Thermal Flutter Analysis Of Panel Under The Aerodynamic Heating Environment

The skin panels of aircraft is a special form of two-dimensional system, its structure dynamicsfeature can be simulated by plate or shell. In the process of design hypersonic vehicles, due to theaerodynamic heat effect is very intense, so panel flutter is a serious problem of aeroelastic. Thisphenomenon always has harmful influence on the flight performance and impacts on the life of thestructure, and even endanger the flight safety. In this paper, on the basis of the thermal modal analysisin the structure, conducting thermal flutter calculations, include the following aspects:First, create and verify the thermal modal analysis methods under complex temperature field andunder different boundary conditions. Establishing the panel modal under different boundaryconditions, conducting model dynamic finite element analysis after loading the temperature field,five-order mode are reserved, obtains the trend of temperature on the natural frequency.Second, establishing wing flutter equation and general equation of panel flutter based on thepiston theory, and establishing panel flutter equation under a zero angle and non zero air flow.Third, completes the technical details during the thermal panel flutter calculation, includingsummary the p k method of flutter calculation; discusses the mode tracking problem in the fluttercalculation; establishes a flutter of sub-quadratic function calculation method; discussed thesupersonic flutter calculations of numerical integration problem, given the inherent vibration mode atthe integration point values and the slope formula; shows the calculation method of flutter patterns.Last, complete15swept wing and simply supported plate supersonic flutter calculations, andcompare with flutter results given by foreign literature, at the same tine included temperature on theelastic modulus and thermal expansion coefficient of factors, obtains the trend of temperature andflow angle on the flutter velocity.