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Aeronautics and Aerospace Open Access Journal

Research Article Volume 8 Issue 4

Structural model and scheme of a piezoengine for aeronautics and aerospace

SM Afonin

National Research University of Electronic Technology, MIET, Russia

Correspondence: SM Afonin, National Research University of Electronic Technology, MIET, Moscow, Russia, Tel +74997314441

Received: December 06, 2024 | Published: December 18, 2024

Citation: Afonin SM. Structural model and scheme of a piezoengine for aeronautics and aerospace. Aeron Aero Open Access J. 2024;8(4):212-217. DOI: 10.15406/aaoaj.2024.08.00213

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Abstract

In the work the structural model and the structural scheme of a piezoengine are calculated for aeronautics and aerospace. The matrix equation of a piezoactuator is determined. The mechanical characteristic and the parameters of the PZT piezoactuator are obtained in control systems for aeronautics and aerospace. A piezoengine is used for nanoalignment and nanopositioning, compensation of temperature and gravitational deformations in aeronautics and aerospace, nanoresearh for tunel microscopy, adaptive optics, astronomy for compound telescope and satellite telescope. The linear change in the size of a piezoengine occurs by the electric field changes. A piezoengine is a piezomechanical device for converting electrical energy into mechanical energy and for actuating mechanisms, systems or its controlling by using inverse piezoeeffect. Piezoceramics include barium titanate or ferroelectric ceramics, based on lead zirconate titanate type PZT, are widely used for the production of piezoengines. The PZT piezoengine is characterized by high accuracy, small overall dimensions, simple design and control, reliability and cost effectiveness. The structural general model, the scheme and the functions a piezoengine are obtained for aeronautics and aerospace. Method of applied mathematical physics is applied for determinations the characteristics of a piezoengine with using the piezoelasticity equation and the differential equation. The static and dynamic characteristics of the PZT piezoengine are determined.

Keywords: piezoengine, structural model and scheme

Introduction

A piezoengine is used for aeronautics and aerospace.1–19 This piezoengine is applied in adaptive optics system for compound telescope and satellite telescope, astrophysics, deformable mirrors, interferometers, damping vibration, scanning microscopy.14–59 The structural model and scheme of a piezoengine are constructed.

Method

For the structural model a piezoengine is used method of mathematical physics with the solution the piezoelasticity equationfor reverse piezoeffect and differential equation at the voltage control.8–41

Si=dmiEm+sEijTjSi=dmiEm+sEijTj

and at current the control

Si=gmiDm+sDijTjSi=gmiDm+sDijTj

here SiSi ,EmEm ,dmidmi ,TjTj ,dmidmi ,gmigmi ,sEijsEij  are the relative displacement, the electric field strength, the electric induction, the mechanical field strength, its modules, the elastic compliance, the indexes i, j, m. The ordinary differential equation a piezoengine 8–41 has form

d2Ξ(x,s)dx2γ2Ξ(x,s)=0d2Ξ(x,s)dx2γ2Ξ(x,s)=0

here Ξ(x,s)Ξ(x,s) ,xx ,ss ,γγ  are the transform of the displacement, its coordinate  and parameter, the propagation coefficient and the general length l={l,δ,bl={l,δ,b an engine. For the transverse engine for x=0x=0, Ξ(0,s)=Ξ1(s)Ξ(0,s)=Ξ1(s) ;and x=hx=h ,Ξ(h,s)=Ξ2(s)Ξ(h,s)=Ξ2(s) .

Model and scheme

Its transverse solution is written

Ξ(x,s)={Ξ1(s)sh[(hx)γ]+Ξ2(s)sh(xγ)}/sh(hγ)Ξ(x,s)={Ξ1(s)sh[(hx)γ]+Ξ2(s)sh(xγ)}/sh(hγ)

here Ξ1(s)Ξ1(s) , Ξ2(s)Ξ2(s) ;are the transforms its end displacements.

The system equations of the boundary conditions for the transverse piezoengine is determined

T1(0,s)=1sE11dΞ(x,s)dx|x=0d31sE11E3(s)T1(0,s)=1sE11dΞ(x,s)dxx=0d31sE11E3(s)

T1(h,s)=1sE11dΞ(x,s)dx|x=hd31sE11E3(s)T1(h,s)=1sE11dΞ(x,s)dxx=hd31sE11E3(s)

From the reverse piezoeffect of a piezoengine at the voltage control the Laplace transform of the force causes displacement is determined

F(s)=dmiS0Em(s)sEijF(s)=dmiS0Em(s)sEij

hereS0S0 is cross sectional area.

