbance d and, in system (14), the input-to-states gain λ2-1 with respect to d~ satisfies λ2-1I<CTC, then ucx,d^ asymptotically stabilize the augmented system of (7) and the disturbance estimation error system, which means the separation principle is available.(14)x˙t=fx+guxuc+v+gdxd^+gdxd~,y=x.Proof.
Whend is known there exists the controller utempx,d globally asymptotically stabilizing system (7) and then there is a Lyapunov function Vx, which makes(15)α_x≤Vx≤α-x,∂Vx∂xfx+guxutempx,d+gdxd≤-βx,where α_, α-, and β belong to the K-class functions.
Invokeucx,d^=utempx,d^+uadx,d^ into system (14), and then we have(16)x˙t=fx+guxutempx,d^+gdxd^+⋯+guxuadx,d^+guxv+gdxd~.Invoking the controller(17)uadx,d^=-c1guTx+c2gu-1xgdxgdTx∂Vx∂xT.utemp in equation (16) is different from the one in equation (15), and we can put the difference term utempx,d-utempx,d^ into the additional input v. Then utemp in (18) can be treated the same as the one in (15). The derivative of the Lyapunov function candidate Vx along the system (16) satisfies(18)V˙x=∂Vx∂xfx+guxutemp+gdxd^+guxuad+guxv+gdxd~≤-βx+∂Vx∂x-c1gu2x+c2gd2x∂Vx∂xT+guxv+gdxd~≤-βx-c1∂Vx∂xgux2-c2∂Vx∂xgdx2+λ1∂Vx∂xgux2+⋯+λ1-1v2+λ2∂Vx∂xgdx2+λ2-1d~2≤-βx-c1-λ1∂Vx∂xgux2-c2-λ2∂Vx∂xgdx2+⋯+λ1-1v2+λ2-1d~2,where the scalars c1 and c2 are designing parameters. Given any λ1>0 and λ2>0, select c1 and c2 making inequations c1-λ1>0 and c2-λ2>0 hold, and then we have(19)V˙x≤-βx-c1-λ1∂Vx∂xgux2-c2-λ2∂Vx∂xgdx2+⋯+λ1-1v2+λ2-1d~2<-βx+λ1-1v2+λ2-1d~2.It shows system (14) is ISS with respect to v,d~.
When the observer error is exponentially convergent uniformly, according to the proof of Theorem8, the Lyapunov function Vo=1/2eTe, and its derivative V˙o<-eTQe. Because C,A is observable, so the matrix CTC is positive definite. Then, take a Lyapunov function candidate(20)Vd=12eTCTCe=12d~Td~.We have(21)V˙d=eTCTCe˙<-eTCTCQe.With Q selectable, choose Q=CTC>μI, where μ is a positive constant. Then we have(22)V˙d<-eTCTCCTCe=-d~TCCTd~T<-μd~2.The original system to be controlled and the dynamic of the disturbance observer error form the augmented system with augmented states x,d~. Take a candidate for Lyapunov function of the augmented system as Vx,d~=Vd+V, whose derivative shows(23)V˙x,d~=V˙d+V˙<-βx+λ1-1v2+λ2-1d~2-μd~2.If v=0, the value of λ2-1 can be set as λ2-1=μ-μ0, μ0>0, and then(24)V˙x,d~<-βx-μ0d~2.So, when the observer states are exponentially convergent to the exostates of exosystem uniformly for x and the input-to-states gain λ2-1 with respect to d~ satisfies λ2-1I<CTC, controller (25) asymptotically stabilizes the augmented system of (7) and the dynamic of the disturbance observer error. The separation principle is available.(25)ucx,d^=utempx,d^-c1guTx+c2gu-1xgdxgdTx∂Vx∂xT.Remark 11.
The IS-gainλ2-1 can be easily designed to satisfy the condition λ2-1I<CTC. This condition is nontrivial and can not be ignored.


