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参考文献 1
PERSOVAM G, SOLOVEICHIKY G, BELOVV K, et al . Modeling of aerodynamic heat flux and thermoelastic behavior of nose caps of hypersonic vehicles [J]. Acta Astronautica, 2017, 136: 312-331.
参考文献 2
KNIGHTD, CHAZOTO, AUSTINJ, et al . Assessment of predictive capabilities for aerodynamic heating in hypersonic flow [J]. Progress in Aerospace Sciences, 2017, 90: 39-53.
参考文献 3
LIJ, CHENH, ZHANGS, et al . On the response of coaxial surface thermocouples for transient aerodynamic heating measurements [J]. Experimental Thermal & Fluid Science, 2017, 86: 141-148.
参考文献 4
VASIL’EVSKIIS A, GORDEEVA N, KOLESNIKOVA F . Local modeling of the aerodynamic heating of the blunt body surface in subsonic high-enthalpy air flow. Theory and experiment on a high-frequency plasmatron[J]. Fluid Dynamics, 2017, 52(1): 158-164.
参考文献 5
OLYNICKD . Trajectory-based thermal protection system sizing for an X-33 winged vehicle concept[J]. Journal of Spacecraft and Rockets, 1998, 35(3): 249-257.
参考文献 6
ALBANOM, MORLESR B, CIOETAF, alet , Coating effects on thermal properties of carbon carbon and carbon silicon carbide composites for space thermal protection systems [J]. Acta Astronautica, 2014, 99: 276-282.
参考文献 7
OSCARA M, ANURAGS, BHAVANIV S, et al . Thermal force and moment determination of an integrated thermal protection system [J]. AIAA Journal, 2010, 48(1): 119-128.
参考文献 8
MURACAR J, COE C F, TULINIUSJ R . Shuttle tile environments and loads[J]. Journal of the Acoustical Society of America, 1982, 70(70):91.
参考文献 9
MISERENTINOR, PINSONANDL D, LEADBETTERS A . Some space shuttle tile/strain-isolator-pad sinusoidal vibration tests [R]. NASA Technical Memorandum, NASA TM-81853, 1980.
参考文献 10
HOUSNERJ M, EDIGHOFFERH H, PARKK C . Nonlinear dynamic phenomena in the space shuttle thermal protection system [J]. Journal of Spacecraft and Rockets, 1982, 19(3): 269-277.
参考文献 11
ELSONJ M, BENNETTJ M . Calculation of the power spectral density from surface profile data [J]. Appl Optics, 1995, 34(1): 201-208.
参考文献 12
LINJ H, ZHANGY H, LIUQ S, et al . Seismic spatial effects for long-span bridges, using the pseudo excitation method [J]. Engineering Structures, 2004, 26(9): 1207-1216.
目录 contents

    Abstract

    In order to study the dynamic behaviors of the thermal protection system (TPS) and dynamic strength of the strain-isolation-pad (SIP), a two degree-of-freedom dynamic theoretical model is presented under the acoustic excitation and base excitation. The tile and SIP are both considered as the elastic body and simplified as a mass point, a linear spring and a damping element. The theoretical solutions are derived, and the reasonability of theoretical model is verified by comparing the theoretical results with the numerical results. Finally, the influences on the dynamic responses of TPS by the structural damping coefficient of TPS, elasticity modulus and thickness of SIP are analyzed. The results show that the material with higher damping, and SIP with thicker size and lower elastic modulus should be considered to reduce the dynamic responses and intensify the security of TPS. The researches provide a theoretical reference for studying the dynamic behaviors of TPS and the dynamic strength of SIP. Besides, the dynamic theoretical model can be used as a quick analysis tool for analyzing the dynamic responses of TPS during the initial design phase.

