A scaling procedure for measuring thermal structural vibration generated by wall pressure fluctuation
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摘要
This paper attempts to develop a scaling procedure to measure structural vibration caused simultaneously by wall pressure fluctuations and the thermal load of hypersonic flow by a wind tunnel test. However, simulating the effect of thermal load is difficult with a scaled model in a wind tunnel due to the nonlinear effect of thermal load on a structure. In this work, the temperature variation of a structure is proposed to indicate the nonlinear effect of the thermal load,which provides a means to simulate both the thermal load and wall pressure fluctuations of a hypersonic Turbulent Boundary Layer(TBL) in a wind tunnel test. To validate the scaling procedure,both numerical computations and measurements are performed in this work. Theoretical results show that the scaling procedure can also be adapted to the buckling temperature of a structure even though the scaling procedure is derived from a reference temperature below the critical temperature of the structure. For the measurement, wall pressure fluctuations and thermal environment are simulated by creating hypersonic flow in a wind tunnel. Some encouraging results demonstrate the effectiveness of the scaling procedure for assessing structural vibration generated by hypersonic flow. The scaling procedure developed in this study will provide theoretical support to develop a new measurement technology to evaluate vibration of aircraft due to hypersonic flow.
This paper attempts to develop a scaling procedure to measure structural vibration caused simultaneously by wall pressure fluctuations and the thermal load of hypersonic flow by a wind tunnel test. However, simulating the effect of thermal load is difficult with a scaled model in a wind tunnel due to the nonlinear effect of thermal load on a structure. In this work, the temperature variation of a structure is proposed to indicate the nonlinear effect of the thermal load,which provides a means to simulate both the thermal load and wall pressure fluctuations of a hypersonic Turbulent Boundary Layer(TBL) in a wind tunnel test. To validate the scaling procedure,both numerical computations and measurements are performed in this work. Theoretical results show that the scaling procedure can also be adapted to the buckling temperature of a structure even though the scaling procedure is derived from a reference temperature below the critical temperature of the structure. For the measurement, wall pressure fluctuations and thermal environment are simulated by creating hypersonic flow in a wind tunnel. Some encouraging results demonstrate the effectiveness of the scaling procedure for assessing structural vibration generated by hypersonic flow. The scaling procedure developed in this study will provide theoretical support to develop a new measurement technology to evaluate vibration of aircraft due to hypersonic flow.
This paper attempts to develop a scaling procedure to measure structural vibration caused simultaneously by wall pressure fluctuations and the thermal load of hypersonic flow by a wind tunnel test. However, simulating the effect of thermal load is difficult with a scaled model in a wind tunnel due to the nonlinear effect of thermal load on a structure. In this work, the temperature variation of a structure is proposed to indicate the nonlinear effect of the thermal load,which provides a means to simulate both the thermal load and wall pressure fluctuations of a hypersonic Turbulent Boundary Layer(TBL) in a wind tunnel test. To validate the scaling procedure,both numerical computations and measurements are performed in this work. Theoretical results show that the scaling procedure can also be adapted to the buckling temperature of a structure even though the scaling procedure is derived from a reference temperature below the critical temperature of the structure. For the measurement, wall pressure fluctuations and thermal environment are simulated by creating hypersonic flow in a wind tunnel. Some encouraging results demonstrate the effectiveness of the scaling procedure for assessing structural vibration generated by hypersonic flow. The scaling procedure developed in this study will provide theoretical support to develop a new measurement technology to evaluate vibration of aircraft due to hypersonic flow.
引文
1.Steinwolf A,White RG,Wolfe HF.Simulation of jet-noise excitation in an acoustic progressive wave tube facility.J Acoust Soc Am 2001;109(3):1043-52.
2.Yu W,Wang X,Huang X.Dynamic modelling of heat transfer in thermal-acoustic fatigue tests.Aerosp Sci Technol 2017;71:675-84.
3.Pickup N,Mangiarotty RA,Okeefe JV.Tests of a thermal acoustic shield with a supersonic jet.J Aircraft 1982;19(11):940-6.
4.Liguore LS.Thermal acoustic test and analysis model updating and correlation.Reston:AIAA;2013.Report No.:AIAA 2013-1665.
5.Wentzt KR.Thermoacoustic loads and fatigue of hypersonic vehicle skin panels.J Aircraft 1993;30(6):971-8.
6.Yu W,Zhong S,Huang X.Dynamic modeling and numerical simulation of acoustic-thermal-fluid coupling for hypersonic vehicle fatigue test.Reston:AIAA;2013.Report No.:AIAA-2013-2130.
7.Swanson AD.Hypersonic vehicle thermal structure test challenges.Reston:AIAA;2007.Report No.:AIAA-2007-1670.
8.De Rosa S.First assessment of the scaling procedure for the evaluation of the damped structural response.J Sound Vib1997;204(3):540-8.