### 4.3. Controller Design and Stability Analysis

In order to solve the regulation problem described in Section2, we firstly solve the regulation problem without input delay, as D(t)≡0, and design a controller based on the backstepping method and the disturbance observer; then, using the ISS property of the designed controller we construct the final delay compensation controller based on Lemma 6.For system (1), reference signal yr and its derivation yri are all known, and a tracking controller with ISS properties is designed as follows.In the first step, define the output tracking error asz1=x1-yr, and its dynamic is described as(26)z˙1=x˙1-y˙r=f1x1+g1x1x2+g1dx1d-y˙r.Define a virtual controller a1: (27)z˙1=f1x1+g1x1a1+x2-a1+g1dx1d-y˙r.Then, define a tracking error with respect to the virtual controller as z2=x2-a1, and we have(28)z˙1=f1x1+g1x1a1+z2+g1dx1d-y˙r.Using an exponentially convergent disturbance observer and according to Theorem 10, there exists a virtual controller a1yr,y˙r,x1,d^ described as below:(29)a1=utemp1-ca1g1Tx1+cca1g1-1x1g1dx1g1dTx1∂V1z1∂z1Twhich makes z1 subsystem ISS with respect to z2 and d~, where d^ and d~=d-d^ are the estimate value of d and its estimate error, respectively. In (29), V1z1 is a CLF (Control Lyapunov Function) for z1 subsystem and utemp1yr,y˙r,x1,d^ is an arbitrary asymptotical stabilizer. They can be chosen as(30)V1z1=12z1Tz1,utemp1=g1-1x1y˙r-f1x1-k1z1-g1dx1d^.In the second step, the dynamic of the tracking error with respect to the first virtual controller is(31)z˙2=x˙2-∂a1∂x1f1x1+g1x1x2+g1dx1d-∂a1∂yry˙r-∂a1∂y˙ryr2-∂a1∂d^d^˙=f2x-2+g2x-2x3+g2dx-2d-∂a1∂x1f1x1+g1x1x2+g1dx1d-∂a1∂yry˙r-∂a1∂y˙ryr2-∂a1∂d^d^˙.Defining a tracking error as z3=x3-a2, (31) becomes as(32)z˙2=f2x-2+g2x-2a2+z3+g2dx-2d-∂a1∂x1f1x1+g1x1x2+g1dx1d-∂a1∂yry˙r-∂a1∂y˙ryr2-∂a1∂d^d^˙.The same as in the first step, there exists a virtual controller a2y-r2,x-2,d^-1 described as below:(33)a2=utemp2-ca2g2Tx-2+cca2g2-1x-2g2dx-2-∂a1∂x1g1dx12∂V2z2∂z2Twhich makes z2 subsystem ISS with respect to z3 and d~. In (33), V2z2 is a CLF for z2 subsystem and utemp2y-r2,x-2,d^-1 is an arbitrary asymptotical stabilizer. They can be chosen as(34)V2z2=12z2Tz2,utemp2=g2-1x-2∂a1∂x1f1x1+g1x1x2+g1dx1d^+∂a1∂yry˙r+⋯+∂a1∂y˙ryr2+∂a1∂d^d^˙-f2x-2-k2z2-g2dx-2d^.The same as in the standard backstepping design process, the virtual controller’s tracking error cross-term in the upper subsystem can be cancelled out with a state feedback term in the lower subsystem. So, there is no need to make every zi subsystem ISS with respect to the virtual controller’s tracking error zi+1. To achieve the counteraction for the cross-term, modify utemp2y-r2,x-2,d^-1 in the virtual controller a2y-r2,x-2,d^-1 as(35)utemp2=g2-1x-2-g1Tx1z1+∂a1∂x1f1x1+g1x1x2+g1dx1d^+∂a1∂yry˙r+⋯+∂a1∂y˙ryr2+∂a1∂d^d^˙-f2x-2-k2z2-g2dx-2d^and set ca1=0, ca2=0, cca1>0, and cca2>0. Hereafter, it is handled the same.In theith step, i≥3, the dynamic of the tracking error zi=xi-ai-1 is(36)z˙i=fix-i+gix-iai+zi+1+gidx-id-∑k=0i-1∂ai-1∂yrkyrk+1-⋯-∑k=0i-2∂ai-1∂d^kd^k+1-∑k=1i-1∂ai-1∂xkfkx-k+gkx-kxk+1+gkdx-kd,where x-i=x1,…,xi, y-ri=yr,y˙r,…,yri, d^-i=d^,d^˙,…,d^i, and zi+1=xi+1-ai. According to Theorem 10, there exists a virtual controller aiy-ri,x-i,d^-i-1 described as below:(37)ai=utempi-caigiTx-i+ccaigi-1x-igidx-i-∑k=1i-1∂ai-1∂xkgkdx-k2∂Vizi∂ziTwhich makes zi subsystem ISS to zi+1 and d~. In (37), Vizi is a CLF for zi subsystem and utempiy-ri,x-i,d^-i-1 is an arbitrary asymptotical stabilizer. Similarly, we can choose(38)Vizi=12ziTzi,utempi=gi-1x-i-gi-1Tx-i-1zi-1-fix-i-kizi-gidx-id^+∑k=0i-1∂ai-1∂yrkyrk+1+⋯+∑k=0i-2∂ai-1∂d^kd^k+1+∑k=1i-1∂ai-1∂xkfkx-k+gkx-kxk+1+gkdx-kd^.Set cai=0 and ccai>0.In thenth step, the tracking error zn=xn-an-1, and its dynamic is(39)z˙n=x˙n-a˙n-1=fnx-n+gnx-nu+gndx-nd-∑k=0n-1∂an-1∂yrkyrk+1-⋯-∑k=0n-2∂an-1∂d^kd^k+1-∑k=1n-1∂an-1∂xkfkx-k+gkx-kxk+1+gkdx-kd.According to Theorem 10, there exists a controller uy-rn,x-n,d^-n-1 described as below:(40)u=utempn-cangnTx-n+ccangn-1x-ngndx-n-∑k=1n-1∂an-1∂xkgkdx-k2∂Vnzn∂znTwhich makes zn subsystem ISS with respect to the additional input v and d~. Vnzn and utempny-rn,x-n,d^-n-1 are chosen as(41)Vnzn=12znTzn,(42)utempn=gn-1x-n-gn-1Tx-n-1zn-1-fnx-n-knzn-gndx-nd^+∑k=0n-1∂ai-1∂yrkyrk+1+⋯+∑k=0n-2∂ai-1∂d^kd^k+1+∑k=1n-1∂ai-1∂xkfkx-k+gkx-kxk+1+gkdx-kd^.Different from the previous steps, here set can>0 and ccan>0.The closed loop system obtained from the above process has a property described as Theorem12.Theorem 12.
Considering system (1), the controller uy-rn,x-n,d^-n-1 as in formula (40) and (42), and virtual controllers aiy-ri,x-i,d^-i-1 given above, the closed loop system (43) is made ISS with respect to the additional input v and d~.(43)z˙1=f1x1+g1x1a1+z2+g1dx1d^+d~-y˙r,⋮z˙i=fix-i+gix-iai+zi+1+gidx-id^+d~-a˙i-1,⋮z˙n=fnx-n+gnx-nu+v+gndx-nd^+d~-a˙n-1,yc=z1.Proof.
Take a Lyapunov function candidate as(44)Vz-n=∑k=1nVkzk=12z-nTz-n,where z-n=z1,…,znT:(45)V˙z-n=∑k=1nzkTz˙k=z1Tf1x1+g1x1a1+z2+g1dx1d-y˙r+⋯+∑k=2n-1zkTfkx-k+gkx-kak+zk+1+gkdx-kd^+d~-a˙k-1+⋯+znTfnx-n+gnx-nu+v+gndx-nd^+d~-a˙n-1.Invoking the controller uy-rn,x-n,d^-n-1 as in formula (40) and (42), and virtual controllers aiy-ri,x-i,d^-i-1 given in the above process, we have(46)V˙z-n=z1T-k1z1+g1x1z2+g1dx1d~-cca1g21dx1∂V1z1∂z1T+⋯+∑k=2n-1zkT-kkzk-gk-1Tx-k-1zk-1+gkx-kzk+1+gkdx-kd~-∑p=1k-1∂ak-1∂xpgpdx-pd~-⋯-ccakgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-p2∂Vkzk∂zkT+⋯+znT-knzn-gn-1Tx-n-1zn-1+gndx-nd~-∑p=1n-1∂ak-1∂xpgpdx-pd~+gnx-nv-⋯-cangn2x-n+ccangndx-n-∑p=1n-1∂an-1∂xpgpdx-p2∂Vnzn∂znT.Using Young’s inequation, we have(47)V˙z-n=-∑k=1nkkzkTzk+z1Tg1dx1d~-cca1z1Tg1dx12+⋯+∑k=2nzkTgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-pd~-ccakzkTgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-p2+znT-cangn2x-nzn+gnx-nv≤-∑k=1nkkzk2-cca1-λ1z1Tg1dx12+∑k=1n1λkd~2-⋯-∑k=2nccak-λkzkTgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-p2-can-γznTgnx-n2+1γv2.From (47), it is shown that, for any λi>0, γ>0, ki>0, ccai≥λi, and can≥γ, the states z-n of system (43) are ISS with respect to the additional input v and the disturbance observer error d~.Then, based on Assumption5 and Lemma 6, an input delay compensation controller is given as below:(48)uy-rn,Pt,d^-n-1,where the term P(t) is the solution of (49)Pt=ϕ-1t-t∫01f1Pϕt+yϕ-1t-t,uϕt+yϕ-1t-tdy+x-nt=∫ϕttf1Pσ,uσdσϕ′ϕ-1σ+x-nt.The function f1(·) represents the right side of system (1). The estimation d^ is given by the disturbance observer presented in (8) and (9).Based on Lemma6 and Theorems 8, 10, and 12, we can easily get the following corollary.Corollary 13.
For system (1), satisfying Assumptions 2 and 3, the delay compensation controller (40), (42), (48), and (49) makes the following inequation hold, where α is a KL class function:(50)xt+supϕt≤θ≤t⁡uθ≤αx0+supϕt≤θ≤0⁡uθ,t,t≥0.Proof.
In Theorem12, system (1) is shown to be ISS with respect to the additional input v and the disturbance observer error d~. In Theorem 8, the observer error is shown to be exponentially convergent and we can easily choose ε>0 to make the augmented system (1) and (2) ISS with respect to v. Then, according to Lemma 6, the delay compensation controller (40), (42), (48), and (49) makes inequation (50) hold.