The transform of the force causes displacement for the transverse piezoengine at the voltage control is written

F(s)=d31S0E3(s)sE11F(s)=d31S0E3(s)sE11

Then the reverse coefficient at the voltage control with U(s)=Em(s)δU(s)=Em(s)δ is determined in the form

kr=F(s)U(s)=dmiS0δsEijkr=F(s)U(s)=dmiS0δsEij

The transverse reverse coefficient at the voltage control is obtained

kr=F(s)U(s)=d31S0δsE11kr=F(s)U(s)=d31S0δsE11

Its transverse model is determined

Ξ1(s)=(M1s2)1{F1(s)+(χE11)1×[d31E3(s)[γ/sh(hγ)]×[ch(hγ)Ξ1(s)Ξ2(s)]]}

Ξ2(s)=(M2s2)1{F2(s)+(χE11)1×[d31E3(s)[γ/sh(hγ)]×[ch(hγ)Ξ2(s)Ξ1(s)]]}

χE11=sE11/S0

For the longitudinal piezoengine its longitudinal solution of the differential equation is written

Ξ(x,s)={Ξ1(s)sh[(δx)γ]+Ξ2(s)sh(xγ)}/sh(δγ)

The system of the boundary conditions for the longitudinal piezoengine is obtained

T3(0,s)=1sE33dΞ(x,s)dx|x=0d33sE33E3(s)

T3(δ,s)=1sE33dΞ(x,s)dx|x=δd33sE33E3(s)

The transform of the force causes displacement for the longitudinal piezo engine at the voltage control is written

F(s)=d33S0E3(s)sE33

The longitudinal reverse coefficient at the voltage control is obtained

kr=F(s)U(s)=d33S0δsE33

Its longitudinal structural model is determined

Ξ1(s)=(M1s2)1{F1(s)+(χE33)1×[d33E3(s)[γ/sh(δγ)]×[ch(δγ)Ξ1(s)Ξ2(s)]]}

Ξ2(s)=(M2s2)1{F2(s)+(χE33)1×[d33E3(s)[γ/sh(δγ)]×[ch(δγ)Ξ2(s)Ξ1(s)]]}

χE33=sE33/S0

From the differential equation of for the shift piezoengine its shift solution is written

Ξ(x,s)={Ξ1(s)sh[(bx)γ]+Ξ2(s)sh(xγ)}/sh(bγ)

The system of the boundary conditions for the shift piezoengine is obtained

T5(0,s)=1sE55dΞ(x,s)dx|x=0d15sE55E1(s)

T5(b,s)=1sE55dΞ(x,s)dx|x=bd15sE55E1(s)

The transform of the force causes displacement for the shift piezo engine at the voltage control is written

F(s)=d15S0E3(s)sE55

The shif reverse coefficient at the voltage control is obtained

kr=F(s)U(s)=d15S0δsE55

Its structural shift model is determined

Ξ1(s)=(M1s2)1{F1(s)+(χE55)1×[d15E1(s)[γ/sh(bγ)]×[ch(bγ)Ξ1(s)Ξ2(s)]]}

Ξ2(s)=(M2s2)1{F2(s)+(χE55)1×[d15E1(s)[γ/sh(bγ)]×[ch(bγ)Ξ2(s)Ξ1(s)]]}

χE55=sE55/S0

The equation of inverse piezo effect 3–41 is written in the general form

Si=νmiΨm+sΨijTj

here Ψm=Em,Dm is control parameter at the voltage or current control.

At x=0 and x=l for l={δ,h,b the system of the boundary conditions for a piezoengine is obtained

Tj(0,s)=1sΨijdΞ(x,s)dx|x=0νmisΨijΨm(s)

Tj(l,s)=1sΨijdΞ(x,s)dx|x=lνmisΨijΨm(s)

The transform of the force causes displacement has the general form

F(s)=νmiS0Ψm(s)sΨij

The general structural model and scheme are obtained on Figure 1

Figure 1 General scheme engine.

