Design method of variable sweepback rudder or wing for improving leading edge thermal environment

Abstract

The invention discloses a design method of a variable sweepback rudder or wing for improving a leading edge thermal environment. The design method comprises the steps of putting forward a requirementfor aerodynamic performance of a flight vehicle, determining the size or sweepback angle of an equal sweepback rudder or wing of the flight vehicle according to the specific requirement for the stability and the steerage in the requirement for aerodynamic performance, conducting variable sweepback design for the equal sweepback rudder or wing leading edge, adjusting the shape of the variable sweepback of the rudder or wing leading edge according to the requirement of the thermal environment, designing the variable sweepback rudder or wing leading edge, judging whether the variable sweepback meets the requirement or not, if not, repeating the third step, and if yes, regarding the current variable sweepback rudder or wing leading edge at this moment as the required variable sweepback rudderor wing. By means of the design method of the variable sweepback rudder or wing for improving the leading edge thermal environment, the leading edge thermal environment of the rudder or wing can be improved greatly, a certain effect of reducing resistance is achieved, and the influence on the stability and the steerage of the flight vehicle is very small. The design method is applicable to the flight vehicle with the rudder or wing, and is particularly applicable to engineering application of design of a hypersonic flight vehicle, and has very high practical value.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic layout design, and in particular relates to a design method of a variable-sweep rudder or wing for improving the thermal environment of the leading edge. Background technique [0002] At present, the rudder or wing generally adopts a fixed sweep angle to achieve the purpose of reducing drag and improving the thermal environment. Due to the limitations of various factors, the scheme of thin tip chord and thick root chord is often adopted, so that the leading edge is close to the tip chord. In general, the radius of the rounding of the leading edge of the rudder or wing is relatively small, especially the radius of the rounding near the tip chord is smaller, and it is easy to be hit by the shock wave to the leading edge, causing the leading edge of the rudder or wing to heat up. The environment is extremely harsh. [0003] With the advancement of aerospace technology, the maximum flight speed o...

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