## 4.1. Disturbance Observer

The disturbance observer for nonlinear systems is firstly presented by Chen in [53]. Here, a disturbance observer is presented with a different assumption and observer gain. Consider a nonlinear system:(7)x˙t=fx+guxu+gdxd,y=x,where the states x∈Rn, input u∈Rk, and measured output y∈Rn. The matrices fx, gux, and gdx are all locally Lipschitz. The gain matrix gux is always invertible. The disturbance d comes from exosystem (2). In order to design a disturbance observer, we make the following assumption.Assumption 7.
For system (7), the gain matrix gdx is known and globally invertible in the whole domain of definition.
Then, a disturbance observer is presented as below:(8)z˙=A-lxgdxCz+Apx-lxgdxCpx+fx+guxu,ξ^=z+px,d^=Cξ^,where the term lx satisfies(9)lx=∂px∂x=Kgd-1x.The observer designed above can estimate the disturbance d exponentially as summarized in the following theorem.Theorem 8.
Considering system (7), where the disturbance d is the output of exosystem (2), when Assumption 7 is satisfied, there exist a matrix K and an observer ((8), (9)) whose output is exponentially convergent to the actual disturbance d, uniformly for x.Proof.
Select a candidate for the Lyapunov function:(10)Vo=12eTe=12ξ-ξ^Tξ-ξ^.We have(11)V˙o=eTAξ-z˙-p˙x=eTAξ-A-lxgdxCz-Apx+⋯+eTlxgdxCpx+fx+guxu-∂px∂xx˙=eTAξ-z-px+lxgdxCz+gdxCpx+fx+guxu-lxx˙=eTAe+lxgdxd^+fx+guxu-x˙=eTAe-lxgdxCe=eTA-lxgdxCe.According to Assumption 7 and because C,A is observable, for any negative definite matrix -Q-εI, ε>0, there exists a matrix K making lx=Kgd-1x and the following holds:(12)V˙o=eTA-lxgdxCe=eTA-KCe=eT-Q-εIe<-eTQe.With the customized positive definite matrix Q, we can easily choose Q=ε1I, ε1>0, which makes(13)V˙o<-ε1Vo.Then states of observer ((8), (9)) are exponentially convergent to the exostates of the exosystem, uniformly for x. This also makes the estimation d^ exponentially convergent to the actual disturbance d.Remark 9.
(1) The controller u in system (7) or in observer (8) can be of any form, such as controllers with time delay or a state usually treated as a virtual controller in the backstepping method, as long as it is known.
(2) In Chen’s design [53], the object system needs to be made passive by output feedback, and the observer gain matrix is designed by partial derivate. The design used in this paper needs the actual value of the invertible disturbance gain matrix and does not need any assumption about passivity.


## 4.2. Separation Principle

The separate principle does not hold for general nonlinear systems, and then the controllers and observers must be designed simultaneously using a single Lyapunov function for the augmented system consisting of the controlled system and the observer. Actually, the nonlinear separation principle is available, according to the Lyapunov stability theorem, when observer errors themselves are asymptotically convergent, and their transition processes do not destabilize the systems controlled by estimated-states feedback controllers. Here, we give a sufficient condition for the separation principle when dealing with a class of nonlinear system described as (7).Theorem 10.
For system (7), if the disturbance d is measured and a controller utempx,d can globally asymptotically stabilize the system; then with an additional input v and an estimate d^ of d, there exist a controller ucx,d^ making system (14) ISS with respect to v,d~; furthermore if the estimation d^ is exponentially convergent to the disturbance d and, in system (14), the input-to-states gain λ2-1 with respect to d~ satisfies λ2-1I<CTC, then ucx,d^ asymptotically stabilize the augmented system of (7) and the disturbance estimation error system, which means the separation principle is available.(14)x˙t=fx+guxuc+v+gdxd^+gdxd~,y=x.Proof.
Whend is known there exists the controller utempx,d globally asymptotically stabilizing system (7) and then there is a Lyapunov function Vx, which makes(15)α_x≤Vx≤α-x,∂Vx∂xfx+guxutempx,d+gdxd≤-βx,where α_, α-, and β belong to the K-class functions.
Invokeucx,d^=utempx,d^+uadx,d^ into system (14), and then we have(16)x˙t=fx+guxutempx,d^+gdxd^+⋯+guxuadx,d^+guxv+gdxd~.Invoking the controller(17)uadx,d^=-c1guTx+c2gu-1xgdxgdTx∂Vx∂xT.utemp in equation (16) is different from the one in equation (15), and we can put the difference term utempx,d-utempx,d^ into the additional input v. Then utemp in (18) can be treated the same as the one in (15). The derivative of the Lyapunov function candidate Vx along the system (16) satisfies(18)V˙x=∂Vx∂xfx+guxutemp+gdxd^+guxuad+guxv+gdxd~≤-βx+∂Vx∂x-c1gu2x+c2gd2x∂Vx∂xT+guxv+gdxd~≤-βx-c1∂Vx∂xgux2-c2∂Vx∂xgdx2+λ1∂Vx∂xgux2+⋯+λ1-1v2+λ2∂Vx∂xgdx2+λ2-1d~2≤-βx-c1-λ1∂Vx∂xgux2-c2-λ2∂Vx∂xgdx2+⋯+λ1-1v2+λ2-1d~2,where the scalars c1 and c2 are designing parameters. Given any λ1>0 and λ2>0, select c1 and c2 making inequations c1-λ1>0 and c2-λ2>0 hold, and then we have(19)V˙x≤-βx-c1-λ1∂Vx∂xgux2-c2-λ2∂Vx∂xgdx2+⋯+λ1-1v2+λ2-1d~2<-βx+λ1-1v2+λ2-1d~2.It shows system (14) is ISS with respect to v,d~.
When the observer error is exponentially convergent uniformly, according to the proof of Theorem8, the Lyapunov function Vo=1/2eTe, and its derivative V˙o<-eTQe. Because C,A is observable, so the matrix CTC is positive definite. Then, take a Lyapunov function candidate(20)Vd=12eTCTCe=12d~Td~.We have(21)V˙d=eTCTCe˙<-eTCTCQe.With Q selectable, choose Q=CTC>μI, where μ is a positive constant. Then we have(22)V˙d<-eTCTCCTCe=-d~TCCTd~T<-μd~2.The original system to be controlled and the dynamic of the disturbance observer error form the augmented system with augmented states x,d~. Take a candidate for Lyapunov function of the augmented system as Vx,d~=Vd+V, whose derivative shows(23)V˙x,d~=V˙d+V˙<-βx+λ1-1v2+λ2-1d~2-μd~2.If v=0, the value of λ2-1 can be set as λ2-1=μ-μ0, μ0>0, and then(24)V˙x,d~<-βx-μ0d~2.So, when the observer states are exponentially convergent to the exostates of exosystem uniformly for x and the input-to-states gain λ2-1 with respect to d~ satisfies λ2-1I<CTC, controller (25) asymptotically stabilizes the augmented system of (7) and the dynamic of the disturbance observer error. The separation principle is available.(25)ucx,d^=utempx,d^-c1guTx+c2gu-1xgdxgdTx∂Vx∂xT.Remark 11.
The IS-gainλ2-1 can be easily designed to satisfy the condition λ2-1I<CTC. This condition is nontrivial and can not be ignored.