Ξ1(s)=(M1s2)1{F1(s)+(χΨij)1×[νmiΨm(s)[γ/sh(lγ)]×[ch(lγ)Ξ1(s)Ξ2(s)]]}

Ξ2(s)=(M2s2)1{F2(s)+(χΨij)1×[νmiΨm(s)[γ/sh(lγ)]×[ch(lγ)Ξ2(s)Ξ1(s)]]}

χΨij=sΨij/S0

here

vmi={d33,d31,d15g33,g31,g15 ,

,Ψm={E3,E3,E1D3,D3,D1 ,sΨij={sE33,sE11,sE55sD33,sD11,sD55 ,γ={γE,γD ,

cΨ={cE,cD

The general structural model and scheme of a piezoengine on Figure 1 are used to calculate systems in aeronautics and aerospace. The displacement matrix is written

(Ξ1(s)Ξ2(s))=(W(s))(Ψm(s)F1(s)F2(s))

(W(s))=(W11(s)W12(s)W13(s)W21(s)W22(s)W23(s))

here its functions

W11(s)=Ξ1(s)/Ψm(s)=νmi[M2χΨijs2+γth(lγ/2)]/Aij

Aij=M1M2(χΨij)2s4+{(M1+M2)χΨij/[cΨth(lγ)]}s3++[(M1+M2)χΨijα/th(lγ)+1/(cΨ)2]s2+2αs/cΨ+α2

W21(s)=Ξ2(s)/Ψm(s)=νmi[M1χΨijs2+γth(lγ/2)]/Aij

W12(s)=Ξ1(s)/F1(s)=χΨij[M2χΨijs2+γ/th(lγ)]/Aij

W13(s)=Ξ1(s)/F2(s)==W22(s)=Ξ2(s)/F1(s)=[χΨijγ/sh(lγ)]/Aij

W23(s)=Ξ2(s)/F2(s)=χΨij[M1χΨijs2+γ/th(lγ)]/Aij

The settled longitudinal displacements at the voltage control are used

ξ1=d33UM2/(M1+M2)

ξ2=d33UM1/(M1+M2)

To the PZT piezoengine d33 = 4×10-10 m/V, U = 50 V, M1 = 0.5 kg, M2 = 2 kg we have displacements ξ1+ξ2 = 20 nm, ξ1 = 16 nm, ξ2 = 4 nm with 10% error.

For the voltage control the equation of the direct piezo effect is written8–41

Dm=dmiTi+εEmkEk

here i, m, k are the indexes,εEmk is the permittivity. The direct coefficient kd ;for the engine at the voltage control is founded

kd=dmiS0δsEij

At the voltage control the transform of the voltage for the feedback on Figure 2 is obtained

Figure 2 Scheme engine with two feedbacks.

Ud(s)=dmiS0RδsEijΞn(s)=kdRΞn(s) ,n=1,2

here the number n of the ends engine.

Let us consider the elastic compliance of a piezoengine. At voltage control its maximum parameters are written

Tjmax=Emdmi/sEij

Fmax=EmdmiS0/sEij

At current control the maximum force is founded

Fmax=UδdmiS0sEij+FmaxS0dmiSc1εTmkSc/δ1δdmiS0sEij

here Sc , C0 are the sectional area of the capacitor, its capacitance.

Then at current control the parameters are written

Tjmax=Emdmi(1k2mi)sEij

kmi=dmi/sEijεTmk

here kmi is the coefficient of electromechanical coupling.

At current control of the parameters are founded

Tjmax=Emdmi/sDij,sDij=(1k2mi)sEij

The elastic compliance sij is written sEij>sij>sDij , here sEij/sDij1.2 . ThenCEij=S0/(sEijl) is the stiffness of the engine at voltage control, CDij=S0/(sDijl) is the stiffness at current control,CEij<C<ijCDij , Cij=S0/(sijl) is a general stiffness of an engine.

