Inverse design method for complex curved shock-onset body based on three-dimensional curved stream surface method

By designing complex curved surface shock wave riders using the three-dimensional curved flow surface method, the problem of performance degradation under the influence of lateral flow was solved, achieving efficient and stable wave rider design and improving aircraft performance.

CN118254959BActive Publication Date: 2026-06-26XIAMEN UNIV
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Patent Information

Application Number
CN202410279789.2
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2024-03-12
Publication Date
2026-06-26
Estimated Expiration
2044-03-12

AI Technical Summary

Technical Problem

Existing technologies lack inverse design methods for complex curved surface shock wave riders based on the three-dimensional curved flow surface method, which leads to reduced propulsion system performance under the influence of transverse flow. Traditional methods are computationally complex and have poor stability.

Method used

A complex surface shock wave rider inverse design method based on the three-dimensional curved flow surface method is adopted. The complex surface shock wave is specified by the parametric surface function, the transverse vortex generated by the transverse flow is considered, and the flow field parameters are solved by Euler equations in the three-dimensional streamline coordinate system to construct a high-performance wave rider.

Benefits of technology

It improves the aerodynamic performance of the waverider, enhances the lift of the aircraft and reduces drag, broadens the design range, and improves calculation accuracy and stability.

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Abstract

The application relates to a complex curved surface shock wave body counter-design method based on a three-dimensional curved flow surface method, and relates to a hypersonic wave body. The complex curved surface shock wave body is provided with a complex curved surface shock wave body lower surface compression profile, a complex curved surface shock wave body upper surface profile and a complex curved surface shock wave body leading edge profile; the complex curved surface shock wave body lower surface profile and the complex curved surface shock wave body upper surface are connected by the complex curved surface shock wave body leading edge profile. A complex curved surface three-dimensional outflow shock wave is specified, and a wave body capture profile is designed; the complex curved surface shock wave is dispersed into a series of initial flow surfaces; shock wave angles, shock wave curvatures and wave rear parameters are solved; a complex shock wave curved surface wave rear flow field is solved, and a compression profile is determined; a wave body upper surface geometric shape is constructed according to design requirements; and the upper and lower surfaces are connected to form a complete complex curved surface shock wave body geometric shape. The method has higher calculation efficiency and higher precision, and provides a wider performance improvement space for aircraft design through free shock wave selection.
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