Hypersonic aerocraft and air inlet internal and external waverider integrated design method

Abstract

The invention discloses a hypersonic aerocraft and air inlet internal and external waverider integrated design method, and relates to a near space aerocraft. An aerodynamics characteristic is firstly appointed, and then a design scheme meeting the characteristic is inferred backwards; a three-dimensional shock wave curved surface in a complex shape is appointed, the change rule of the transverse curvature center is obtained, and a series of basic flow fields meeting the needs of the waverider design are inferred backwards according to the change rule; flow lines of different curvature centers and different radial positions are traced in every basic flow field in the circumferential direction; a waverider device capable of producing the appointed complex three-dimensional shock wave curved surface is obtained finally, namely the integrated design scheme is obtained. The advantages of a waveriders and an internal waverider air inlet are kept, the integrated design of the two high-performance devices is achieved, the waverider model with high lift-drag ratio and the scheme of the air inlet with full-flow capture can be obtained at the same time, and accordingly the overall performance of the aerocraft is improved.

Description

technical field [0001] The invention relates to a near-space vehicle, in particular to an integrated design method for a hypersonic vehicle and an inner and outer waverider of an air inlet. Background technique [0002] The development of near-space vehicles involves national security and the peaceful use of space, and is one of the focuses of the current international competition for space technology, and the research on near-space hypersonic long-range maneuvering vehicles has become the focus of the development of near-space vehicles because of its important strategic significance heavy. World powers represented by the United States and Russia are vigorously promoting their own hypersonic flight development programs. A large number of studies since the 1960s have fully demonstrated that the integrated design of the aircraft and propulsion system is the key to achieving hypersonic flight, and the core of the integration of the airframe and the propulsion system is the int...

AI Technical Summary

Problems solved by technology

Mark Lewis, chief scientist of the U.S. Air Force's hypersonic program, pointed out in the literature (M.Lewis, A Hypersonic Propulsion Airframe Integration Overview, 39th AIAA and ASME and SAE and ASEE Joint Propulsion Conference and Exhibit, 2003), although a sound waveriding theory can help We can easily design an aircraft with a lift-to-drag ratio of 7-8, but the maximum lift-to-drag ratio of existing hypersonic aircraft with engines is only 3.8

It can be seen that the key problem restricting the overall performance of the hypersonic system is the lack of an efficient integrated design method for the aircraft and the inlet.

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