The mechanical characteristic of a piezoengine 8–41

Si(Tj)|Ψ=const=νmiΨm|Ψ=const+sΨijTj

The adjustment characteristic

Si(Ψm)|T=const=vmiΨm+sΨijTj|T=const

Then the mechanical characteristic is written

Δl=Δlmax(1F/Fmax)

Δlmax=νmiΨml ,Fmax=Tj maxS0=νmiΨmS0/sΨij

here Δlmax , Fmax are the maximum of the displacement and the force. The transverse mechanical characteristic is founded

Δh=Δhmax(1F/Fmax)

Δhmax=d31E3h ,Fmax=d31E3S0/sE11

To the PZT piezoengine d31 = 2∙10-10 m/V, E3 = 0.25∙105 V/m, h = 2.5∙10-2 m, S0 = 1.5∙10-5 m2, sE11 = 15∙10-12 m2/N the parameters are determined Δhmax = 125 nm and Fmax = 5 N with 10% error.

The relative displacement at elastic load

Δll=νmiΨmsΨijCeS0Δl ,F=CeΔl

The adjustment characteristic

Δl=νmilΨm1+Ce/CΨij

The general elastic compliance

sij=kssEij ,(1k2mi)ks1

The scheme on Figure 3 we have at the voltage control the piezoengine with first fixed end and elastic-inertial load.

Figure 3 Scheme engine with one feedback.

The function at the voltage control with fixed first end and elastic-inertial load on second end for Figure 3 has the form

W(s)=Ξ2(s)/U(s)=kr/(a3p3+a2p2+a1p+a0)

a3=RC0M2 ,a2=M2+RC0kv

a1=kv+RC0C+ijRC0C+eRkrkd ,a0=C+eCij

The function withis obtained

W(s)=Ξ(s)U(s)=kU31T2ts2+2Ttξts+1

kU31=d31(h/δ)/(1+Ce/CE11)

Tt=M2/(Ce+CE11) ,ωt=1/Tt

To the PZT piezoengine M2 = 4 kg, Ce = 0.1×107 N/m, CE11 = 1.5×107 N/m the parameters are founded Tt = 0.5×10-3 s, ωt = 2×103 s-1 with 10% error.

To d31 = 2∙10-10 m/V, h/δ = 22, Ce/CE11 = 0.1 the coefficient is determined kU31 = 4 nm/V with 10% error.

Discussion

A piezoengine is used for aeronautics and aerospace in system of adaptive optics for compound telescope and satellite telescope, deformable mirrors, interferometers, damping vibration, astrophysics for displacements of mirrors and scanning microscopy. The structural model and scheme of a piezoengine are constructed by applied method mathematical physics. For a piezoengine its displacement matrix is obtained. The schemes with the feedbacks at the voltage control are determined.

The structural model and scheme of a piezoengine for aeronautics and aerospace are obtained taking into account equation of piezoeffects and decision wave equation. We have the general structural model and scheme of a piezoengine for the longitudinal, transverse and shift deformations. The structural scheme of the piezoactuator for longitudinal, transverse, shift piezoelectric effects at voltage control converts to the general structural scheme of the piezoactuator for aeronautics and aerospace with the replacement of the following parameters:

Ψm=E3,E3,E1 ,νmi=d33,d31,d15 sΨij=sE33,sE11,sE55 ,

,l=δ,h,b .

It is possible to construct the general structural model and scheme, the transfer functions in matrix form of the piezoengine, using the solutions of the wave equation of the piezoactuator and taking into account the features of the deformations actuator along the coordinate axes. The general structural model and scheme of the piezoengine after algebraic transformations are produced the transfer functions of the piezoengine. The piezoengine with the transverse piezoeffect compared to the piezoengine for the longitudinal piezoeffect provides greater range its displacement and less force.

 

Conclusion

The general structural model model and the scheme of a piezoengine are obtained. The systems of equations are determined for the structural models of the piezoengines for aeronautics and aerospace. Using the obtained solutions of the wave equation and taking into account the features of the deformations along the coordinate axes, it is possible to construct the general structural model and scheme of a piezoengine for systems of adaptive optics and to describe its dynamic and static properties. The transfer functions in matrix form are described the deformations of the piezoengines during its operation as a part of systems of adaptive optics.

The general structural scheme and the transfer functions of a piezoengine for aeronautics and aerospace are obtained from the structural model of a piezoengine for the transverse, longitudinal, shift piezoelectric effects. The displacement matrix is founded. The parameters of the piezoengine at the voltage control are determined for aeronautics and aerospace. The static and dynamic characteristics of the PZT piezoengine are obtained.

Acknowledgments

None.

Funding

None.

Conflicts of interest

The author declares that there are no conflicts of interest.

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