    摘要

    暂无

  • 0 Introduction

    The space plane orbiter is subject to aerodynamic heating during the lift-off and re-entry phases[1,2,3,4]. A thermal protection system (TPS) is necessary to ensure the internal structure of the orbiter within the sustainable temperature range[5,6,7]. The ceramic tile is the most widely used heat insulation structure, attached on the surface of structure through a strain-isolation-pad (SIP). In addition to resisting the aerodynamic heating, TPS is subject to the acoustic excitation on the outer surface of tile and the base excitation of structure as well[8]. The above two excitations are the dynamic mechanical loads, the dynamic responses including the acceleration of TPS and the dynamic stress of SIP will be generated. Once the value of dynamic stress of SIP exceeds the strength value, the failure will happen on SIP, and it will result in the separation between the tile and structure of the orbiter. The disastrous accident will happen to the space plane orbiter because of losing the thermal protection function. Therefore, the dynamic analysis for tile and SIP is necessary when designing TPS.

    The studies on dynamic behaviors of TPS are very few, and they were mainly analyzed by experimental method. Miserentino et al.[9] studied the dynamic responses of the tile/SIP system under the sinusoidal excitation by experiments. A dynamic instability is described which has large in-plane motion at a frequency one-half that of the nominal driving frequency. Considering the nonlinear stiffening hysteresis and viscous behavior of SIP, Housner et al.[10] studied the effects of the sinusoidal motions of the skin on the dynamic responses of the tile/SIP system.

    The dynamic behaviors of TPS can be studied by the above experimental method, but it is limited by experimental environment and expenses. In order to study the dynamic behaviors of TPS and analyze the dynamic strength of SIP, the tile and SIP are both considered as the elastic body and simplified as a mass point, a linear spring and a damping element. A two degree-of-freedom dynamic theoretical model for random dynamic behaviors of TPS is presented under the acoustic excitation and base excitation. The theoretical solutions are derived and compared with the numerical solutions. Finally, the parametric studies for the dynamic behaviors of TPS are conducted.

  • 1 Vibration Environment

    TPS is under the multi-task environments, including aerodynamic heating, aerodynamic force and base excitation from the structure of orbiter. This paper focuses on the dynamic behaviors of TPS, and the dynamic loads are the acoustic pressure and base excitation[8] (Fig.1) which mainly occur during the lift-off and re-entry phases. The base excitation is generally the acceleration of structure, which comes from the vibration of the engine and acts on the bottom of TPS. However, the acoustic excitation mainly comes from the pulsation of the turbulent boundary layer and acts on the outer surface of TPS.

    Fig.1
                            Tile dynamic load sources

    Fig.1 Tile dynamic load sources

    The acoustic excitation and base excitation are random[8], so the random vibration method should be used in the dynamic analysis of TPS. The power spectral density (PSD) function of the acoustic excitation is usually the band-limited white noise with the constant value during the frequency range. But the PSD function of the acceleration base excitation is usually ladder spectrum, and the typical PSD function of it is shown in Fig.2. The PSD functions are generally obtained by the experiment and signal processing method. Firstly, the time-domain signal is measured by experiment, and then it is converted into frequency-domain excitation by the fast Fourier transform. Finally, the PSD function is obtained by signal processing method[11].

    Fig.2
                            Typical acceleration base PSD function

    Fig.2 Typical acceleration base PSD function

  • 2 Dynamic Theoretical Model

    The elasticity modulus of the tile is usually between 10 MPa and 50 MPa, and that of SIP is usually between 1 MPa and 10 MPa. Compared with SIP, the tile cannot be treated as a rigid body, so the tile is considered as the elastic body in this paper. As the width of TPS is small and usually between 50 mm and 200 mm, the acoustic excitation and base excitation are approximately uniformly distributed. Since the effect of the coating on the dynamic behaviors of TPS is very small, this paper does not consider its influence. According to the above discussions, the assumptions made in the dynamic theoretical model are given by:

    (1) The dynamic system obeys the stationary random vibration, and all the excitations obey the Gauss stochastic process.

    (2) The tile is simplified as a mass point, a linear spring and a damping element to describe the inertial force, elastic force and damping force of tile.

    (3) The SIP is simplified as a mass point, a linear spring and a damping element to describe the inertial force, elastic force and damping force of SIP.

    (4) The acoustic excitation and base excitation are uniformly distributed on the outer surface of tile and bottom of SIP, respectively.

