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Design method of hypersonic embedded waverider

A design method and hypersonic technology, applied in supersonic aircraft, motor vehicles, aircraft, etc., can solve problems such as difficulty in taking into account high volume ratio and high lift-to-drag ratio

Active Publication Date: 2021-05-11
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

From the previous analysis, it can be known that the traditional waverider design method adopts the concept of span-wise integration design, which has inherent contradictions, and it is difficult to balance high volume ratio and high lift-to-drag ratio

Method used

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  • Design method of hypersonic embedded waverider
  • Design method of hypersonic embedded waverider
  • Design method of hypersonic embedded waverider

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] With the current Mach number 5.0 and the angle of attack 4° as the design state, the aerodynamic layout design of the embedded waverider aircraft is carried out.

[0038] First, the shape of the fuselage needs to be given as the basic body. Since the fuselage mainly considers the characteristics of high volume ratio, a typical slender body shape is adopted as the fuselage shape. The cross-sectional shape of the fuselage adopts a closed hypercircular curve, and the side of the fuselage head adopts a tangent oval line. The designed fuselage shape is as follows: figure 1 shown. Then the leading edge line of the embedded waverider is given. The leading edge line is a single straight line, which is located in the horizontal plane at half the height of the fuselage. The sweep angle of the leading edge line is 60°, the distance from the most forward point to the vertex of the fuselage head is 4.3D, and D is the diameter of the fuselage. Only considering the case where the em...

Embodiment 2

[0043] Since the current Mach number is 5.0 and the angle of attack is 4° as the design state, consider the situation that the wing span is larger than the shock wave range of the fuselage head, that is, part of the wing is located in the shock wave range of the fuselage head, and part of the wing is located in the fuselage head shock range. Embedded waverider wing design is carried out outside the scope of the internal shock wave.

[0044] The fuselage adopts the shape of the fuselage obtained in Example 1. The waverider leading edge line is two straight line segments with segmental sweep. Among them, the sweep angle of the inner straight section close to the fuselage is 65°, and the straight section is located in the flow field behind the shock wave of the fuselage head as a whole; the sweep angle of the outer straight section far away from the fuselage is 52°, and the straight section along the The shock wave spanwise across the nose of the fuselage enters the free stream....

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Abstract

The present invention proposes a hypersonic embedded waverider design method, which is proposed based on the idea of ​​partial decoupling. Compared with the traditional method, the basic body that generates the shock wave flow field in the design method proposed by the present invention is the fuselage , while the primitives in the traditional method are not components of the final aircraft. The method proposed by the invention breaks through the scope of the traditional design method that the fuselage and wings must be designed in a spanwise direction based on the flow field of the same shock wave intensity, and regards the fuselage as a high-volume component and the wing as a high lift-to-drag ratio component , therefore, the fuselage can be designed based on higher-intensity shock waves, even without considering the waverider design. The wing is based on the flow field of the fuselage to construct the embedded waverider reference flow field for waverider design. The design method of the present invention can obtain the aerodynamic layout of the hypersonic aircraft while taking into account both high volume ratio and high lift-to-drag ratio.

Description

technical field [0001] The invention belongs to the field of hypersonic aircraft design, in particular to a design method for a hypersonic embedded waverider. Background technique [0002] The waverider layout is a form of hypersonic aircraft layout that enables the shock wave to attach to the leading edge and the high-pressure gas behind the wave to be located under the body without leakage. It has higher lift-drag than wing-body combination or lift body layout Therefore, it has received great attention from researchers all over the world. [0003] Since Nonweiler proposed the concept of waveriders in 1959, a variety of waverider design methods have been proposed. Generally speaking, the basic idea of ​​the traditional waverider design method is to construct a basic body first, and obtain the shock wave flow field generated by the basic body under the design conditions, and then apply streamline tracing and other methods in the shock wave flow field to obtain the multiplie...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00B64C30/00
CPCB64C30/00B64F5/00
Inventor 蒋崇文罗磊许晨豪高振勋李椿萱
Owner BEIHANG UNIV