## 4.3. Controller Design and Stability Analysis

In order to solve the regulation problem described in Section2, we firstly solve the regulation problem without input delay, as D(t)≡0, and design a controller based on the backstepping method and the disturbance observer; then, using the ISS property of the designed controller we construct the final delay compensation controller based on Lemma 6.For system (1), reference signal yr and its derivation yri are all known, and a tracking controller with ISS properties is designed as follows.In the first step, define the output tracking error asz1=x1-yr, and its dynamic is described as(26)z˙1=x˙1-y˙r=f1x1+g1x1x2+g1dx1d-y˙r.Define a virtual controller a1: (27)z˙1=f1x1+g1x1a1+x2-a1+g1dx1d-y˙r.Then, define a tracking error with respect to the virtual controller as z2=x2-a1, and we have(28)z˙1=f1x1+g1x1a1+z2+g1dx1d-y˙r.Using an exponentially convergent disturbance observer and according to Theorem 10, there exists a virtual controller a1yr,y˙r,x1,d^ described as below:(29)a1=utemp1-ca1g1Tx1+cca1g1-1x1g1dx1g1dTx1∂V1z1∂z1Twhich makes z1 subsystem ISS with respect to z2 and d~, where d^ and d~=d-d^ are the estimate value of d and its estimate error, respectively. In (29), V1z1 is a CLF (Control Lyapunov Function) for z1 subsystem and utemp1yr,y˙r,x1,d^ is an arbitrary asymptotical stabilizer. They can be chosen as(30)V1z1=12z1Tz1,utemp1=g1-1x1y˙r-f1x1-k1z1-g1dx1d^.In the second step, the dynamic of the tracking error with respect to the first virtual controller is(31)z˙2=x˙2-∂a1∂x1f1x1+g1x1x2+g1dx1d-∂a1∂yry˙r-∂a1∂y˙ryr2-∂a1∂d^d^˙=f2x-2+g2x-2x3+g2dx-2d-∂a1∂x1f1x1+g1x1x2+g1dx1d-∂a1∂yry˙r-∂a1∂y˙ryr2-∂a1∂d^d^˙.Defining a tracking error as z3=x3-a2, (31) becomes as(32)z˙2=f2x-2+g2x-2a2+z3+g2dx-2d-∂a1∂x1f1x1+g1x1x2+g1dx1d-∂a1∂yry˙r-∂a1∂y˙ryr2-∂a1∂d^d^˙.The same as in the first step, there exists a virtual controller a2y-r2,x-2,d^-1 described as below:(33)a2=utemp2-ca2g2Tx-2+cca2g2-1x-2g2dx-2-∂a1∂x1g1dx12∂V2z2∂z2Twhich makes z2 subsystem ISS with respect to z3 and d~. In (33), V2z2 is a CLF for z2 subsystem and utemp2y-r2,x-2,d^-1 is an arbitrary asymptotical stabilizer. They can be chosen as(34)V2z2=12z2Tz2,utemp2=g2-1x-2∂a1∂x1f1x1+g1x1x2+g1dx1d^+∂a1∂yry˙r+⋯+∂a1∂y˙ryr2+∂a1∂d^d^˙-f2x-2-k2z2-g2dx-2d^.The same as in the standard backstepping design process, the virtual controller’s tracking error cross-term in the upper subsystem can be cancelled out with a state feedback term in the lower subsystem. So, there is no need to make every zi subsystem ISS with respect to the virtual controller’s tracking error zi+1. To achieve the counteraction for the cross-term, modify utemp2y-r2,x-2,d^-1 in the virtual controller a2y-r2,x-2,d^-1 as(35)utemp2=g2-1x-2-g1Tx1z1+∂a1∂x1f1x1+g1x1x2+g1dx1d^+∂a1∂yry˙r+⋯+∂a1∂y˙ryr2+∂a1∂d^d^˙-f2x-2-k2z2-g2dx-2d^and set ca1=0, ca2=0, cca1>0, and cca2>0. Hereafter, it is handled the same.In theith step, i≥3, the dynamic of the tracking error zi=xi-ai-1 is(36)z˙i=fix-i+gix-iai+zi+1+gidx-id-∑k=0i-1∂ai-1∂yrkyrk+1-⋯-∑k=0i-2∂ai-1∂d^kd^k+1-∑k=1i-1∂ai-1∂xkfkx-k+gkx-kxk+1+gkdx-kd,where x-i=x1,…,xi, y-ri=yr,y˙r,…,yri, d^-i=d^,d^˙,…,d^i, and zi+1=xi+1-ai. According to Theorem 10, there exists a virtual controller aiy-ri,x-i,d^-i-1 described as below:(37)ai=utempi-caigiTx-i+ccaigi-1x-igidx-i-∑k=1i-1∂ai-1∂xkgkdx-k2∂Vizi∂ziTwhich makes zi subsystem ISS to zi+1 and d~. In (37), Vizi is a CLF for zi subsystem and utempiy-ri,x-i,d^-i-1 is an arbitrary asymptotical stabilizer. Similarly, we can choose(38)Vizi=12ziTzi,utempi=gi-1x-i-gi-1Tx-i-1zi-1-fix-i-kizi-gidx-id^+∑k=0i-1∂ai-1∂yrkyrk+1+⋯+∑k=0i-2∂ai-1∂d^kd^k+1+∑k=1i-1∂ai-1∂xkfkx-k+gkx-kxk+1+gkdx-kd^.Set