The distributed control system synthesis of elastic structure


For an elastic distributed plant with parameters depending on the spatial variable, based on the spectral method of distributed systems analysis and synthesis and considering the internal resistance according to Voigt the transition is made from PDE to an infinite system of ODE in state space form. The boundary conditions are additively included to the obtained spectral representation, which enables to control from the boundaries. The control law for suppression of oscillations is synthesized and the closed system is analyzed. The obtained results can be used in the control systems synthesis for aircraft with active dynamic compensation of elastic vibrations.

Full Text


Elastic structures are widely used in the fields of aviation and rocket engineering to increase flight speed, reduce weight, and increase aircraft length. Under the appropriate flight conditions and particularly in terms of fuel consumption, elastic oscillations of the carrying structure occur; these are commensurate with the angular oscillations of an aircraft in terms of frequency and amplitude.

Elastic oscillations affect control system sensors and consequently, the control elements. These disturbances can result in the loss of accuracy and stability of the flight control [1, 2]. This creates an issue in the development of the aircraft control law to counteract external disturbances and elastic oscillations of the aircraft’s body.

Modern spacecraft are equipped with both rigid members and elastic structures, such as antennae, solar batteries, and outboard rods with metering instruments. These devices require passive or active stabilization for normal operation of the spacecraft.

The major control operations of elastic structures and their stabilization are based on the modern theory of analytical design of the best regulators for the systems with distributed parameters [3, 4].

It should be noted that for the objects described with the help of the system of differential or integro-differential equations with partial derivatives, the optimization system of the control-determining equations comprises a non-linear system of differential and integro-differential equations with partial derivatives [3]. The resolution of this system is a rather complicated task in both the implementation of computation procedures and the search for algorithms that provide a good convergence of the obtained solutions.

This study’s objectives are first, to perform a transition from differential equations with partial derivatives to an infinite system of standard differential equations in the form of the state space. This uses a spectral method of the theory of control [5, 6] for an elastic distributed object (an aircraft fuselage or a rocket body) with parameters dependent on the spatial variable and with regard to the inner resistance according to Voigt [2]. The second objective is to synthesize the law of control for the suppression of oscillations and perform an analysis of the closed system.


1. Mathematical model of the controlled object

It is assumed in this study that the elastic oscillations of both the aircraft fuselage and the rocket body are sufficiently accurately described by the equation of the flexible beam of the variable cross section with regard to the inner resistance as per Voigt, which, according to [2], appears as follows:

μx2yx,tt2+2x2EJx2yx,tx2++hxt2x2EJx2yx,tx2=fx,t,μ0, μ0, x(0, l), y(0, l), EJ(0, E0, J0),F(0, F0), h(0, h0), t(0, t0), (1)

where x is the spatial variable,

t0 is time,

yx,t is the beam-axis bending measured in a perpendicular direction to the non-deformed beam axis,

μx is the length unit weight,

EJx is the flexural stiffness,

E is the elastic modulus,

J is the moment of inertia of the beam cross section relative to the section’s neutral axis perpendicular to the oscillation plane,

fx,t is the external distributed transversal load attributed to the beam-length unit, and

h(x) is the coefficient of the inner resistance, as per Voigt.


Equation (1) is the following:

μ¯x¯2y¯x¯,t¯t¯2+2EJ¯x¯x¯22y¯x¯,t¯x¯2+2EJ¯x¯x¯3y¯x¯,t¯x¯3+EJ¯x¯4y¯x¯,t¯x¯4+μ¯x¯t¯2EJ¯x¯x¯22y¯x¯,t¯x¯2+2EJ¯x¯x¯3y¯x¯,t¯x¯3+EJ¯x¯4y¯x¯,t¯x¯4=f¯x¯,t¯ (2)

Let (2) be considered as a mathematical model of the controlled object with initial conditions

yx, 0=f1x, y¯x, 0/t¯=f2x, x0, l (3)

and boundary conditions

2y¯(l, t)/x¯2=U¯t, 2y¯(0, t)/x¯2=3y¯0, t¯/x¯3=3y¯(l, t)/x¯3=0, t0. (4)

Let differential equation (2), initial conditions (3), and boundary conditions (4) be reduced to a dimensionless form. The dimensionless variables are introduced as

μ=μ/μ0, x=x/l, y=y/l, EJ=EJ(E0J0), f=f/f0,h=h/h0, t=t/t0, f1=f1/l, f2=f2t0/l, U=U/l,  (5)

where μ0, E0J0, f0, h0, t0 are some nominal values of appropriate variables.

