The long-range hypersonic vehicle is in an extremely harsh aerodynamic heating and vibration coupling environment. The combination of the severe high-temperature and long-time vibration environment can cause cracks, misalignment, peeling or falling off of the aircraft's thermal protection materials, and even lead to fatal safety accidents. Therefore, the ground thermal/vibration test of thermal protection materials in ultra-high temperature environment is extremely important for the safety and reliability design of hypersonic vehicles. In this paper, a high-temperature heat/vibration combined test system is established. The difficulty of measuring and controlling the surface temperature of lightweight porous insulation materials under the strong vibration is solved. Water-cooled heat insulation device is designed to protect the expensive vibration excitation equipment. The experiment realizes the thermal/vibration test of insulation materials for hypersonic vehicle at 1 500℃, obtaining the fracture morphology and crack section characteristics of the non-metallic insulating material of ceramic fiber plate. The test results of the appearance and microscopic changes of the materials before and after the test and the changes of the internal binder show that the material property is improved and the performance requirement is satisfied. The thermal/vibration combined test system under extreme high-temperature environment up to 1 500℃ and the test results provide an important basis for the evaluation of the anti-vibration capability, the determination of the thermal insulation effect, and the improvement of the material property of the thermal protection material for the long-range hypersonic vehicle.
[1] CHENG H, XUE H, HONG C, et al. Preparation, mechanical, thermal and ablative properties of lightweight needled carbon fiber felt/phenolic resin aerogel composite with a bird's nest structure[J]. Composites Science and Technology, 2017, 140:63-72.
[2] XU Y, HU X, YANG Y, et al. Dynamic simulation of insulation material ablation process in solid propellant rocket motor[J]. Journal of Aerospace Engineering, 2014, 28(5):1-21.
[3] SPRAVKA J J, JORRIS T R. Current hypersonic and space vehicle flight test instrumentation challenges[C]//AIAA Flight Testing Conference. Reston:AIAA, 2015.
[4] 甄华萍,蒋崇文. 高超声速技术验证飞行器HTV-2综述[J]. 飞航导弹, 2013(6):7-13. ZHEN H P, JIANG C W. Overview of hypersonic technology verification of air-craft HTV-2[J]. Aerodynamic Missile Journal, 2013(6):7-13(in Chinese).
[5] LEE I, LEE D M, OH I K. Supersonic flutter analysis of stiffened laminated plates subject to thermal load[J]. Journal of Sound and Vibration, 1999, 224(1):49-67.
[6] BROWN A M. Temperature-dependent modal test/analysis correlation of X-34 FASTRAC composite rocket nozzle[J]. Journal of Propulsion and Power, 2002, 18(2):284-288.
[7] CHAKRAVERTY S, PRADHAN K K. Free vibration of exponential functionally graded rectangular plates in thermal environment with general boundary conditions[J]. Aerospace Science and Technology, 2014, 36:132-156.
[8] FAN Y, WANG H. Nonlinear vibration of matrix cracked laminated beams containing carbon nanotube reinforced composite layers in thermal environments[J]. Composite Structures, 2015, 124:35-43.
[9] MALEKZADEH P, FIOUZ A R, SOBHROUYAN M. Three-dimensional free vibration of functionally graded truncated conical shells subjected to thermal environment[J]. International Journal of Pressure Vessels and Piping, 2012, 89:210-221.
[10] FU Y, CHEN Y, ZHONG J. Analysis of nonlinear dynamic response for delaminated fiber-metal laminated beam under unsteady temperature field[J]. Journal of Sound and Vibration, 2014, 333(22):5803-5816.
[11] NATALIE D S. High-temperature modal survey of a hot-structure control surface[C]//Proceedings of the 27th International Congress of the Aeronautical Sciences, 2010.
[12] JEON B H, KANG H W, LEE Y S. Free vibration characteristics of rectangular plate under rapid thermal loading[C]//The 9th International Congress on Thermal Stresses, 2011.
[13] ZHANG X, YU K, BAI Y, et al. Thermal vibration characteristics of fiber-reinforced mullite sandwich structure with ceramic foams core[J]. Composite Structures, 2015, 131:99-106.
[14] WU D, WANG Y, SHANG L, et al. Experimental and computational investigations of thermal modal parameters for a plate-structure under 1200℃ high temperature environment[J]. Measurement, 2016, 94:80-91.
[15] 吴大方, 赵寿根, 潘兵,等. 高速巡航导弹翼面结构热-振联合试验研究[J]. 航空学报, 2012, 33(9):1633-1642. WU D F, ZHAO S G, PAN B, et al. Research on thermal-vibration joint test for wing structure of high-speed cruise missile[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(9):1633-1642(in Chinese).
[16] 刘浩, 李晓东, 杨文岐,等. 高速飞行器翼面结构热振动试验的TARMA模型方法[J]. 航空学报, 2015, 36(7):2225-2235. LIU H, LI X D, YANG W Q, et al. Thermal vibration test on wing structure of high-speed flight vehicle using TARMA model method[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(7):2225-2235(in Chinese).
[17] YU K, YANG K, BAI Y. Experimental investigation on the time-varying modal parameters of a trapezoidal plate in temperature-varying environments by subspace tracking-based method[J]. Journal of Vibration and Control, 2014, 21(16):3305-3319.
[18] CHENG H, LI H, ZHANG W, et al. Effects of radiation heating on modal characteristics of panel structures[J]. Journal of Spacecraft and Rockets, 2015, 52(4):1228-1235.
[19] 谭光辉, 李秋彦, 邓俊. 热环境下结构固有振动特性试验及分析[J]. 航空学报, 2016, 37(S1):32-37. TAN G H, LI Q Y, DENG J. Test and analysis of natural modal characteristics of a wing model with thermal effect[J].Acta Aeronautics et Astronautics,2016, 37(S1):32-37(in Chinese).
[20] WADHAMS T, MACLEAN M, HOLDEN M, et al. A review of transition studies on full-scale flight vehicles at duplicated flight conditions in the LENS tunnels and comparisons with prediction methods and flight measurement[C]//48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.Reston:AIAA, 2010.
[21] KHARITONOV A M, ZVEGINTSEV V I, VASENEV L G, et al. Characteristics of the AT-303 hypersonic wind tunnel. Part 1. Velocity fields[J]. Thermophysics and Aeromechanics, 2006, 13(1):1-16.
[22] WATARI M, HIRABAYASHI N, KOYAMA T, et al. Flow qualities of JAXA hypersonic wind tunnel facilities[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference.Reston:AIAA,2006.
[23] 吴大方, 潘兵, 高镇同,等. 超高温、大热流、非线性气动热环境试验模拟及测试技术研究[J]. 实验力学, 2012, 27(3):255-271. WU D F, PAN B, GAO Z T, et al. On the experimental simulation of ultra-high temperature, high heat flux and nonlinear aerodynamic heating environment and thermo-mechanical testing technique[J]. Journal of Experimental Mechanics, 2012, 27(3):255-271(in Chinese).
[24] WU D, WANG Y, SHANG L, et al. Thermo-mechanical properties of C/SiC composite structure under extremely high temperature environment up to 1500℃[J]. Composites Part B:Engineering, 2016, 90:424-431.
[25] American Society for Metals. Metals handbook[M]. 10th ed. Metals Park:ASM International, 2004.
[26] 钟群鹏, 赵子华. 断口学[M]. 北京:高等教育出版社, 2006. ZHONG Q P, ZHAO Z H. Fracture surface[M]. Beijing:Higher Education Press, 2006(in Chinese).
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