cai=0 and ccai>0.In thenth step, the tracking error zn=xn-an-1, and its dynamic is(39)z˙n=x˙n-a˙n-1=fnx-n+gnx-nu+gndx-nd-∑k=0n-1∂an-1∂yrkyrk+1-⋯-∑k=0n-2∂an-1∂d^kd^k+1-∑k=1n-1∂an-1∂xkfkx-k+gkx-kxk+1+gkdx-kd.According to Theorem 10, there exists a controller uy-rn,x-n,d^-n-1 described as below:(40)u=utempn-cangnTx-n+ccangn-1x-ngndx-n-∑k=1n-1∂an-1∂xkgkdx-k2∂Vnzn∂znTwhich makes zn subsystem ISS with respect to the additional input v and d~. Vnzn and utempny-rn,x-n,d^-n-1 are chosen as(41)Vnzn=12znTzn,(42)utempn=gn-1x-n-gn-1Tx-n-1zn-1-fnx-n-knzn-gndx-nd^+∑k=0n-1∂ai-1∂yrkyrk+1+⋯+∑k=0n-2∂ai-1∂d^kd^k+1+∑k=1n-1∂ai-1∂xkfkx-k+gkx-kxk+1+gkdx-kd^.Different from the previous steps, here set can>0 and ccan>0.The closed loop system obtained from the above process has a property described as Theorem12.Theorem 12.
Considering system (1), the controller uy-rn,x-n,d^-n-1 as in formula (40) and (42), and virtual controllers aiy-ri,x-i,d^-i-1 given above, the closed loop system (43) is made ISS with respect to the additional input v and d~.(43)z˙1=f1x1+g1x1a1+z2+g1dx1d^+d~-y˙r,⋮z˙i=fix-i+gix-iai+zi+1+gidx-id^+d~-a˙i-1,⋮z˙n=fnx-n+gnx-nu+v+gndx-nd^+d~-a˙n-1,yc=z1.Proof.
Take a Lyapunov function candidate as(44)Vz-n=∑k=1nVkzk=12z-nTz-n,where z-n=z1,…,znT:(45)V˙z-n=∑k=1nzkTz˙k=z1Tf1x1+g1x1a1+z2+g1dx1d-y˙r+⋯+∑k=2n-1zkTfkx-k+gkx-kak+zk+1+gkdx-kd^+d~-a˙k-1+⋯+znTfnx-n+gnx-nu+v+gndx-nd^+d~-a˙n-1.Invoking the controller uy-rn,x-n,d^-n-1 as in formula (40) and (42), and virtual controllers aiy-ri,x-i,d^-i-1 given in the above process, we have(46)V˙z-n=z1T-k1z1+g1x1z2+g1dx1d~-cca1g21dx1∂V1z1∂z1T+⋯+∑k=2n-1zkT-kkzk-gk-1Tx-k-1zk-1+gkx-kzk+1+gkdx-kd~-∑p=1k-1∂ak-1∂xpgpdx-pd~-⋯-ccakgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-p2∂Vkzk∂zkT+⋯+znT-knzn-gn-1Tx-n-1zn-1+gndx-nd~-∑p=1n-1∂ak-1∂xpgpdx-pd~+gnx-nv-⋯-cangn2x-n+ccangndx-n-∑p=1n-1∂an-1∂xpgpdx-p2∂Vnzn∂znT.Using Young’s inequation, we have(47)V˙z-n=-∑k=1nkkzkTzk+z1Tg1dx1d~-cca1z1Tg1dx12+⋯+∑k=2nzkTgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-pd~-ccakzkTgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-p2+znT-cangn2x-nzn+gnx-nv≤-∑k=1nkkzk2-cca1-λ1z1Tg1dx12+∑k=1n1λkd~2-⋯-∑k=2nccak-λkzkTgkdx-k-∑p=1k-1∂ak-1∂xpgpdx-p2-can-γznTgnx-n2+1γv2.From (47), it is shown that, for any λi>0, γ>0, ki>0, ccai≥λi, and can≥γ, the states z-n of system (43) are ISS with respect to the additional input v and the disturbance observer error d~.Then, based on Assumption5 and Lemma 6, an input delay compensation controller is given as below:(48)uy-rn,Pt,d^-n-1,where the term P(t) is the solution of (49)Pt=ϕ-1t-t∫01f1Pϕt+yϕ-1t-t,uϕt+yϕ-1t-tdy+x-nt=∫ϕttf1Pσ,uσdσϕ′ϕ-1σ+x-nt.The function f1(·) represents the right side of system (1). The estimation d^ is given by the disturbance observer presented in (8) and (9).Based on Lemma6 and Theorems 8, 10, and 12, we can easily get the following corollary.Corollary 13.
For system (1), satisfying Assumptions 2 and 3, the delay compensation controller (40), (42), (48), and (49) makes the following inequation hold, where α is a KL class function:(50)xt+supϕt≤θ≤t⁡uθ≤αx0+supϕt≤θ≤0⁡uθ,t,t≥0.Proof.
In Theorem12, system (1) is shown to be ISS with respect to the additional input v and the disturbance observer error d~. In Theorem 8, the observer error is shown to be exponentially convergent and we can easily choose ε>0 to make the augmented system (1) and (2) ISS with respect to v. Then, according to Lemma 6, the delay compensation controller (40), (42), (48), and (49) makes inequation (50) hold.


