Abstract
The objective of this paper is to accurately describe the influence of structural parameter uncertainties on the thermal efficiency of an aircraft wing anti-icing cavity. To do this, a new method of parameter sensitivity evaluation is proposed according to the weighted stochastic response surface method. First, the concept of fitting the explicit performance function of the anti-icing cavity structure using the weighted stochastic response surface method is presented. A structural parameter sensitivity analysis based on thermal efficiency is then conducted considering the uncertainties of the position of the flute tube, the height of the double-skin channel, and the diameter and angle of the jet holes. The results indicate that the height of the double-skin channel and the diameter of the jet holes are the main factors influencing the functional reliability of the anti-icing cavity.
Highlights
Ice accretion on airfoils can cause significant damage to an aircraft by increasing its weight and by deteriorating its aerodynamic capabilities and decreasing the available lift force, affecting its stability and safe operation [1,2,3,4]
As the core part of an airfoil thermal anti-icing system, the design quality of the anti-icing cavity has a significant impact on the deicing and anti-icing effect provided to the aircraft [5, 6]
The stochastic response surface method was originally proposed by Isukapalli et al [23, 24] as an evolution of the classical response surface method during their study on the uncertainty of environmental and economic systems
Summary
Ice accretion on airfoils can cause significant damage to an aircraft by increasing its weight and by deteriorating its aerodynamic capabilities and decreasing the available lift force, affecting its stability and safe operation [1,2,3,4]. With the development of large aircraft projects in China, the study of airfoil thermal anti-icing systems has attracted increasing attention. As the core part of an airfoil thermal anti-icing system, the design quality of the anti-icing cavity has a significant impact on the deicing and anti-icing effect provided to the aircraft [5, 6]. Parameters such as the jet hole angle, jet hole diameter, and distance between the jet holes and aircraft skin anti-icing area should be adjusted so that the air supply system can effectively provide sufficient hot air for deicing [7,8,9,10]. Traditional studies on anti-icing systems have mainly focused on the simulation of the flow characteristics inside the cavity and the heat exchange between the cavity and the aircraft skin under the condition that the geometric structure of the anti-icing cavity is well known
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