    According to the above assumptions, a two degree-of-freedom dynamic theoretical model for the random vibration of TPS is presented under the acoustic excitation and base excitation (Fig.3). In the theoretical model, Sf (ω) and Sÿ (ω) are the PSD functions of acoustic excitation and acceleration base excitation respectively; m 1 and m 2 are the masses of the tile and SIP respectively; k 1 and k 2 are the linear stiffness coefficients of the tile and SIP respectively; c 1 and c 2 are the viscous damping coefficients of the tile and SIP respectively; x 1 and x 2 are the displacements of the tile and SIP respectively. The acoustic excitation acts on the outer surface of the tile, and the base excitation acts on the bottom of SIP.

    Fig.3
                            Dynamic theoretical models

    Fig.3 Dynamic theoretical models

  • 3 Acoustic Excitation

    The two degree-of-freedom dynamic theoretical model under the acoustic excitation is shown in Fig.3(a), and the motion equation of the dynamic system is given by

    Mx¨(t)+Kx(t)+Cx˙(t)=Ff(t)
    (1)

    where M is the mass matrix, K the stiffness matrix, C the damping matrix, F f the external acoustic load vector and x the displacement vector.

    M=m100m2K=k1-k1-k1k1+k2C=c1-c1-c1c1+c2Ff(t)=f(t)0Tx=x1x2T
    (2)

    Suppose the acoustic excitation f˜(t)=Sf(ω)eiωt , and then the displacement, velocity and acceleration can be given by

    x˜1(t)=H1(ω)f˜(t),x˜2(t)=H2(ω)f˜(t)x˙˜1(t)=H1(ω)f˙˜(t),x˙˜2(t)=H2(ω)f˙˜(t)x¨˜1(t)=H1(ω)f¨˜(t),x¨˜2(t)=H2(ω)f¨˜(t)
    (3)

    where Hi is the frequency response function between the displacement xi and the acoustic pressure f.

    Substituting Eq.(3) into Eq.(1) yields

    AH1H2=10
    (4)
    A=-ω2m1+k1+iωc1-k1-iωc1-k1-iωc1-ω2m2+k1+k2+iω(c1+c2)
    (5)

    So the frequency response function Hi can be derived as

    H1(ω)=iω(c1+c2)+k1+k2-ω2m2(-m1ω2+iωc1+k1)[-m2ω2+iω(c1+c2)+(k1+k2)]-(iωc1+k1)2H2(ω)=iωc1+k1(-m1ω2+iωc1+k1)[-m2ω2+iω(c1+c2)+(k1+k2)]-(iωc1+k1)2
    (6)

    Based on the pseudo excitation method (PEM)[12], the PSD functions of responses can be calculated by

    Sx1(ω)=x˜1x˜¯1,Sx2(ω)=x˜2x˜¯2Sx˙1(ω)=x˙˜1x˙˜¯1,Sx˙2(ω)=x˙˜2x˙˜¯2Sx¨1(ω)=x¨˜1x¨˜¯1,Sx¨2(ω)=x¨˜2x¨˜¯2
    (7)

    where x¨˜¯i , x˙˜¯i and x˜¯i are the conjugate complex of x¨˜i , x˙˜i and x˜i respectively.

    By substituting Eqs.(3,6) into Eq.(7), the PSD functions of the responses are given by

    Sx1(ω)=|H1|2Sf,Sx2(ω)=|H2|2SfSx˙1(ω)=ω2|H1|2Sf,Sx˙2(ω)=ω2|H2|2SfSx¨1(ω)=ω4|H1|2Sf,Sx¨2(ω)=ω4|H2|2Sf
    (8)

    where Sx¨i(ω) , Sx˙i(ω) and Sxi(ω) are the PSD functions of acceleration, velocity and displacement respectively.

    By integrating the above PSD functions in the frequency domain, the corresponding mean square values are calculated by

    ψx12=ω1ω2Sx1(ω)dω,ψx22=ω1ω2Sx2(ω)dωψx˙12=ω1ω2Sx˙1(ω)dω,ψx˙22=ω1ω2Sx˙2(ω)dωψx¨12=ω1ω2Sx¨1(ω)dω,ψx¨22=ω1ω2Sx¨2(ω)dω
    (9)

    where ψx¨i , ψx˙i and ψxi are root-mean-square (RMS) values of the acceleration, velocity and displacement, respectively.