## 5. AHV Attitude Control

### 5.1. AHV Control System Description

According to the dynamic equation and kinematics equation of attitude motion of an AHV, when time delay caused by signal transmission and actuator dynamics is abstracted as an input delay, the control problem of AHV attitude angles with respect to the air-path axis system can be described as a control design problem of a system in the states strict feedback form, which is presented as below:(51)Ω˙=fs+gsω+d,ω˙=ff+gfgfδδt-Dt+d,y=Ω.The nonlinear function vectors, fs and ff, and the virtual and actual control gain matrices, gs and gfgδ, are all known. The disturbance d is given by the exosystem model (2). The aerodynamic model is given by the NASA Langley Research Center in [54]. The model of time delay Dt is assumed to be known. Here, for simplicity, the disturbance gain matrices are set as the identity matrix. The control object is to design a controller making the system output track the reference signal yd(t) and keep all the states bounded. For research convenience and considering actual situations, some assumptions are given as below.Assumption 14.
(1) All the states, Ω and ω, which means the angle of attack, the angle of sideslip, the angle around the roll speed, and elements of the angular velocity in the body frame, are all measured. The reference output signal yd(t) is exactly known, which is continue enough and bounded, and its derivatives with enough degrees are also known, continuous, and bounded.
(2) The virtual control gain matrix gs and the actual control gain matrix gfgfδ are all invertible in the whole domain.
(3) The AHV attitude system (51) fulfills Assumption 2 when the delay is relatively small.
The problem is solved using the method presented above. Based on the separation principle proved, disturbance observers can be designed independently as(52)z˙1=A1-K1C1z1+A1K1Ω-K1C1K1Ω+fs+gsω,ξ^1=z1+K1Ω,d^1=C1ξ^1,(53)z˙2=A2-K2C2z2+A2K2ω-K2C2K2ω+ff+gfgfδδt-Dt,ξ^2=z2+K2ω,d^2=C2ξ^2.Here, for simplicity, the disturbances in the attitude angles dynamic equation and in the angle rate dynamic equation are assumed to come from the same exosystem. Then, the virtual controller and actual controller are presented as below for the nondelayed system:(54)ωd=gs-1-cses-fs-d^+Ω˙d-cca1gs-1es,where es=Ω-Ωd and(55)δc=g2-1-cfef-ff-gsTes-d^-d~+∂ωd∂Ωfs+gsω+d^+d~+∂ωd∂Ω˙dΩd2+∂ωd∂d^1d^˙-⋯-ca2g2T+cca2g2-1I-∂ωd∂ΩI-∂ωd∂ΩTefT,where g2≜gfgf,δ and ef=ω-ωd.
Finally, the actual controller for the delay system is obtained as(56)δcΩ-d2,Pt,d^-1,where the time delay compensation term Pt is given by (49).


### 5.2. Simulation

In the Simulink simulation, the mass and moments of inertia are assumed to be constant. Other parameters are set as follows: the flight initial velocity is 2200 m/s, the thrust is always 400 KN, the initial flight height is 27 km, the initial AOA is 0.5°, the initial value of the sideslip angle is 0°, the initial value of the angle around the roll speed isμ0 = −0.1°, and the elements of the angular velocity in the body frame are all zero. The time delay model is Dt=1+t/81+2t, which can be easily verified fulfilling Assumption 3. The angles command is α=6∘/s+2 or a sine signal with the amplitude of 6∘, β = 0∘, and μ = −1∘. The disturbances are given by model (2) with A=[0,1,1,1;-1,0,1,1;-1,-1,0,1;-1,-1,-1,0] and C=[1,0,0,0;0,1,0,0;0,0,1,0] and the initial condition is 0.01×1;1;1;1. The simulation results are shown below.


#### 5.2.1. In the Case of Being Disturbance-Free

Firstly, the disturbances are not put into the system, so the time delay compensation control method itself can be verified. When the controller obtained from the nondelayed system is used in the delayed system, the tracking results and actuators’ responses are shown in Figures1 and 2. It is shown that when time delay is small, without delay compensation, the attitude still can track the commands, but there are a big overshoot in the AOA tracking and an apparent oscillation in the tracking error of the angle around the roll speed, which are harmful for the actual flight control. When the delay compensation controller with the same control gains is applied, the tracking results and actuators’ response are shown in Figures 3 and 4. It is shown that, using delay compensation, the overshoot in the AOA tracking is quite small, and the oscillation in the tracking error of the angle around the roll speed is effectively suppressed. Those results demonstrate that, under small time delays in the input channel, the delay compensation can significantly improve the control performance and tracking accuracy. In both situations, the actuator deflection angles are quite big, which shows the inherent character of low aerodynamic efficiencies for an AHV’s actuation surfaces.Figure 1
Uncompensated tracking results.Figure 2
Uncompensated actuator deflections.Figure 3
Compensated tracking results.Figure 4
Compensated actuator deflections.When the time delay is bigger enough, extreme situations come out. In those situations, without delay compensation, the attitude tracking is out of control, as shown in Figures5 and 6. Then, using the delay compensation controller with the same control gains, it is shown that the attitude tracking objects are well achieved, as shown in Figures 7 and 8.Figure 5
Uncompensated tracking results in extreme.Figure 6
Uncompensated actuator deflections in extreme.Figure 7
Compensated tracking results in extreme.Figure 8
Compensated actuator deflections in extreme.A result of AOA tracking to a sinus signal is given in Figures9 and 10.Figure 9
Compensated tracking results of AOA sinus.Figure 10
Actuator deflections in AOA tracking of a sinus signal.The simulation results shown above verify the effectiveness of input delay compensation controller for an AHV attitude tracking control. The compensation control presented in this paper can improve the control performance and tracking accuracy and enhance the stability of the system even in the situations of big input delays.


#### 5.2.2. In the Case of Being Time-Delayed and Disturbed

Then, the disturbances are put into the system, so the whole control method with time delay compensation and disturbance estimation can be verified. Here, a smaller time delay is given asDt=1+t/101+2t. When the delay compensation controller with disturbance estimation is applied, the tracking results and actuators’ response are shown in Figures 11 and 12. The disturbance observers’ observing errors are shown in Figures 13 and 14. It is shown that when the disturbances and input delay are considered, the observers in the form of (52) and (53) can asymptotically estimate the disturbance produced by the exosystem, and the attitude commands can be well tracked. In Figure 11, it can be found that there are quite small steady-state errors which are bigger than those in the case of being disturbance-free. The reason for that lies in the adopted Assumption 2. In order to assure the availability of input delay compensation method, the controlled system must be strongly forward complete, which means the states of the controlled object must be in a safe range all the time. For flight systems, it is reasonable to assume that the attitude tracking error system’s states will not get out of the safe range when the input time delay and the disturbance are small enough. So, in the case of being time-delayed and disturbed, the time delay is chosen a little smaller and the disturbance’s amplitude is relatively small. Actually, the disturbance’s amplitude (about 0.01 rad/s) is not quite small with respect to the speed of AOA’ tracking (about 0.05 rad/s). Although there are steady-state errors in the attitude tracking, it is shown in Figure 15 that the AOA can efficiently track a complex signal, such as a sine signal. All the actuator deflection results in Figures 12 and 16 indicate that the control method used here can make the AHV’s attitude tracking realized without reaching the deflecting constraint of 30 degrees.Figure 11
Compensated tracking results.Figure 12
Compensated actuator deflections.Figure 13
Disturbance observer errors in angles dynamic.Figure 14
Disturbance observer errors in angle_rate dynamic.Figure 15
Compensated tracking results of AOA sinus.Figure 16
Actuator deflections in AOA tracking of a sinus signal.


