Wall-pressure-controllable internal and external wave rider integrated design method

Abstract

The invention relates to a near space hypersonic flight vehicle, in particular to a wall-pressure-controllable internal and external wave rider integrated design method. The projection and needed pressure distribution of a front edge capture molded line on a design section are specified according to design requirements. The projection of the front edge capture molded line on a top view is designed, and according to given pressure distribution, a reverse characteristic line method is utilized for solving a corresponding compression molded line. According to the compression molded line and the included angle between an osculating plane and a symmetry plane, an internal and external wave rider integrated compression molded surface is obtained in a corresponding axial symmetry external compressive flow field or an axial symmetry internal contraction flow field through coordinate transformation. The projection of a three-dimensional internal rotating air inlet channel outlet section and a three-dimensional internal rotating air inlet channel lip on the design section is designed, and a three-dimensional structure of the three-dimensional internal rotating air inlet channel lip is obtained according to the shock wave relation. The compression molded surface is adopted as a foundation for carrying out geometric construction on internal and external wave rider integrated aircrafts.

Description

technical field [0001] The invention relates to a hypersonic vehicle in adjacent space, in particular to an integrated design method for internal and external waveriders with controllable wall surface pressure. 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 (Joseph, M.H, James S.M.Richard C.M., The X-51A Scramjet Engine Flight Demonstration Program, 15 th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2008). 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 s...

AI Technical Summary

Problems solved by technology

It can be seen that one of the current problems restricting the overall performance of hypersonic systems is the lack of an integrated design method for internal and external waveriders with controllable wall pressure

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