Papers by Keyword: Aerodynamic Heating

Abstract: In order to accurately simulate the transient aerodynamic heating conditions experienced by aircraft when flying at high speeds, rapid and highly precise non-linear dynamic control of the heating process in aerodynamic simulation experiments must be conducted using a transient heat flux control system. This process involves carrying out ‘thermoelectric potential - temperature (E-T)’ conversion of sensors. Here a fast and high-precision ‘E-T’ sensor conversion method for the transient aerodynamic heating control systems of high-speed aircraft is proposed. The developed method has the advantages of easy calculation, rapid conversion speed and high calibration precision, and can thus be employed for fast non-linear dynamic control of rapidly-changing temperature fields in the aerodynamic heating process of high-speed aircraft.

Abstract: A fast and high-precision ‘thermoelectric potential - temperature (E-T)’ sensor conversion method for the transient aerodynamic heating control systems of high-speed aircraft is proposed. The developed method has the advantages of easy calculation, rapid conversion speed and high calibration precision, and can thus be employed for fast non-linear dynamic control of rapidly-changing temperature fields in the aerodynamic heating process of high-speed aircraft.

Abstract: Four turbulent models are introduced. The hypersonic aerodynamic heating calculation results by Shear Stress Transport (SST) turbulent model of different grid scale shows that near wall y+ spacing approximate to one third of the upper limit prescribed by turbulent model. Then, the comparison of the hypersonic aerodynamic heating calculation results by different turbulent model and the test data shows that SST turbulent model can give an enough accurate result.

Abstract: Numerical schemes play an important role on the calculation of aerodynamic heating in hypersonic flows. An appropriate scheme can effectively distinguish shock, and reduce numerical dissipation to improve numerical resolution near the wall. In this paper the second order TVD (total variation diminishing) scheme was improved to automatically adjust the numerical viscosity, which can appease the above requirements. In this paper two numerical experiments indicated that the numerical method was effective.

Abstract: The leading structure of circumferential embedded high temperature heat-pipes in sidewall is considered as thermal protection system to prevent capsule type re-entry vehicle from the serious aerodynamic heating. It can lighten thermal load of windward and make good use of the endothermic capability of low temperature leeward. By means of fluid structure interaction method, we calculate the temperature distribution of capsule under given conditions and the maximum sidewall temperature decreases by 8.45%. The transfer of heat from windward to leeward is achieved, the windward of the thermal load is weakened and the ability of thermal protection is strengthened. The influence of structure parameters of heat-pipe-cooled capsule, flying attributes and materials attributes of coating to thermal protection effect are discussed in this paper to provide some references for the selection of leading structure and materials.

Abstract: Based on the theory and semi-empirical formulas, the surface heating flux of hypersonic flying vehicle under aerodynamic heating is calculated by using reference enthalpy method. On this basis, the thermal response of structure made of ultrahigh temperature ceramics(UHTCs) is simulated by using finite-element method. The results show that thermal stress shock is able to cause material to damage in a very short time

Abstract: Due to the missile in flight, the airflow temperature around the missile body shall rise and the surface of the missile body shall also be heated. It introduces the engineering calculation method of thick wall aerodynamic heating of the missile, including air flow parameters, heat exchange coefficient and the head surface temperature calculation formula of the missile body.

Abstract: By the uses of finite element method and finite volume method, we calculated the solid domain and fluid domain of windward leading edge which is flying under one condition. And the paper proved that heat pipes which covered on the leading edge have effect on thermal protection. The maximum temperature of the head decreased 12.2%. And the minimum temperature of after-body increased 8.85%. Achieving the transfer of heat from head to after-body, the front head of the thermal load was weakened and the ability of leading edge thermal protection was strengthen. The effect of the thickness of heat pipe, black level of covering materials and equivalent thermal conductivity of heat pipes on the wall temperature were discussed for the selection of thermal protection materials of windward leading edge to provide a frame of reference.

Abstract: Ceramic insulating tile is the main insulation material used on space shuttle thermal protection system at present, but this material has low strength, high brittleness and easy to be damaged. So the study of thermodynamic response of damaged rigid ceramic insulating tiles is very important. In this paper the temperature field and thermal stress field of the damaged ceramic insulating tiles under aerodynamic heating are simulated by ABAQUS code. The analyzed results indicate that the sharp degree of the damage shape has minor influence on the temperature field, but is more significant for the maximum thermal stress. Meanwhile the larger loading is, the bigger influence is.

Abstract: Based on theory and semi-empirical formula, this paper uses the method of reference enthalpy to calculate the surface aerodynamic heating flux of waverider with sharp leading edge. On this basis, applying ultra high temperature ceramic materials ZrB₂–SiC, thermal response of the sharp leading edge is studied. The results show that the aerodynamic heating can make thermal stress intensity extremum inside the structure exceed the ultimate strength of material quickly. Though the temperature inside the structure is much lower than material heat-resistant temperature extremes, thermal stress shock is able to cause material to damage in a very short time.