Two-stage compression inner waverider air inlet channel inverse design method based on bending shock wave theory

Abstract

The invention discloses a two-stage compression inner waverider air inlet channel inverse design method based on a bending shock wave theory, and relates to a near space hypersonic air inlet channel. A two-stage compression reference flow field comprising two three-dimensional incident shock waves and one three-dimensional reflection shock wave is specified according to design requirements, and the three-dimensional incident shock waves and the three-dimensional reflection shock waves are designed in a bending axial symmetry shape. The first three-dimensional bending incident shock wave is dispersed into a series of reference planes, corresponding two-stage compression reference flow field aerodynamic parameters are solved in each two-dimensional plane according to incident shock wave angle, shock wave curvature and reflected wave rear flow direction angle distribution, and all the planes are superposed to obtain a three-dimensional internal contraction reference flow field. The inlet section of the two-stage compression inner waverider air inlet channel is designed, and streamline tracking is carried out in the reference flow field. Geometric construction is carried out on the hypersonic two-stage compression inner waverider air inlet channel on the basis of the compression molded surface; and according to the outlet area requirement, the shoulder molded line is straightened or expanded and stretched to obtain the two-stage compression inner waverider air inlet channel isolation section. The working performance of the air inlet channel is improved.

Description

technical field [0001] The invention relates to an adjacent space hypersonic inlet, in particular to a reverse design method for a two-stage compression inner waverider inlet based on the bending shock wave theory. Background technique [0002] Since the 21st century, hypersonic vehicles have gradually become the forefront of the global aerospace industry. As the core structure of the air inlet, it is necessary to achieve efficient compression while capturing enough air to ensure that the entire propulsion system generates enough thrust to meet the working range of a wide Mach number. At present, the more mature ones are binary type, axisymmetric type and lateral pressure type. In the 1940s, scholars at home and abroad proposed three-dimensional internally constricted inlets with high compression efficiency, low external resistance, and a wide Mach number operating range, and discussed their design methods, flow characteristics, operating characteristics, and engineering de...

AI Technical Summary

Problems solved by technology

The reference flow field directly determines the aerodynamic performance of the inlet, but the current flow field and design methods still have inherent defects: the shock wave compression ratio is small, and the flow field loss is large; the wall profile or the aerodynamic parameters along the way need to be given during design , the wave system distribution cannot be directly controlled, which greatly affects the design flexibility of the inlet

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 has poor stability, which limits the selection range of the reference 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 two-stage compression internal waverider inlet reverse design based on the bending shock wave theory that can achieve controllable shock wave profile and outlet parameter distribution. method

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