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Integrated design method of hypersonic slender body vehicle and three-dimensional inward turning inlet

A technology of hypersonic speed and design method, which is applied in the directions of aircraft parts, ground equipment, transportation and packaging, etc., to achieve the effect of high lift resistance characteristics and broaden the range of working Mach number

Active Publication Date: 2017-08-25
XIAMEN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It can be seen that the key problem restricting the overall performance of the hypersonic system at present is the lack of a design method suitable for the integration of the slender body vehicle and the three-dimensional inward turning inlet.

Method used

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  • Integrated design method of hypersonic slender body vehicle and three-dimensional inward turning inlet
  • Integrated design method of hypersonic slender body vehicle and three-dimensional inward turning inlet
  • Integrated design method of hypersonic slender body vehicle and three-dimensional inward turning inlet

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Embodiment Construction

[0026] like Figure 1~5 As shown, the integration scheme of the hypersonic slender body aircraft and the three-dimensional inward turning inlet includes the slender waverider aircraft precursor 23 and the three-dimensional inturning inlet, wherein the aspect ratio of the integrated device is 26, and the three-dimensional inner turning inlet The air inlet consists of a three-dimensional inner turning inlet compression surface 25, a three-dimensional inner turning inlet lip 26, a three-dimensional inner turning inlet shoulder 24, a three-dimensional inner turning inlet isolation section 21 and a three-dimensional inner turning inlet Transverse overflow port 28 is formed. And the three-dimensional inward turning inlet can realize internal wave riding. The front body 23 of the slender waverider aircraft and the three-dimensional inward turning inlet are connected and transitioned by means of the binary wedge guide band 20, and the three-dimensional inner turning inlet profile 25 ...

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Abstract

The invention discloses an integration design method for a hypersonic slender body air vehicle and a three-dimensional inward rotation air inlet channel, and relates to near space aerocrafts. The method comprises the following steps that a three-dimensional shock wave hook face is designated according to the design requirement; a series of basic flow fields are derived reversely according to the relation between the discrete shock wave curve and the curvature center; a slender waverider vehicle lower surface molded line and the outlet section of the three-dimensional inward rotation air inlet channel are designed, and streamline tracing in the counter flow direction is conducted in the basic flow fields; the two-dimensional projection shape of a lip of the three-dimensional inward rotation air inlet channel is designed, and a three-dimensional configuration of the lip of the three-dimensional inward rotation air inlet channel is obtained according to the shock wave relation; and the hypersonic slender body air vehicle is subjected to geometric construction based on a compression molded face. The performance of an outer waverider vehicle front body and the performance of the three-dimensional inward rotation air inlet channel are simultaneously considered by the generated slender body hypersonic air vehicle and the air inlet channel, the lift drag characteristic is high, full-flow incoming flow capture can be ensured, engine thrust is increased, outflow resistance is reduced, the operation Mach number range of the air inlet channel is widened, and natural transition of an inner waverider part and an outer waverider part is achieved.

Description

technical field [0001] The invention relates to a near-space vehicle, in particular to an integrated design method of a hypersonic slender body vehicle and a three-dimensional inward turning inlet. 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. Judging from the current research hotspots and trends, the design of the outer waverider aircraft and the research on the three-dimensional shr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00
CPCB64F5/00
Inventor 施崇广李怡庆尤延铖
Owner XIAMEN UNIV
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