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| Single degree of freedom dynamic theoretical model for a thermal protection system |
| HUANG Jie1，YAO Weixing1,2，SHAN Xianyang3 |
1.Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China；
2.State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China；
3.System Design Institute of Hubei Aerospace Technology Academy,Wuhan 430040，China |
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Abstract A single degree of freedom random dynamic theoretical model for the thermal protection system (TPS) is proposed to study the acceleration response of tile and dynamic strength of the strain isolation pad (SIP). The linear and nonlinear stiffness of SIP is considered. The solutions of linear theoretical model are derived, and the iterative solving procedure of nonlinear theoretical model is studied. The rationality of linear theoretical model is verified by comparing linear theoretical solutions with the results of finite element analysis. The theoretical solutions of nonlinear and linear theoretical models are compared. The dynamic responses and the equivalent linear stiffness coefficient are related to the nonlinear stiffness of SIP and the types of excitations. Finally, the influence laws of the equivalent linear stiffness coefficient and the responses on the external loads are studied. The equivalent linear stiffness and the responses are increases with increasing of the external loads. The investigations in this paper provide a theoretical basis for the researches of the acceleration response of tile, dynamic strength of the SIP and the dynamic integrity of the TPS.
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Received: 25 July 2017
Published: 15 January 2019
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[1] Yang J, Liu M. A wall grid scale criterion for hypersonic aerodynamic heating calculation [J]. Acta Astronautica, 2017, 136: 137-143.
[2] 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.
[3] 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.
[4] Yang Q, Meng S, Xie W, et al. Effective mitigation of the thermal short and expansion mismatch effects of an integrated thermal protection system through topology optimization [J]. Composites Part B Engineering, 2017, 118: 149-157.
[5] Kumar S, Mahulikar S P. Design of thermal protection system for reusable hypersonic vehicle using inverse approach [J]. Journal of Spacecraft & Rockets, 2017, 54(2): 1-11.
[6] 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.
[7] Muraca R J, Coe C F, Tulinius J R. Shuttle tile environments and loads [C]. Structural Dynamics and Materials Conference, 1982, 631.
[8] Miserentino R, Pinsonand L D, Leadbetter S A. Some space shuttle tile/strain-isolator-pad sinusoidal vibration tests [R]. NASA TM-81853, 1980.
[9] Cooper P. A, Miserentino R, Sawyer J W, et al. Effect of simulated mission loads on orbiter thermal protection system undensified tiles [J]. Journal of Spacecraft and Rockets, 1984, 21(5): 441-447.
[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] Edighoffer H. Parametric analytical studies for the nonlinear dynamic response of the tile/pad space shuttle thermal protection system [R]. NAS1-16121, 1981.
[12] Spanos P D. Stochastic linearization in structural dynamics [J]. Applied Mechanics Reviews, 1981, 34(1): 1-8.
[13] Elson J M, Bennett J M. Calculation of the power spectral density from surface profile data [J]. Applied Optics, 1995, 34(1): 201-208. |
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