In the new variables in (5), the differential equation of the controlled object will be the following:

μ¯2yt2+a12EJx22yx2+a2EJx3yx3+a3EJ4yx4+htb12EJx22yx2+b2EJx3yx3+b3EJ4yx4=cf,μ(0, 1), x(0, 1), y(0,1), EJ(0,1), h(0,1). (6)

The coefficients of equation (6) are determined with expressions as

a1=a3=E0J0t02/(l4μ0), a2=2E0J0t02/l4μ0,b1=b3=h0E0J0t02/(l4μ0), b2=2h0E0J0t02/l4μ0, c=f0t02/μ0l. (7)

The initial conditions are

yx, 0=f1x, y(x, 0)/t=f2x,  x0,1 (8)

The boundary conditions are

2y(1,t)/x2=Ut, 2y(0, t)/x2=3y(0, t)/x3=3y(l, t)/x3=0, t0 (9)

Then, based on the properties of the spectral features in [5], the expressions for the matrix of spectral representation of the controlled object is obtained.


2. Spectral representation of the task

Let it be assumed that the function describing the controlled object’s condition yx, t is a substantial one-valued limited function with square integrability in the area of the spatial variable xa,b, and boundary conditions are applied at the points a=a+0, b=b-0 and t0,t0, t0.

The function yx, t with regard to the boundary conditions can be presented as follows:

yx, t=y0x, t+φa0t·1a-x+φb0t·1x-b, (10)

where y0x, t is the function coinciding with the function yx, t at the interval xa+0, b-0,

φa0 is the value of the single jump function at the boundary x=a+0,

φb0 is the value of the single jump function at the boundary x=b-0, and

 1a+0-x=1, xa+0,0, x>a+0, 1(x-b+0)=1, xb-0,0, x<b-0.

The generalized variable [7] of function (10) on x will be as follows:

y(x, t)x=y0(x, t)x-φa0t·δa-x+φb0t·δx-b.

For the m- variable, the following expression can be written as

myx, txm=my0x, txm-j=1m-2φaj(t)m-jδa-xxm-j-φbjtm-jδx-bxm-j.

Function y0(x, t) shall be decomposed in the Fourier series according to the system of orthonormal functions Ph, t, h=1, on the variation interval xa, b

y0(x, t) = h=1Ф0h, tP(h, x),  Ф0(h, t)=aby0(x, t)P(h, x)dx (11)

Using spectral-feature properties and with regard to a=0, b=1, the transition from the differential equation with partial variables (2) at the initial conditions (3) and the boundary conditions (4) is performed to the system of standard differential equations as follows:

PμФ¨0+a1PEJ2+i=1kP2EJiP2Ф0+a2PEJ1+i=1kP1EJi(P3Ф0+Г321)+a3PEJP4Ф0+Г421+b1PhPEJ2+i=1kP2EJiP2Ф0+b2PhPEJ1+i=1kP1EJi(P3Ф0+Г321)+b3PhPEJP4Ф0+Г421=cФf (12)

where Ф0Rh, h=1,  is the vector of the spectral feature of function y0x, t with components

 Ф0h,t=01y0(x,t)P(h,x)dx, h=1, ;

Pμ, PEJ, Ph are the infinite-dimensional square operational matrices of the first multiplier of the spectral properties of functions μx, EJx, hx accordingly, whose elements are calculated with the expressions

Pμh, h=01Ph, xPh, xμxdx, PEJh, h=01Ph, xPh, xEJxdx,Phh, h=01Ph, xPh, xhxdx, h, h=1, ;

PEJ1, PEJ2 are the infinite-dimensional square operational matrices of the multipliers EJx/dx, 2EJx/dx2,  whose elements are determined with the expressions

PEJkh, h=01kτkPh, τPh, τEJτdτ, k=1,2, h, h=1, ;

ФfRh, h=1,  is the vector of the spectral property of function  with the components

Фfh,t=01f(x,t)P(h,x)dx, h=1, ;                        

Pm is the infinite-dimensional square operational matrix of differentiation with the elements calculated according to the expression

Pmh, h=01Ph, xmPh, xxmdx, h, h=1, , m=1,4,                                                       

Гm21Rn, n=1, , m=3,4 are vectors of the spectral properties of the boundary conditions with the elements

Γm21h=01φ12m-1δ(x-1)xm-1Ph, xdx,   h=1, , m=3, 4.

