Inverse Design Method of Full 3D Inverted Inlet Based on Bending Shock Wave Theory

Abstract

Inverse design method of full 3D inward turning inlet based on bending shock wave theory 1) specify full 3D incident shock wave in full 3D reference flow field according to design requirements; 2) discretize full 3D incident shock wave into a series of reference planes, according to For the full three-dimensional incident shock angle, shock curvature, and post-wave parameters, use the bending shock theory to solve the corresponding full three-dimensional inner contraction basic flow field; 3) design the full three-dimensional inner turning inlet outlet section, and Perform streamline tracing in the basic flow field of the full three-dimensional internal contraction to obtain the hypersonic full three-dimensional internal rotation inlet compression profile; the shape of the section is elliptical or rectangular; 4) use the full three-dimensional internal rotation Based on the compression profile of the inlet port, the geometric structure of the hypersonic full three-dimensional inward turning inlet is carried out: according to the requirements of the outlet area, the shoulder profile is straightened or stretched to obtain the full three-dimensional inner turning inlet isolation section, and the A full three-dimensional inward turning inlet based on the bending shock wave theory in the design flight state.

Description

technical field [0001] The invention relates to the field of adjacent space hypersonic inlets, in particular to a full three-dimensional inward turning inlet inverse design method based on the bending shock wave theory. Background technique [0002] The development of near-space vehicles involves national security and peaceful use of space, and is one of the focuses of the current international competition for space technology. World powers represented by the United States and Russia are vigorously promoting their own hypersonic flight development programs (Joseph, M.H, James S.M.Richard C.M., The X-51A Scramjet Engine Flight Demonstration Program, 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008). The air intake is a major component in the propulsion system of a hypersonic vehicle. It is located at the front of the aircraft and is directly connected to the front of the hypersonic aircraft, compressing the incoming flow and prov...

AI Technical Summary

Problems solved by technology

At the same time, researchers generally use the traditional characteristic line method to carry out the reverse design of the reference flow field, which is not only complicated in programming, but also poor in stability, which limits the selection range of the basic flow field, thereby reducing the geometric structure range of the inlet.

It can be seen that one of the current problems restricting the performance of hypersonic inlets is the lack of a full three-dimensional inward turning inlet inverse design method based on the bending shock wave theory

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