Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method

Abstract

The invention discloses an aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method and relates to an aircraft. The method is characterized in that the method is based on an axisymmetric internal contraction basic flow field; the axisymmetric internal contraction basic flow field only comprises an axisymmetric internal contraction rotary wall surface which is formed by connecting two sections of compression molded lines with different compression angles by the internal contraction basic flow field; after the shape of a separation section outlet is specified, basic flow field flow line tracing in different radial positions is performed on each circumferential plane of an inlet, so as to ensure that the internal contraction basic flow field meets designs of an aircraft fore-body and the hypersonic inlet, and an internal waverider-derived hypersonic inlet integrated device with the fore-body is obtained. The method overcomes the defect that inlet overflow of the traditional inlet is serious due to the action of the fore-body; incoming flow captured by the inlet in full flow is realized; the motor thrust is increased, the overflow resistance is reduced; the working range of the inlet is improved; and the low mach number performance of the inlet is improved.

Description

technical field [0001] The invention relates to an aircraft, in particular to an integrated design method for an aircraft precursor and an internal waveriding hypersonic inlet. Background technique [0002] The research of near-space vehicles is one of the focuses of the current international competition for space technology, and the research of scramjet has become the top priority of the development of near-space vehicles because of its important strategic significance. World powers represented by the United States, Russia, Germany, France, and Australia are vigorously promoting their respective scramjet development programs ([1] Joseph, M.H, James S.M.Richard C.M., The X-51A Scramjet Engine Flight Demonstration Program[1] R],15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference,2008; [2]Steven,H.W.,Col,J.S.,Dale S.R.et.al The DARPA / AF Falcon Program:The Hypersonic Technology Vehicle#2(HCV-2 ) Flight Demonstration Phase[R], 15th AIAA Inter...

AI Technical Summary

Problems solved by technology

The traditional design method is to design the aircraft precursor first, and then design the corresponding air inlets to match the shape of the already designed aircraft precursors. The disadvantage of this design method is that the aircraft precursors and air inlets are designed discretely, and then Mutual coupling leads to mutual interference between the designed precursor and the inlet, and the incident shock wave generated by the aircraft precursor will have a negative impact on the incident shock wave of the inlet, resulting in a decrease in the capture capacity of the inlet and overflow Increased drag, which reduces the ability of the propulsion system to work

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