PνEJi, i=1,k, ν=1, 2 are operational matrices describing the jumps of function EJx at interval x0, 1 calculated with the expression

PνEJih, h=01Ph, xPh, xφiν-1δ(x-xi)xν-1dx, h=1, , i=1, k, ν=1, 2

Expression (12) is reduced to the following:

Ф¨0=-Pμ-1a1PEJ2+i=1kP2EJiP2+a2PEJ1+i=1kP1EJiP3+a3PEJP4Ф0++a2Pμ-1PEJ1+i=1kP1EJiГ321+a3PEJГ421++Pμ-1Phb1PEJ2+i=1kP2EJiP2+b2PEJ1+i=1kP1EJiP3+b3PEJP4Ф0++Pμ-1Phb2PEJ1+i=1kP1EJiГ321+b3PEJГ431+cPμ-1Фf. (13)

The new variable Ф1=Ф˙0 is introduced and represented with equation (13) in the form of the system of vector–matrix equations in Cauchy’s integral formula as

Ф˙0=Ф1,Ф˙1=-Pμ-1a1PEJ2+i=1kP2EJiP2+a2PEJ1+i=1kP1EJiP3+a3PEJP4Ф0++a2Pμ-1PEJ1+i=1kP1EJiГ321+a3PEJГ421++Pμ-1Phb1PEJ2+i=1kP2EJiP2+b2PEJ1+i=1kP1EJiP3+b3PEJP4Ф0++Pμ-1Phb2PEJ1+i=1kP1EJiГ321+b3PEJГ431+cPμ-1Фf. (14)

The value of moment u1t and its derivative in time u2t=u1t/t are considered as control activities at the object’s right boundary. The following designations are introduced:

A=a1PEJ2+i=1kP2EJiP2+a2PEJ1+i=1kP1EJiP3+a3PEJP4,A~=b1PEJ2+i=1kP2EJiP2+b2PEJ1+i=1kP1EJiP3+b3PEJP4,B=a2PEJ1+i=1kP1EJi Px=1+a3PEJP/xx=1,B~=b2PEJ1+i=1kP1EJi Px=1+b3PEJP/xx=1. (15)

Expressions (15) use the designations of vectors  Px=1=colon P1,x, P2,x,...x=1, P/xx=1=colonP(1,x)x, P(2,x)x,...x=1.

With regard to designations (15), the system (14) can be written in the vector–matrix form as

Ф=AФ+Bu+Mv,  (16)

where Ф=colon Ф0, Ф1Rn, n=2h, h=1,  is the vector of the condition,

u=colon u1, u2 is the vector of control, and

ν=colon 0, Фf is the vector of disturbance.

Matrices A, B, and M are the following:

A=0I-Pμ-1A-Pμ-1PhA~, B=0I-Pμ-1B-Pμ-1PhB~, M=000cPμ-1. (17)

Thus, the transition from the description of the controlled object of equation with partial derivatives (2) with the set initial and boundary conditions (3) and (4) is performed to the system of standard differential equations (16) in the form of the state space with permanent coefficients.

Expression (16) is added with the following expression:

θ=DФ, D=D 0, (18)

where θRr is the vector of measured variables – values y (x,t) at the points where the sensors are installed, and D is the matrix, whose lines are composed of the orthonormal functions Ph,x, h=1,  used for splitting into the Fourier series (11) and calculated at the points of measurement.

An analysis of the spectral representation of the controlled object (14) demonstrates that the boundary conditions are included in the object’s equation, which allows control to be performed from the object’s boundaries. Both bending moment and lateral force can be applied on the beam ends as the control activities; therefore, expressions (14) consider the members proportional to the second and third derivatives of function y (x,t) per the spatial variable x at the object’s right boundary.


3. Calculation of the matrix of the controlled object’s spectral representation and regulator synthesis

Let the distributed controlled object (2)-(4) with coefficients that are the functions of spatial coordinates with the following baseline data be considered as:

l=1, hx=0.0011+x, fx,t=e-0.5tδx-x*, x*=0.8,yx,0=-0.84+sinπx, y/tt=0=0. (19)

The distribution of weight and rigidity is

μx=105, 0<x0.45,705, 0.45<x0.65,141, 0.65<x<1. EJx=88, 0<x0.45,146, 0.45<x0.65,117, 0.65<x<1, (20)

The dimensionless coefficients are obtained from (7) after the selection of the following nominal values:

μ0=146, E0J0=705, f0=1, h0=1, t0=1.

The relative distribution of weight and rigidity will be the following for the selected values (20):

μx=0.60, 0<x0.45,1, 0.45<x0.65,0.80, 0.65<x<1. EJx=0.15, 0<x0.45,1, 0.45<x0.65,0.2, 0.65<x<1,

and the numerical values of the coefficients in (7) will be the following:

a1=a3=b1=b3=0.2071, a2=b2=0.4142, c=0.0014.

