Integrated design method of forward-swept interior waverider inlet based on conical precursor shock wave

Abstract

The invention relates to an integrated design method for a forward-sweep internal wave-multiplying inlet based on conical precursor shock waves, and relates to a hypersonic vehicle. The method comprises the following steps of: calculating a basic flow field of the conical precursor according to design conditions to obtain a three-dimensional conical shock wave surface of the conical precursor; determining an installation position of the three-dimensional internal contraction air inlet, determining a capture area of the three-dimensional internal contraction air inlet, and designing a two-dimensional projection shape of an inlet of the three-dimensional internal contraction air inlet according to the capture area and the installation position; according to the installation position, obtaining the inlet inflow condition of the three-dimensional internal contraction inlet, and designing the basic flow field of the three-dimensional internal contraction inlet. Carrying out streamline tracking in a reference flow field according to the two-dimensional projection shape to obtain a profile of the three-dimensional internal contraction air inlet; reversely installing the three-dimensionalinternal contraction air inlet at a certain installation position; cutting the profile of the three-dimensional internal contraction air inlet by using a three-dimensional conical shock wave curved surface of the conical precursor, and removing the part which extends out of the head conical shock wave surface so as to obtain the forward-sweep internal wave-multiplying air inlet which can be matched with the integrated design of the conical precursor.

Description

technical field [0001] The invention relates to a hypersonic aircraft, in particular to an integrated design method for a forward-swept inner waverider inlet based on a conical precursor shock wave. 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. 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 integration of the aircraft and the air intake. [0003] For hypersonic vehicles, scholars such as Peter F.Covell, Richard M.Wood, and Steven X.Bauer ([1] [0004] AIAA.Configuration trade ...

AI Technical Summary

Problems solved by technology

However, if the conical precursor is directly coupled with the three-dimensional constricted inlet, there is a mismatch between the three-dimensional external compression flow field of the conical precursor and the three-dimensional internal contraction flow field of the inlet.

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