    According to the elastic force and damping force of SIP, the RMS values of the total force ψF and stress ψσ for SIP are calculated by

    ψF=k2ψx2+c2ψx˙2
    (10)
    ψσ=ψFA
    (11)
  • 4 Base Excitation

    The two degree-of-freedom dynamic theoretical model under the base excitation is shown in Fig.3(b), and the motion equation of the dynamic system is given by

    Mx¨(t)+Kx(t)+Cx˙(t)=Fy(t)
    (12)

    where F y is the external base load vector.

    Fy=0k2y(t)+c2y˙(t)T
    (13)

    Suppose the base excitation y˜=Sy(ω)eiωt , and then the displacement, velocity and acceleration can be given by

    x˜1(t)=H1(ω)y˜(t),x˜2(t)=H2(ω)y˜(t)x˙˜1(t)=H1(ω)y˙˜(t),x˙˜2(t)=H2(ω)y˙˜(t)x¨˜1(t)=H1(ω)y¨˜(t),x¨˜2(t)=H2(ω)y¨˜(t)
    (14)

    where Hi is the frequency response function between the displacement xi and the base excitation y. Besides Hi is also the frequency response function between the acceleration x¨i and excitation y¨ .

    Substituting Eq.(14) into Eq.(12) yields

    A'H1H2=0k2+iωc2
    (15)
    A'=-ω2m1+k1+iωc1-k1-iωc1-k1-iωc1-ω2m2+k1+k2+iω(c1+c2)
    (16)

    So the frequency response function Hi can be derived as

    H1(ω)=(-iωc1-k1)(iωc2+k2)(iωc1+k1)2-(-m1ω2+iωc1+k1)[-m2ω2+iω(c1+c2)+(k1+k2)]H2(ω)=-(-m1ω2+iωc1+k1)(iωc2+k2)(iωc1+k1)2-(-m1ω2+iωc1+k1)[-m2ω2+iω(c1+c2)+(k1+k2)]
    (17)

    Based on the PEM, the PSD functions of responses can be calculated by

    Sx1(ω)=x˜1x˜¯1,Sx2(ω)=x˜2x˜¯2
    Sx˙1(ω)=x˙˜1x˙˜¯1,Sx˙2(ω)=x˙˜2x˙˜¯2
    (18)
    Sx¨1(ω)=x¨˜1x¨˜¯1,Sx¨2(ω)=x¨˜2x¨˜¯2

    By substituting Eqs.(14,17) into Eq.(18), the PSD functions of the responses are given by

    Sx¨1(ω)=|H1|2Sy¨,Sx¨2(ω)=|H2|2Sy¨Sx˙1(ω)=|H1|2Sy¨/ω2,Sx˙2(ω)=|H2|2Sy¨/ω2Sx1(ω)=|H1|2Sy¨/ω4,Sx2(ω)=|H2|2Sy¨/ω4
    (19)

    By integrating the above PSD functions in the frequency domain, the corresponding RMS values are calculated. And according to the Newton’s Second Law, the RMS values of the total force ψF and stress ψσ for SIP are calculated by

    ψF=m1ψx¨1+m2ψx¨2
    (20)
    ψσ=ψFA
    (21)
  • 5 Numerical Verification

    An example is presented in this paper to verify the dynamic theoretical model by the comparisons between the theoretical and numerical solutions. In the example, the length and width of TPS are both 150 mm, besides, the thickness t, elasticity modulus E, Poisson’s ratio ν, density ρ and structural damping coefficient g of the tile and SIP are listed in Table1. The corresponding mechanical parameters for theoretical model are listed in Table2. The PSD function of the acoustic excitation on the outer surface of tile is band-limited white noise with the constant value 1 000 N2/Hz in the frequency ranges from 20 Hz to 2 000 Hz. However, the PSD function of the acceleration base excitation is the ladder spectrum shown in Fig.2. Finally, structural damping coefficient g can be translated into the viscous damping coefficient cn through the natural frequency ωn

    Table 1 Material properties of TPS

    Part t/mm E/MPa ν ρ/(kg·m-3) g/%
    Tile54.860.00.254204
    SIP5.201.460.405214