## 5.1. AHV Control System Description

According to the dynamic equation and kinematics equation of attitude motion of an AHV, when time delay caused by signal transmission and actuator dynamics is abstracted as an input delay, the control problem of AHV attitude angles with respect to the air-path axis system can be described as a control design problem of a system in the states strict feedback form, which is presented as below:(51)Ω˙=fs+gsω+d,ω˙=ff+gfgfδδt-Dt+d,y=Ω.The nonlinear function vectors, fs and ff, and the virtual and actual control gain matrices, gs and gfgδ, are all known. The disturbance d is given by the exosystem model (2). The aerodynamic model is given by the NASA Langley Research Center in [54]. The model of time delay Dt is assumed to be known. Here, for simplicity, the disturbance gain matrices are set as the identity matrix. The control object is to design a controller making the system output track the reference signal yd(t) and keep all the states bounded. For research convenience and considering actual situations, some assumptions are given as below.Assumption 14.
(1) All the states, Ω and ω, which means the angle of attack, the angle of sideslip, the angle around the roll speed, and elements of the angular velocity in the body frame, are all measured. The reference output signal yd(t) is exactly known, which is continue enough and bounded, and its derivatives with enough degrees are also known, continuous, and bounded.
(2) The virtual control gain matrix gs and the actual control gain matrix gfgfδ are all invertible in the whole domain.
(3) The AHV attitude system (51) fulfills Assumption 2 when the delay is relatively small.
The problem is solved using the method presented above. Based on the separation principle proved, disturbance observers can be designed independently as(52)z˙1=A1-K1C1z1+A1K1Ω-K1C1K1Ω+fs+gsω,ξ^1=z1+K1Ω,d^1=C1ξ^1,(53)z˙2=A2-K2C2z2+A2K2ω-K2C2K2ω+ff+gfgfδδt-Dt,ξ^2=z2+K2ω,d^2=C2ξ^2.Here, for simplicity, the disturbances in the attitude angles dynamic equation and in the angle rate dynamic equation are assumed to come from the same exosystem. Then, the virtual controller and actual controller are presented as below for the nondelayed system:(54)ωd=gs-1-cses-fs-d^+Ω˙d-cca1gs-1es,where es=Ω-Ωd and(55)δc=g2-1-cfef-ff-gsTes-d^-d~+∂ωd∂Ωfs+gsω+d^+d~+∂ωd∂Ω˙dΩd2+∂ωd∂d^1d^˙-⋯-ca2g2T+cca2g2-1I-∂ωd∂ΩI-∂ωd∂ΩTefT,where g2≜gfgf,δ and ef=ω-ωd.
Finally, the actual controller for the delay system is obtained as(56)δcΩ-d2,Pt,d^-1,where the time delay compensation term Pt is given by (49).


## 5.2. Simulation

In the Simulink simulation, the mass and moments of inertia are assumed to be constant. Other parameters are set as follows: the flight initial velocity is 2200 m/s, the thrust is always 400 KN, the initial flight height is 27 km, the initial AOA is 0.5°, the initial value of the sideslip angle is 0°, the initial value of the angle around the roll speed isμ0 = −0.1°, and the elements of the angular velocity in the body frame are all zero. The time delay model is Dt=1+t/81+2t, which can be easily verified fulfilling Assumption 3. The angles command is α=6∘/s+2 or a sine signal with the amplitude of 6∘, β = 0∘, and μ = −1∘. The disturbances are given by model (2) with A=[0,1,1,1;-1,0,1,1;-1,-1,0,1;-1,-1,-1,0] and C=[1,0,0,0;0,1,0,0;0,0,1,0] and the initial condition is 0.01×1;1;1;1. The simulation results are shown below.


### 5.2.1. In the Case of Being Disturbance-Free

Firstly, the disturbances are not put into the system, so the time delay compensation control method itself can be verified. When the controller obtained from the nondelayed system is used in the delayed system, the tracking results and actuators’ responses are shown in Figures1 and 2. It is shown that when time delay is small, without delay compensation, the attitude still can track the commands, but there are a big overshoot in the AOA tracking and an apparent oscillation in the tracking error of the angle around the roll speed, which are harmful for the actual flight control. When the delay compensation controller with the same control gains is applied, the tracking results and actuators’ response are shown in Figures 3 and 4. It is shown that, using delay compensation, the overshoot in the AOA tracking is quite small, and the oscillation in the tracking error of the angle around the roll speed is effectively suppressed. Those results demonstrate that, under small time delays in the input channel, the delay compensation can significantly improve the control performance and tracking accuracy. In both situations, the actuator deflection angles are quite big, which shows the inherent character of low aerodynamic efficiencies for an AHV’s actuation surfaces.Figure 1
Uncompensated tracking results.Figure 2
Uncompensated actuator deflections.Figure 3
Compensated tracking results.Figure 4
Compensated actuator deflections.When the time delay is bigger enough, extreme situations come out. In those situations, without delay compensation, the attitude tracking is out of control, as shown in Figures5 and 6. Then, using the delay compensation controller with the same control gains, it is shown that the attitude tracking objects are well achieved, as shown in Figures 7 and 8.Figure 5
Uncompensated tracking results in extreme.Figure 6
Uncompensated actuator deflections in extreme.Figure 7
Compensated tracking results in extreme.Figure 8
Compensated actuator deflections in extreme.A result of AOA tracking to a sinus signal is given in Figures9 and 10.Figure 9
Compensated tracking results of AOA sinus.Figure 10
Actuator deflections in AOA tracking of a sinus signal.The simulation results shown above verify the effectiveness of input delay compensation controller for an AHV attitude tracking control. The compensation control presented in this paper can improve the control performance and tracking accuracy and enhance the stability of the system even in the situations of big input delays.


