All-three-dimensional two-stage compression double waverider integrated design method based on bending shock wave theory

Abstract

The invention discloses a full-three-dimensional two-stage compression double waverider integrated design method based on a bending shock wave theory. A full-three-dimensional shock wave curve intersected by two required full-three-dimensional bending shock waves and one required full-three-dimensional internal flow reflection shock wave is specified in a design section and discretized; solving corresponding flow field parameters by using a bending shock wave theory in combination with a multi-stage compression theory; solving corresponding flow field parameters by combining a bending shock wave theory with a multi-stage compression theory, and superposing all the internal flow pseudo flow planes to obtain an internal flow part of the full-three-dimensional two-stage compression double waverider reference flow field; specifying a projection molded line of a front edge capture molded line of the full-three-dimensional two-stage compression double waverider integrated configuration in a design section, and performing streamline tracking in a reference flow field; and carrying out geometric construction on the hypersonic full-three-dimensional two-stage compression double waverider integrated configuration on the basis of the compression molded surface. The high lift-drag ratio of the three-dimensional external flow waverider and the full-flow capture of the three-dimensional internal waverider air inlet channel are both considered, and the aerodynamic performance of the double waverider is greatly improved through two-stage compression.

Description

technical field [0001] The invention relates to the integration of near space hypersonic aircraft, in particular to a full three-dimensional two-stage compression double-waverider integration design method based on the bending shock wave theory. Background technique [0002] At present, the near space hypersonic vehicle is the hot research content of the aerospace powers in the world, and it is also an important direction of the future development of the aircraft. Waveriders have become the first choice for aerodynamic layout design of hypersonic vehicles due to their high lift-to-drag ratio. However, the high aerodynamic performance of the waverider alone cannot guarantee the success of hypersonic flight. Lewis pointed out that although the perfect waverider theory can better design an aircraft with a lift-to-drag ratio of 7 to 8, the lift-drag ratio of a hypersonic aircraft currently matched with an upper-air-breathing engine is only the largest after adding various lift ...

AI Technical Summary

Problems solved by technology

However, so far, even the dual waveriders are still designed with an axisymmetric reference flow field, and the resulting three-dimensional dual waveriders only have flow in the flow direction, and the lateral flow plays a vital role in improving the performance of the aircraft

In addition, traditional double waveriders are designed based on the reference flow field of single-stage compression. In the design state, the compression performance of double waveriders is limited, which restricts its wide application in engineering practice. Therefore, it is hoped that through multi-stage compression way to improve the comprehensive performance of dual waveriders

At the same time, researchers generally use the traditional characteristic line method to carry out the inverse design of the reference flow field. The design process is slow and not stable enough, which limits the design scope of the double waverider.

It can be seen that one of the current problems restricting the integrated performance of hypersonic vehicles is the lack of a full three-dimensional two-stage compression dual-wave rider integrated design method based on the bending shock wave theory.

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