    Table 2 Mechanical parameters of theoretical model

    Part m/kg k/(kN·mm-1) c/( N·s/m)
    Tile0.517 924.662.21
    SIP0.060 96.3256.98
    cn=gmnωn
    (22)

    The finite element numerical model is established as shown in Fig.4, and the numerical results are analyzed by the software MSC/NASTRAN. The range of numerical results and the values of theoretical results are listed in Table3. According to the results, the acceleration response of tile is greater than that of SIP under the both acoustic and base excitations, and all the theoretical results almost fall within the range of numerical results. Besides, theoretical results are close to the maximum values of numerical results. So the reasonability of the dynamic theoretical model is verified, and the dynamic theoretical model can be used to estimate the acceleration responses of tile/SIP and the stress response of SIP.

    Fig.4
                            3D finite element models of TPS

    Fig.4 3D finite element models of TPS

    Table 3 Comparisons between theoretical and numerical results

    ExcitationMethodSIPTile
    ψx¨2 /(km·s-2) ψσ /MPa ψx¨1 /(km·s-2)
    BaseFEM(0.81,3.18)(0.054,0.094)(2.71,4.11)
    Theoretical3.220.103.97
    AcousticFEM(0,9.61)(0.18,0.26)(8.84,11.20)
    Theoretical8.480.2610.37
  • 6 Discussion

    The influences on the random dynamic responses of TPS by the structural damping coefficient g, the thickness of SIP t 2 and the elasticity modulus of SIP E 2 are studied in this paper (Figs.57). The results show that the higher structural damping coefficient of TPS and the thicker SIP can reduce the responses of the dynamic system effectively. So the material with higher damping and SIP with thicker size should be considered when designing TPS.

    Fig.5
                            Dynamic responses vs. structural damping coefficient

    Fig.5 Dynamic responses vs. structural damping coefficient

    Fig.6
                            Dynamic responses vs. thickness of SIP

    Fig.6 Dynamic responses vs. thickness of SIP

    Fig.7
                            Dynamic responses vs. elasticity modulus of SIP

    Fig.7 Dynamic responses vs. elasticity modulus of SIP

    According to Eq.(22), the higher elasticity modulus of SIP can result in a higher viscous damping. The higher damping coefficient will reduce the vibration of TPS. However, the higher elasticity modulus of SIP will intensify the vibration. When the elasticity modulus of SIP is lower than a critical value, the effect of the higher elasticity modulus of SIP is greater than that of the higher viscous damping. When the elasticity modulus of SIP is higher than the critical value, the effect of the higher elasticity modulus of SIP is smaller than that of the higher viscous damping. So as the elasticity modulus of SIP increases, all the responses increase firstly and then decrease. Above analysis is conducted in the case of changing elasticity modulus of SIP only, but the damping of actual material usually decreases with the increasing stiffness. So SIP with lower elastic modulus should be considered to reduce the vibration of TPS.

  • 7 Conclusions

    (1) A two degree-of-freedom dynamic theoretical model is presented to study the dynamic behaviors of TPS and dynamic strength of SIP under the acoustic excitation and base excitation. The tile and SIP are both considered as elastic body and simplified as a mass point, a linear spring and a damping element. And the reasonability of the theoretical model is verified by the comparisons between the theoretical and numerical solutions.

    (2) The material with higher damping, and SIP with thicker size and lower elastic modulus should be used to reduce the dynamic responses and intensify the integrity and security of TPS.

    The paper provides a reference foundation for studying the dynamic behaviors of TPS and the dynamic strength of SIP. Besides, the dynamic theoretical model can be used as a quick analysis tool for the dynamic responses of TPS during the initial design phase.

  • References

    • 1

      PERSOVA M G, SOLOVEICHIK Y G, BELOV V K, et al . Modeling of aerodynamic heat flux and thermoelastic behavior of nose caps of hypersonic vehicles [J]. Acta Astronautica, 2017, 136: 312-331.

    • 2

      KNIGHT D, CHAZOT O, AUSTIN J, et al . Assessment of predictive capabilities for aerodynamic heating in hypersonic flow [J]. Progress in Aerospace Sciences, 2017, 90: 39-53.

