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Vector nozzle design method and vector nozzle

A design method and nozzle technology, applied in the field of vector nozzles, can solve the problems of low angular actuation accuracy, complex design of circular vector nozzles, and difficulty in grasping the operation mode.

Inactive Publication Date: 2018-06-15
HAINAN UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, the circular vector nozzle has the problems of complex design, difficult to grasp the action mode, and low angle action accuracy.

Method used

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  • Vector nozzle design method and vector nozzle
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  • Vector nozzle design method and vector nozzle

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Embodiment Construction

[0033] It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0034] The present invention will be further described below in conjunction with the accompanying drawings.

[0035] The invention provides a method for designing a vector nozzle. The vector nozzle includes three interconnected cylindrical structures, wherein both ends of the second cylinder B are elliptical sections, and the first section A and the second section B pass through the first section A and the second section B. An elliptical section is connected, and the second section B and the third section C are connected through the second elliptical section, such as figure 1 shown. The design method includes the following steps:

[0036] Determine the inner diameter r of the vector nozzle; determine the semi-minor axis a and semi-major axis b of the ellipse section according to the inner diameter r of the vector no...

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Abstract

The invention discloses a vector nozzle design method and a vector nozzle and relates to the field of aircraft vector nozzle design. The design method comprises the steps that the inner diameter r ofthe vector nozzle is determined; a semi-minor axis a and a semi-major axis b of an oval cross section are determined according to the inner diameter r of the vector nozzle; a coordinate system oe-xeyeze is established with the center point of the oval cross section being an origin, wherein the xeye plane coincides with the oval cross section, and the ze axis coincides with the axis of a second cylinder segment; a coordinate system oc-xcyczc is established with the center point of a projection circle of the oval cross section being an origin, wherein the xcyc plane coincides with a vertical plane, and the zc axis coincides with the axis of the second cylinder segment; a coordinate system O-XYZ is established with one point on the projection circle of the oval cross section being an origin,wherein the XY plane coincides with a vertical plane, and the Z axis is perpendicular to the axis of the second cylinder segment; and horizontal coordinates and vertical coordinates of points on the oval cross section are calculated to obtain the shapes of two cross sections of the second cylinder segment. The method is simple in calculation, and the vector nozzle is convenient to cut and manufacture.

Description

technical field [0001] The invention relates to a vector nozzle of an aircraft, in particular to a design method of a vector nozzle and the vector nozzle. Background technique [0002] The flight angle of attack of ordinary aircraft is relatively small. In this state, the wings and tail of the aircraft can generate enough lift to ensure the normal flight of the aircraft. When the angle of attack of the aircraft gradually increases, the tail of the aircraft will be caught in the low-energy wake of the wings, causing the tail to stall, and the aircraft will enter a spin and crash. At this time, even if the engine is working normally, it is impossible to keep the aircraft in balance and stay in the air. However, when the aircraft adopts thrust vectoring, the engine nozzle deflects up and down, and the generated thrust no longer passes through the aircraft's center of gravity, resulting in a pitch moment around the aircraft's center of gravity. At this time, the thrust plays th...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 李晖
Owner HAINAN UNIVERSITY
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