9.Tabiei A.Scaling laws of cylindrical shells under lateral pressure.AIAA J 1997;35(10):1669-71.
10.Frostig Y,Simitses GJ.Structural similitude and scaling laws for sandwich beams.AIAA J 2002;40(4):765-73.
11.De Rosa S,Franco F.A scaling procedure for the response of an isolated system with high modal overlap factor.Mech Syst Signal Pr 2008;22(7):1549-65.
12.De Rosa S,Franco F.On the use of the asymptotic scaled modal analysis for time-harmonic structural analysis and for the prediction of coupling loss factors for similar systems.Mech Syst Signal Pr 2010;24(2):455-80.
13.Ciappi E.Analysis of the scaling laws for the turbulence driven panel responses.J Fluid Struct 2012;32:90-103.
14.Zhao X.A scaling procedure for panel Vibro-acoustic response induced by turbulent boundary layer.J Sound Vib2016;380:165-79.
15.Zhao X,Ai B.Predicting the structural response induced by turbulent boundary layer in wind tunnel.AIAA J 2017;55(4):1221-9.
16.Jeyaraj P,Padmanabhan C,Ganesan N.Vibration and acoustic response of an isotropic plate in a thermal environment.J Vib Acoust 2008;130(5):1-6.
17.Jeyaraj P,Ganesan N,Padmanabhan C.Vibration and acoustic response of a composite plate with inherent material damping in a thermal environment.J Sound Vib 2009;320(1-2):322-38.
18.Yang X,Wang C,Li Y.Vibro-acoustic response of a thermally stressed reinforced conical shell.Adv Sci Lett 2011;4(8-10):2802-6.
19.Ohayon R,Soize C.Advanced computational dissipative structural acoustics and fluid-structure interaction in low-and medium-frequency domains.Reduced-order models and uncertainty quantification.Int J Aeronaut Space 2012;13(2):127-53.
20.Geng Q,Li Y.Analysis of dynamic and acoustic radiation characters for a flat plate under thermal environments.Int J Appl Mech 2012;4(3):1250028.
21.Geng Q,Li Y.Solutions of dynamic and acoustic responses of a clamped rectangular plate in thermal environ ments.J Vib Control2016;22(6):1593-603.
22.Geng Q,Wang D,Liu Y,Li YM.Experimental and numerical investigations on dynamic and acoustic responses of a thermal post-buckled plate.Sci China Technol Sc 2016;58(8):1414-24.
23.Gupta KK.Aero-thermo-elastic-acoustics simulation of flight vehicles.AIAA J 2017;55(1):49-56.
24.Liu B.Noise radiation of aircraft panels subjected to boundary layer pressure fluctuations.J Sound Vib 2008;314(3-5):693-711.
25.De Rosa S,Franco F.Exact and numerical responses of a plate under a turbulent boundary layer excitation.J Fluid Struct 2008;24(2):212-30.
26.Liu B.Predicted and measured plate velocities induced by turbulent boundary layers.J Sound Vib 2012;331(24):5309-25.
27.Geng Q,Li H,Li Y.Dynamic and acoustic response of a clamped rectangular plate in thermal environments:Experiment and numerical simulation.J Acoust Soc Am 2014;135(5):2674-82.
28.Avsec J,Oblak M.Thermal vibrational analysis for simply supported beam and clamped beam.J Sound Vib 2007;308(3):514-25.
29.Piatak DJ,Martin KS,Russ DR.Ares launch vehicle transonic buffet testing and analysis techniques.J Spacecraft Rockets2012;49(5):798-807.
30.Hua J,Zheng S,Zhong M,et al.Recent development of a CFD-wind tunnel correlation study based on CAE-AVM investigation.Chin J Aeronaut 2018;31(3):419-27.
31.Gebbink R,Wang GL,Zhong M.High-speed wind tunnel test of the CAE aerodynamic validation model.Chin J Aeronaut 2018;31(3):439-47.
32.Weilmuenster KJ.Hypersonic thermal environment of a proposed single-stage-to-orbit vehicle.J Spacecraft Rockets 1997;34(56):697-704.
33.Kleb WL.Computational aero heating predictions for X-34.JSpacecraft Rockets 1999;36(2):179-88.
34.Berry SA.X-33 hypersonic boundary-layer transition.J Spacecraft Rockets 2001;38(5):646-57.
2.Yu W,Wang X,Huang X.Dynamic modelling of heat transfer in thermal-acoustic fatigue tests.Aerosp Sci Technol 2017;71:675-84.
3.Pickup N,Mangiarotty RA,Okeefe JV.Tests of a thermal acoustic shield with a supersonic jet.J Aircraft 1982;19(11):940-6.
4.Liguore LS.Thermal acoustic test and analysis model updating and correlation.Reston:AIAA;2013.Report No.:AIAA 2013-1665.
5.Wentzt KR.Thermoacoustic loads and fatigue of hypersonic vehicle skin panels.J Aircraft 1993;30(6):971-8.