    • 3

      LI J, CHEN H, ZHANG S, et al . On the response of coaxial surface thermocouples for transient aerodynamic heating measurements [J]. Experimental Thermal & Fluid Science, 2017, 86: 141-148.

    • 4

      VASIL’EVSKII S A, GORDEEV A N, KOLESNIKOV A F . Local modeling of the aerodynamic heating of the blunt body surface in subsonic high-enthalpy air flow. Theory and experiment on a high-frequency plasmatron[J]. Fluid Dynamics, 2017, 52(1): 158-164.

    • 5

      OLYNICK D . Trajectory-based thermal protection system sizing for an X-33 winged vehicle concept[J]. Journal of Spacecraft and Rockets, 1998, 35(3): 249-257.

    • 6

      ALBANO M, MORLES R B, CIOETA F, et al , Coating effects on thermal properties of carbon carbon and carbon silicon carbide composites for space thermal protection systems [J]. Acta Astronautica, 2014, 99: 276-282.

    • 7

      OSCAR A M, ANURAG S, BHAVANI V S, et al . Thermal force and moment determination of an integrated thermal protection system [J]. AIAA Journal, 2010, 48(1): 119-128.

    • 8

      MURACA R J, COE C F, TULINIUS J R . Shuttle tile environments and loads[J]. Journal of the Acoustical Society of America, 1982, 70(70):91.

    • 9

      MISERENTINO R, PINSONAND L D, LEADBETTER S A . Some space shuttle tile/strain-isolator-pad sinusoidal vibration tests [R]. NASA Technical Memorandum, NASA TM-81853, 1980.

    • 10

      HOUSNER J M, EDIGHOFFER H H, PARK K C . Nonlinear dynamic phenomena in the space shuttle thermal protection system [J]. Journal of Spacecraft and Rockets, 1982, 19(3): 269-277.

    • 11

      ELSON J M, BENNETT J M . Calculation of the power spectral density from surface profile data [J]. Appl Optics, 1995, 34(1): 201-208.

    • 12

      LIN J H, ZHANG Y H, LIU Q S, et al . Seismic spatial effects for long-span bridges, using the pseudo excitation method [J]. Engineering Structures, 2004, 26(9): 1207-1216.

  • 贡献声明和致谢

    Mr. HUANG Jie established the models. Prof. YAO Weixing checked the models. Mr.KONG Bin, Mr. YANG Jiayong, Mr. WANG Man and Mr. ZHANG Qingmao calculated the results. All authors commented on the manuscript draft and approved the submission.

    This work was supported by the Priority Academic Program Development of Jiangsu Higher Education Institutions.

    利益冲突

    The authors declare no competing interests.

HUANGJie

Affiliation: Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R. China

Profile:Mr. HUANG Jie is a Ph.D. student at the College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics. He received his B.S. degree from Nanjing University of Aeronautics and Astronautics in 2012. His research area includes thermal protection system, hypersonic aerodynamic heating and aerothermoelasticity.

YAOWeixing

Affiliation:

1. Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R. China

2. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R. China

角 色:通讯作者

Role:Corresponding author

邮 箱:wxyao@nuaa.edu.cn.

Profile:YAO Weixing,received his B.S., M.S. and Ph.D. degrees in Northwestern Polytechnical University and then became a teacher in the College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics. His main research interests are structure fatigue, composite material structure design, structural optimum design and thermal protection system.E-mail:wxyao@nuaa.edu.cn.

KONGBin

Affiliation:

1. Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R. China

3. AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, P.R. China

Profile:Mr. KONG Bin received his M.S. degree from Nanjing University of Aeronautics and Astronautics in 2011. Now he is an engineer in AVIC Chengdu Aircraft Design and Research Institute.

YANGJiayong

Affiliation: AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, P.R. China

Profile:Mr. YANG Jiayong is a senior engineer in AVIC Chengdu Aircraft Design and Research Institute.

WANGMan

Affiliation: AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, P.R. China

Profile:Mr. WANG Man is an engineer in AVIC Chengdu Aircraft Design and Research Institute.