### 5.2.2. In the Case of Being Time-Delayed and Disturbed

Then, the disturbances are put into the system, so the whole control method with time delay compensation and disturbance estimation can be verified. Here, a smaller time delay is given asDt=1+t/101+2t. When the delay compensation controller with disturbance estimation is applied, the tracking results and actuators’ response are shown in Figures 11 and 12. The disturbance observers’ observing errors are shown in Figures 13 and 14. It is shown that when the disturbances and input delay are considered, the observers in the form of (52) and (53) can asymptotically estimate the disturbance produced by the exosystem, and the attitude commands can be well tracked. In Figure 11, it can be found that there are quite small steady-state errors which are bigger than those in the case of being disturbance-free. The reason for that lies in the adopted Assumption 2. In order to assure the availability of input delay compensation method, the controlled system must be strongly forward complete, which means the states of the controlled object must be in a safe range all the time. For flight systems, it is reasonable to assume that the attitude tracking error system’s states will not get out of the safe range when the input time delay and the disturbance are small enough. So, in the case of being time-delayed and disturbed, the time delay is chosen a little smaller and the disturbance’s amplitude is relatively small. Actually, the disturbance’s amplitude (about 0.01 rad/s) is not quite small with respect to the speed of AOA’ tracking (about 0.05 rad/s). Although there are steady-state errors in the attitude tracking, it is shown in Figure 15 that the AOA can efficiently track a complex signal, such as a sine signal. All the actuator deflection results in Figures 12 and 16 indicate that the control method used here can make the AHV’s attitude tracking realized without reaching the deflecting constraint of 30 degrees.Figure 11
Compensated tracking results.Figure 12
Compensated actuator deflections.Figure 13
Disturbance observer errors in angles dynamic.Figure 14
Disturbance observer errors in angle_rate dynamic.Figure 15
Compensated tracking results of AOA sinus.Figure 16
Actuator deflections in AOA tracking of a sinus signal.


## 5.2.1. In the Case of Being Disturbance-Free

Firstly, the disturbances are not put into the system, so the time delay compensation control method itself can be verified. When the controller obtained from the nondelayed system is used in the delayed system, the tracking results and actuators’ responses are shown in Figures1 and 2. It is shown that when time delay is small, without delay compensation, the attitude still can track the commands, but there are a big overshoot in the AOA tracking and an apparent oscillation in the tracking error of the angle around the roll speed, which are harmful for the actual flight control. When the delay compensation controller with the same control gains is applied, the tracking results and actuators’ response are shown in Figures 3 and 4. It is shown that, using delay compensation, the overshoot in the AOA tracking is quite small, and the oscillation in the tracking error of the angle around the roll speed is effectively suppressed. Those results demonstrate that, under small time delays in the input channel, the delay compensation can significantly improve the control performance and tracking accuracy. In both situations, the actuator deflection angles are quite big, which shows the inherent character of low aerodynamic efficiencies for an AHV’s actuation surfaces.Figure 1
Uncompensated tracking results.Figure 2
Uncompensated actuator deflections.Figure 3
Compensated tracking results.Figure 4
Compensated actuator deflections.When the time delay is bigger enough, extreme situations come out. In those situations, without delay compensation, the attitude tracking is out of control, as shown in Figures5 and 6. Then, using the delay compensation controller with the same control gains, it is shown that the attitude tracking objects are well achieved, as shown in Figures 7 and 8.Figure 5
Uncompensated tracking results in extreme.Figure 6
Uncompensated actuator deflections in extreme.Figure 7
Compensated tracking results in extreme.Figure 8
Compensated actuator deflections in extreme.A result of AOA tracking to a sinus signal is given in Figures9 and 10.Figure 9
Compensated tracking results of AOA sinus.Figure 10
Actuator deflections in AOA tracking of a sinus signal.The simulation results shown above verify the effectiveness of input delay compensation controller for an AHV attitude tracking control. The compensation control presented in this paper can improve the control performance and tracking accuracy and enhance the stability of the system even in the situations of big input delays.


## 5.2.2. In the Case of Being Time-Delayed and Disturbed

Then, the disturbances are put into the system, so the whole control method with time delay compensation and disturbance estimation can be verified. Here, a smaller time delay is given asDt=1+t/101+2t. When the delay compensation controller with disturbance estimation is applied, the tracking results and actuators’ response are shown in Figures 11 and 12. The disturbance observers’ observing errors are shown in Figures 13 and 14. It is shown that when the disturbances and input delay are considered, the observers in the form of (52) and (53) can asymptotically estimate the disturbance produced by the exosystem, and the attitude commands can be well tracked. In Figure 11, it can be found that there are quite small steady-state errors which are bigger than those in the case of being disturbance-free. The reason for that lies in the adopted Assumption 2. In order to assure the availability of input delay compensation method, the controlled system must be strongly forward complete, which means the states of the controlled object must be in a safe range all the time. For flight systems, it is reasonable to assume that the attitude tracking error system’s states will not get out of the safe range when the input time delay and the disturbance are small enough. So, in the case of being time-delayed and disturbed, the time delay is chosen a little smaller and the disturbance’s amplitude is relatively small. Actually, the disturbance’s amplitude (about 0.01 rad/s) is not quite small with respect to the speed of AOA’ tracking (about 0.05 rad/s). Although there are steady-state errors in the attitude tracking, it is shown in Figure 15 that the AOA can efficiently track a complex signal, such as a sine signal. All the actuator deflection results in Figures 12 and 16 indicate that the control method used here can make the AHV’s attitude tracking realized without reaching the deflecting constraint of 30 degrees.Figure 11
Compensated tracking results.Figure 12
Compensated actuator deflections.Figure 13
Disturbance observer errors in angles dynamic.Figure 14
Disturbance observer errors in angle_rate dynamic.Figure 15
Compensated tracking results of AOA sinus.Figure 16
Actuator deflections in AOA tracking of a sinus signal.


## 6. Conclusion

The main contribution in this article is the new framework of solving a nonlinear input delay regulation problem. It is impossible to get an analytic solution when the nonlinear regulation equations contain delay terms, so the nonlinear regulation problem with input delay has not been solved for a long time. In this paper, based on the framework we proposed, the nonlinear regulation problem with input delay is settled for the first time, for the class of strict feedback nonlinear systems. The framework proposed consisted of nonlinear damping controllers, nonlinear disturbance observers, and a nonlinear time delay predictor-based compensator, under the proved separation principle. Then, in application, the attitude tracking control of an AHV with considering the input delay is studied for the first time, using the proposed framework. The input delay is abstracted from the controller signal transmission and actuator dynamics and the disturbances come from the wind or modeling error. Based on the simulation results, we have demonstrated the advantage of the control method described in this paper and its availability for AHVs’ attitude control.



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*Source: 6850909-2017-05-08.xml*