6.Yu W,Zhong S,Huang X.Dynamic modeling and numerical simulation of acoustic-thermal-fluid coupling for hypersonic vehicle fatigue test.Reston:AIAA;2013.Report No.:AIAA-2013-2130.
7.Swanson AD.Hypersonic vehicle thermal structure test challenges.Reston:AIAA;2007.Report No.:AIAA-2007-1670.
8.De Rosa S.First assessment of the scaling procedure for the evaluation of the damped structural response.J Sound Vib1997;204(3):540-8.
9.Tabiei A.Scaling laws of cylindrical shells under lateral pressure.AIAA J 1997;35(10):1669-71.
10.Frostig Y,Simitses GJ.Structural similitude and scaling laws for sandwich beams.AIAA J 2002;40(4):765-73.
11.De Rosa S,Franco F.A scaling procedure for the response of an isolated system with high modal overlap factor.Mech Syst Signal Pr 2008;22(7):1549-65.
12.De Rosa S,Franco F.On the use of the asymptotic scaled modal analysis for time-harmonic structural analysis and for the prediction of coupling loss factors for similar systems.Mech Syst Signal Pr 2010;24(2):455-80.
13.Ciappi E.Analysis of the scaling laws for the turbulence driven panel responses.J Fluid Struct 2012;32:90-103.
14.Zhao X.A scaling procedure for panel Vibro-acoustic response induced by turbulent boundary layer.J Sound Vib2016;380:165-79.
15.Zhao X,Ai B.Predicting the structural response induced by turbulent boundary layer in wind tunnel.AIAA J 2017;55(4):1221-9.
16.Jeyaraj P,Padmanabhan C,Ganesan N.Vibration and acoustic response of an isotropic plate in a thermal environment.J Vib Acoust 2008;130(5):1-6.
17.Jeyaraj P,Ganesan N,Padmanabhan C.Vibration and acoustic response of a composite plate with inherent material damping in a thermal environment.J Sound Vib 2009;320(1-2):322-38.
18.Yang X,Wang C,Li Y.Vibro-acoustic response of a thermally stressed reinforced conical shell.Adv Sci Lett 2011;4(8-10):2802-6.
19.Ohayon R,Soize C.Advanced computational dissipative structural acoustics and fluid-structure interaction in low-and medium-frequency domains.Reduced-order models and uncertainty quantification.Int J Aeronaut Space 2012;13(2):127-53.
20.Geng Q,Li Y.Analysis of dynamic and acoustic radiation characters for a flat plate under thermal environments.Int J Appl Mech 2012;4(3):1250028.
21.Geng Q,Li Y.Solutions of dynamic and acoustic responses of a clamped rectangular plate in thermal environ ments.J Vib Control2016;22(6):1593-603.
22.Geng Q,Wang D,Liu Y,Li YM.Experimental and numerical investigations on dynamic and acoustic responses of a thermal post-buckled plate.Sci China Technol Sc 2016;58(8):1414-24.
23.Gupta KK.Aero-thermo-elastic-acoustics simulation of flight vehicles.AIAA J 2017;55(1):49-56.
24.Liu B.Noise radiation of aircraft panels subjected to boundary layer pressure fluctuations.J Sound Vib 2008;314(3-5):693-711.
25.De Rosa S,Franco F.Exact and numerical responses of a plate under a turbulent boundary layer excitation.J Fluid Struct 2008;24(2):212-30.
26.Liu B.Predicted and measured plate velocities induced by turbulent boundary layers.J Sound Vib 2012;331(24):5309-25.
27.Geng Q,Li H,Li Y.Dynamic and acoustic response of a clamped rectangular plate in thermal environments:Experiment and numerical simulation.J Acoust Soc Am 2014;135(5):2674-82.
28.Avsec J,Oblak M.Thermal vibrational analysis for simply supported beam and clamped beam.J Sound Vib 2007;308(3):514-25.
29.Piatak DJ,Martin KS,Russ DR.Ares launch vehicle transonic buffet testing and analysis techniques.J Spacecraft Rockets2012;49(5):798-807.
30.Hua J,Zheng S,Zhong M,et al.Recent development of a CFD-wind tunnel correlation study based on CAE-AVM investigation.Chin J Aeronaut 2018;31(3):419-27.
31.Gebbink R,Wang GL,Zhong M.High-speed wind tunnel test of the CAE aerodynamic validation model.Chin J Aeronaut 2018;31(3):439-47.
32.Weilmuenster KJ.Hypersonic thermal environment of a proposed single-stage-to-orbit vehicle.J Spacecraft Rockets 1997;34(56):697-704.
33.Kleb WL.Computational aero heating predictions for X-34.JSpacecraft Rockets 1999;36(2):179-88.
34.Berry SA.X-33 hypersonic boundary-layer transition.J Spacecraft Rockets 2001;38(5):646-57.