Integrated design method and system of hypersonic flight vehicle body and inward rotating type air inlet duct

Abstract

The invention discloses an integrated design method, configuration and system of a hypersonic flight vehicle. According to the design method, an inward rotating type axial symmetry standard flow fieldand an outer compressing standard flow field are firstly generated, an inward rotating type shock wave and an outer compressing shock wave are generated under the design condition, and the two shockwaves intersect to form a shock wave intersecting line; and then a bottom projective plane perpendicular to the rotation axis of the standard flow field is arranged, a projection line of the shock wave intersecting line is generated on the projective plane, a projection line of a wave rider leading edge line is designed, and then a wave riding face, a free flow face, an inward rotating type air inlet duct and an air inlet duct outer fairing are generated. The internal flow and external flow integrated configuration of the hypersonic flight vehicle is formed by the generated inward rotating type air inlet duct, air inlet duct outer fairing, wave riding face and free flow face. According to the designed internal flow and external flow integrated configuration of the hypersonic flight vehicle, the excellent performance of the inward rotating type air inlet duct and the high lift-drag ratio property of a wave rider are basically kept, and complex wave system interference between an enginebody and the air inlet duct is weakened from the perspective of flow field coupling.

Description

technical field [0001] The invention relates to the technical field of aerodynamic shape design of a hypersonic vehicle, in particular to an integrated design method, configuration and system for internal and external flows of a hypersonic vehicle. Background technique [0002] Good airframe / propulsion system integration has become a key technology for hypersonic flight, and the integration of aircraft airframe and air intake as its core element has attracted extensive attention from scholars at home and abroad. The high degree of integration between the air intake and the airframe has an important impact on the aerodynamic characteristics of the aircraft and the performance of the air intake. [0003] The current layout of the airframe and the inlet generally brings about complex wave system interference between the airframe and the inlet, which will lead to a decrease in the performance of the inlet, such as compression efficiency and capture performance. Contents of the...

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Problems solved by technology

[0004] The present invention provides an integrated design method, configuration and system for the internal and external flow of a hypersonic aircraft, which is used to overcome the complex wave system interference between the body and the air inlet caused by the layout of the airframe and the air inlet in the prior art, etc. Defects, weaken the wave system interference between the airframe and the air inlet, so as to ensure that the performance of the air inlet is less affected by the airframe, and the performance of the airframe is less affected by the air inlet

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