Hypersonic bump compression profile inverse design method based on curved cone precursor

Abstract

The invention discloses a hypersonic bump compression profile inverse design method based on a curved cone precursor. The method comprises the following steps: 1) specifying a full-three-dimensional precursor shock wave curved surface according to the overall design requirement of a hypersonic aircraft; 2) dispersing the full-three-dimensional precursor shock wave curved surface into a series of precursor shock wave curves in a reference plane, and solving a corresponding flow field and a curved cone precursor compression surface by utilizing a bending shock wave theory; 3) taking an air inletlip as an input condition, and specifying a full-three-dimensional bump shock wave curved surface matched with the air inlet lip; wherein the intersecting line of the full-three-dimensional bump shock wave curved surface and the curved cone precursor compression surface obtained in the step 2) is the front edge profile line of the bump compression profile surface; and 4) dispersing the full-three-dimensional bump shock wave curved surface and the bump compression profile front edge molded line in a reference plane form, and solving by utilizing a bending shock wave theory to obtain a reference flow field and a bump compression profile line in the reference plane, and combining all the bump compression profile lines in the reference plane to obtain the hypersonic bulge compression profilebased on the curved cone precursor.

Description

technical field [0001] The invention relates to the technical field of hypersonic vehicle design in adjacent space, in particular to a reverse design method of a hypersonic bulge compression profile based on a curved cone precursor. Background technique [0002] The development of near-space vehicles has become one of the focuses of international competition for space technology. A large number of studies since the 1960s have fully demonstrated that the integrated design of the propulsion system and the airframe is the key to the realization of a hypersonic vehicle, and one of the cores of the integration of the propulsion system and the airframe is the integration of the aircraft precursor and the air intake. design. Hypersonic inlets can be mainly divided into binary inlets, axisymmetric outer turning inlets, side pressure inlets, and three-dimensional inner turning inlets according to the geometrical characteristics; while the hypersonic aircraft’s The precursor body ca...

AI Technical Summary

Problems solved by technology

Although the boundary layer suction device can effectively improve the low-speed start-up characteristics of the hypersonic inlet, its complex mechanism will greatly increase the weight of the high-speed aircraft and the difficulty of control

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