Multi-constraint refined aerodynamic optimization design method for tailless flying wing layout

Abstract

The invention belongs to the technical field of aerospace, and particularly relates to a multi-constraint refined aerodynamic optimization design method for a tailless flying wing layout. According to the multi-constraint refined aerodynamic optimization design method for the tailless flying wing layout, design objective optimization under various design constraints is realized by adopting a unified objective function, and accurate aerodynamic performance is obtained by adopting a flow field solving method based on an N-S equation; the gradient information of multiple design variables is quickly and efficiently obtained by adopting a gradient solving method based on an adjoint theory, unification of multiple design constraints, refined design and efficient optimization design of the tailless layout is effectively realized, detailed design requirements of an aircraft scheme in engineering are met, and an optimization design result can be quickly obtained.

Description

technical field [0001] The application belongs to the field of aerospace technology, and in particular relates to a multi-constraint refined aerodynamic optimization design method for a tailless flying wing layout. Background technique [0002] The tailless flying wing layout has been widely used in military aircraft due to its good aerodynamic efficiency and stealth characteristics. At the same time, the flying wing layout has typical problems such as low control efficiency and trim loss. Generally speaking, the aircraft is required to have a high lift-to-drag ratio in the cruising state, and at the same time have a small nose-down moment, so as not to cause a large trim loss, and these two requirements are often contradictory, especially in the flying wing layout The performance is more prominent, that is, increasing the cruise lift-to-drag ratio will bring a larger nose-down moment, so that the lift-to-drag ratio of the final trim of the whole aircraft will not increase. ...

AI Technical Summary

Problems solved by technology

[0003] At present, the domestic design of flying wing layout mainly adopts the "trial and error method" based on manual experience. This method can meet the requirements in terms of conceptual design and preliminary design, but with the deepening of the development stage, there are more and more design constraints in various disciplines. , the space for aerodynamic shape optimization is further reduced, and it is difficult to find a reasonable optimization result based on manual experience. At the same time, the aerodynamic shape is required to be frozen quickly, which further compresses the aerodynamic shape design cycle. Difficulties facing designers

The optimization methods based on CFD are divided into stochastic methods and gradient methods. The stochastic methods track the information related to the objective function value, have good globality, and do not require the advantages of continuous distribution of design variables and the existence of derivatives, such as genetic algorithms and proxy model methods. etc., but its disadvantage is that in the refined aerodynamic shape design of multiple design variables, the optimization efficiency is low and the accuracy is reduced; while the gradient method is the most widely used, and the optimization method based on the adjoint theory has no relationship with the design variable digital model. , which has good applicability in the design stage of aircraft refinement

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