ZHANGQingmao

Affiliation: AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, P.R. China

Profile:Mr. ZHANG Qingmao is a professor in AVIC Chengdu Aircraft Design and Research Institute.

html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F001.jpg
html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F002.jpg
html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F003.jpg
Part t/mm E/MPa ν ρ/(kg·m-3) g/%
Tile54.860.00.254204
SIP5.201.460.405214
Part m/kg k/(kN·mm-1) c/( N·s/m)
Tile0.517 924.662.21
SIP0.060 96.3256.98
html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F004.jpg
ExcitationMethodSIPTile
ψx¨2 /(km·s-2) ψσ /MPa ψx¨1 /(km·s-2)
BaseFEM(0.81,3.18)(0.054,0.094)(2.71,4.11)
Theoretical3.220.103.97
AcousticFEM(0,9.61)(0.18,0.26)(8.84,11.20)
Theoretical8.480.2610.37
html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F005.jpg
html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F006.jpg
html/njhkhten/201901013/alternativeImage/f72bd20e-8b0e-42fd-b3d3-5a8d6712fa11-F007.jpg

Fig.1 Tile dynamic load sources

Fig.2 Typical acceleration base PSD function

Fig.3 Dynamic theoretical models

Table 1 Material properties of TPS

Table 2 Mechanical parameters of theoretical model

Fig.4 3D finite element models of TPS

Table 3 Comparisons between theoretical and numerical results

Fig.5 Dynamic responses vs. structural damping coefficient

Fig.6 Dynamic responses vs. thickness of SIP

Fig.7 Dynamic responses vs. elasticity modulus of SIP

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  • References

    • 1

      PERSOVA M G, SOLOVEICHIK Y G, BELOV V K, et al . Modeling of aerodynamic heat flux and thermoelastic behavior of nose caps of hypersonic vehicles [J]. Acta Astronautica, 2017, 136: 312-331.

    • 2

      KNIGHT D, CHAZOT O, AUSTIN J, et al . Assessment of predictive capabilities for aerodynamic heating in hypersonic flow [J]. Progress in Aerospace Sciences, 2017, 90: 39-53.

    • 3

      LI J, CHEN H, ZHANG S, et al . On the response of coaxial surface thermocouples for transient aerodynamic heating measurements [J]. Experimental Thermal & Fluid Science, 2017, 86: 141-148.

    • 4

      VASIL’EVSKII S A, GORDEEV A N, KOLESNIKOV A F . Local modeling of the aerodynamic heating of the blunt body surface in subsonic high-enthalpy air flow. Theory and experiment on a high-frequency plasmatron[J]. Fluid Dynamics, 2017, 52(1): 158-164.

    • 5

      OLYNICK D . Trajectory-based thermal protection system sizing for an X-33 winged vehicle concept[J]. Journal of Spacecraft and Rockets, 1998, 35(3): 249-257.

    • 6

      ALBANO M, MORLES R B, CIOETA F, et al , Coating effects on thermal properties of carbon carbon and carbon silicon carbide composites for space thermal protection systems [J]. Acta Astronautica, 2014, 99: 276-282.

    • 7

      OSCAR A M, ANURAG S, BHAVANI V S, et al . Thermal force and moment determination of an integrated thermal protection system [J]. AIAA Journal, 2010, 48(1): 119-128.

    • 8

      MURACA R J, COE C F, TULINIUS J R . Shuttle tile environments and loads[J]. Journal of the Acoustical Society of America, 1982, 70(70):91.

    • 9

      MISERENTINO R, PINSONAND L D, LEADBETTER S A . Some space shuttle tile/strain-isolator-pad sinusoidal vibration tests [R]. NASA Technical Memorandum, NASA TM-81853, 1980.

    • 10

      HOUSNER J M, EDIGHOFFER H H, PARK K C . Nonlinear dynamic phenomena in the space shuttle thermal protection system [J]. Journal of Spacecraft and Rockets, 1982, 19(3): 269-277.

    • 11

      ELSON J M, BENNETT J M . Calculation of the power spectral density from surface profile data [J]. Appl Optics, 1995, 34(1): 201-208.

    • 12

      LIN J H, ZHANG Y H, LIU Q S, et al . Seismic spatial effects for long-span bridges, using the pseudo excitation method [J]. Engineering Structures, 2004, 26(9): 1207-1216.