Abstract
Aerothermoelasticity plays a vital role in the design and optimisation of hypersonic aircraft. Furthermore, the transient and nonlinear effects of the harsh thermal and aerodynamic environment a lifting surface is in cannot be ignored. This article investigates the effects of transient temperatures on the flutter behavior of a three-dimensional wing with a control surface and compares results for transient and steady-state temperature distributions. The time-varying temperature distribution is applied through the unsteady heat conduction equation coupled to nonlinear aerodynamics calculated using 3rd order piston theory. The effect of a transient temperature distribution on the flutter velocity is investigated and the results are compared with a steady-state heat distribution. The steady-state condition proves to over-compensate the effects of heat on the flutter response, whereas the transient case displays the effects of a constantly changing heat load by varying the response as time progresses.
Highlights
Hypersonic aeroelasticity and aerothermoelasticity have been active areas of research since the late 1950s [1,2]
This work has shown that the dynamic behaviour of the structure under the harsh thermal environment must be investigated for hypersonic aircraft to become a reality
This paper extends the previous work by developing a novel method for coupling the nonlinear aerodynamics, thermodynamics and structural dynamics of a simplified wing
Summary
Hypersonic aeroelasticity and aerothermoelasticity have been active areas of research since the late 1950s [1,2]. Whereas the early research was instrumental in providing the basis for the aerothermoelastic design of the X-15 and the space shuttle [3,4,5], the current focus is on the development of hypersonic technologies for next-generation reusable launch vehicles and hypersonic cruise vehicles [6,7,8]. This work has shown that the dynamic behaviour of the structure under the harsh thermal environment must be investigated for hypersonic aircraft to become a reality. The early aerothermoelastic work focused on the effects of thermal stresses on the static aeroelastic stability and dynamic response of thin metal wings [1,17,18]. Ericsson et al [19] studied the effects of different temperature profiles on the aerothermoelastic characteristics of missiles, whereas
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