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A Sweep Angle-controllable Spike Close Cone Waverider

A sweep angle and waverider technology, which is applied in aircraft control, affects the air flow through the aircraft surface, aircraft parts, etc. Aerodynamic performance, design favorable effect

Inactive Publication Date: 2016-09-28
AERODYNAMICS NAT KEY LAB
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0011] The design of the upper surface is difficult. The design of the expansion surface can improve the aerodynamic performance but reduce the volume efficiency, and the design of the compression surface can improve the volume efficiency but reduce the aerodynamic performance. At present, the general design is a free flow surface, which has no contribution to the aerodynamic performance and volume efficiency. ;
[0012] Low-speed performance is poor, because the design of the waverider only considers the performance of the design state, so the performance of other speed domains, especially the take-off and landing and transonic flight performance is poor

Method used

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  • A Sweep Angle-controllable Spike Close Cone Waverider
  • A Sweep Angle-controllable Spike Close Cone Waverider
  • A Sweep Angle-controllable Spike Close Cone Waverider

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Embodiment Construction

[0045] The present invention installs the following steps to implement:

[0046] 1. According to the design requirements, the cruising Mach number, flight altitude and fuselage length are given;

[0047] 2. To determine the sweep angle, first determine the upper limit of the sweep angle of the waverider by the cruise Mach number, and then select a reasonable sweep angle according to the design requirements;

[0048] 3. To determine the shock angle, first determine the variation range of the shock angle by the cruise Mach number and the upper limit of the sweep angle, and then select a reasonable shock angle according to the design requirements;

[0049] 4. Given the curved surface of the flow capture pipe, the curved surface is determined by the projection curve of the flow capture pipe on the plane where the bottom of the waverider is located. In order to ensure a straight leading edge, the curve adopts a straight line segment with a certain angle with the horizontal line , ...

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Abstract

The invention discloses a sharp vertex osculation tapered wave-rider with a controllable sweepback. A whole front edge of the wave-rider is a straight-line section; the angle of the sweepback at the front edge of the straight-line section is controllable at a design phase; a gas capturing curve is composed of one straight-line section and one section of circular arc; the circular arc is located on one side close to a symmetrical plane; and a circular center is an end point located on the symmetrical plane of a flowing capturing tube curve. According to the sharp vertex osculation tapered wave-rider, a stable separation vortex is generated on the upper surface of the front edge of a straight line with the controllable sweepback; and the aerodynamic performance of the upper surface is improved and the volume efficiency of an air vehicle is not sacrificed, so that the design of the upper surface is facilitated very well.

Description

technical field [0001] The invention relates to the field of aerodynamics, in particular to a pointed apex close cone waverider with controllable sweep angle. Background technique [0002] When an aircraft with a traditional layout flies at hypersonic speed, the maximum lift-to-drag ratio has the following relationship with the flight Mach number: [0003] ( L / D ) m a x = 4 ( M ∞ + 3 ) M ∞ [0004] where M ∞ is the flight Mach number. It can be seen from the above formula that when the traditional layout is at a high Mach number, the maximum lift-to-drag ratio can only reach ab...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C21/00
Inventor 段焰辉范召林吴文华余雷
Owner AERODYNAMICS NAT KEY LAB
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