The following will be used as the system of orthonormal functions:

P=2cos2i-1πx/2, i=1,. (21)

The values of the controlled-object matrix are provided, which consider (17). The calculations of matrix D also consider the fact that measurements are conducted at point x=0.7:

A=0n×nInA21A22, B=0n×10n×1B21B22, M=0n×10n×10n×1M22, D=D110. (22)

A21=5.71-74.4652.84...-0.31-233.71872.12...0.3910.92383.40..............., A22=0.01-0.05-0.10...0-0.351.58...00.09-2.55..............., B21=-2.848.40-10.95..., B22=-0.010.02-0.02..., M22=10-2·0.760.240.09...0.240.580...0.0900.68...............,D11=0.64-1.401.00.... (23)

The synthesis of the continuous control unit is conducted for the controlled object (16) with matrices (22) and (23) based on LQ-optimization and the theory of supervising devices in accordance with the procedure described in [6]. The control unit equation is expressed as

ξ˙=Arξ+Brθ,u=Crξ+Drθ, (24)

where ξRα, α=n-r is the vector of the control unit conditions and Ar, Br, Cr,Dr constitute the numerical matrix. The calculations consider the five amplitudes of the spatial modes.

The values of the control unit matrix are provided as






Cr=36.0410.052.8367.151.660.400.591.172.620.060.0100.1100000, Dr=119.740.21.

Figures 1 and 2 present the results of the closed-system analysis.


Fig. 1. Value of regulated variable at point x = 0.7


The diagram of the transition process presented in Fig. 1 demonstrates that the disturbance effect is compensated with error that does not exceed 3%. The control activities applied at the elastic object’s right boundary are active for 1.5 sec and do not exceed the module’s allowable values.


Fig. 2. The control actions. а: moment u1(t) at the object’s right boundary and б: time derivative u2(t) = ∂u1(t)/∂t at the object’s right boundary


Based on the spectral method of the theory of control, this study performed a transition from an equation with partial derivatives to an infinite system of standard differential equations in Cauchy’s form. The partial derivatives describe an aircraft’s elastic oscillations with regard to the inner resistance as per Voigt with irregular distribution of weight and rigidity in the structure.

Using LQ-optimization and the theory of supervising devices, the control unit was synthesized, and the watch unit was constructed with correction of the recovery error.

The obtained results can be used for the construction of aircraft control systems with active dynamic compensation of elastic oscillations. The application of these findings can facilitate an improvement in aircraft dynamics, a decrease in navigation errors, and a reduction in structural loads and stresses.


About the authors

Vladimir A Koval’

Yuri Gagarin State Technical University of Saratov, Saratov, Russian Federation

Author for correspondence.

(Dr. Sci. (Techn.)), Professor.

77, Politechnicheskaya st., Saratov, 410054, Russian Federation

Olga Yu Torgashova

Yuri Gagarin State Technical University of Saratov, Saratov, Russian Federation


(Dr. Sci. (Techn.)), Professor.

77, Politechnicheskaya st., Saratov, 410054, Russian Federation

Michail F Stepanov

Yuri Gagarin State Technical University of Saratov, Saratov, Russian Federation


(Dr. Sci. (Techn.)), Professor.

77, Politechnicheskaya st., Saratov, 410054, Russian Federation


  1. Красовский А.А. Системы автоматического управления полетом и их аналитическое конструирование. - М.: Наука, 1973. - 560 с.
  2. Лебедев А.А., Чернобровкин Л.С. Динамика полета беспилотных летательных аппаратов. - М.: Машиностроение, 1973. - 616 с.
  3. Сиразетдинов Т.К. Оптимизация систем с распределенными параметрами. - М.: Наука, 1977. - 480 с.
  4. Дегтярев Г.Л., Сиразетдинов Т.К. Теоретические основы оптимального управления упругими космическими аппаратами. - М.: Машиностроение, 1986. - 216 с.
  5. Коваль В.А. Спектральный метод анализа и синтеза распределенных систем. - Саратов: Изд-во Сарат. гос. техн. ун-та, 2010. - 148 с.
  6. Коваль В.А., Торгашова О.Ю. Решение задач анализа и синтеза для пространственно-двумерного распределенного объекта, представленного бесконечной системой дифференциальных уравнений // АиТ. - 2014. - № 2. - С. 54-71.
  7. Гельфанд И.М., Шилов Г.Е. Обобщенные функции и действия над ними. - М.: Гос. изд-во физ.-мат. литературы, 1959. - 472 с.

Supplementary files

Supplementary Files
1. Fig. 1. Value of regulated variable at point x = 0.7

Download (18KB)
2. Fig. 2. The control actions. а: moment u1(t) at the object’s right boundary and б: time derivative u2(t) = ∂u1(t)/∂t at the object’s right boundary

Download (27KB)



Abstract: 65

PDF (Russian): 24

PDF (English): 16


Article Metrics

Metrics Loading ...



  • There are currently no refbacks.

Copyright (c) 2017 Samara State Technical University

Creative Commons License
This work is licensed under a Creative Commons Attribution 4.0 International License.

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies