An adaptive bulging inlet shape control method based on flexible skin

A control method and air inlet technology, applied in the field of aeronautical structure design, can solve the problems of unadjustable three-dimensional profile and poor performance, etc.

Active Publication Date: 2016-11-02
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Application Information

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Problems solved by technology

However, the three-dimensional profile of this inlet is not adjustable, and it can only achieve the best performance at the design flight speed, while the performance becomes worse at non-design points

Method used

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  • An adaptive bulging inlet shape control method based on flexible skin
  • An adaptive bulging inlet shape control method based on flexible skin
  • An adaptive bulging inlet shape control method based on flexible skin

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Embodiment Construction

[0018] The specific implementation manners of the present invention will be further described in detail below.

[0019] The bulge surface of the bulge air intake is a three-dimensional surface designed aerodynamically, and the area between the bulge surface and the air intake cover is the throat of the air intake, such as figure 1 shown. On the bulge surface, a certain area is selected as the deformation area of ​​the bulge inlet. The deformed area is in the shape of an oblate spheroid, and its outline is generally elliptical, and may also be circular or other suitable shapes.

[0020] The initial position of the bulge profile is the base profile, which is a rigid surface and is usually made of metal materials such as aluminum alloy. In the deformed area, a layer of flexible skin is attached to the inner and outer surfaces of the basic surface ("inner side" is the side pointing to the plane of symmetry of the aircraft fuselage, and "outer side" is the opposite direction to "...

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Abstract

The invention belongs to the technical field of aviation structure design, and relates to an adaptive bump air inlet passage shape control method based on a flexible skin. The adaptive bump air inlet passage shape control method based on the flexible skin includes: selecting a plurality of typical monitoring points from the inner surface of the outside flexible skin, and arranging a large deformation strain sensor and a displacement sensor; performing ground demarcation on the outside flexible skin, and obtaining a relationship among displacement and other parameters of each monitoring point of the flexible skin; confirming flow requirements of an engine of an airplane at different flight speed according to a flow matching relationship between an air inlet passage and the engine so as to obtain a relationship between the flight speed and displacement of the outside flexible skin; obtaining the displacement of each monitoring point on the outside flexible skin in real time so as to obtain the shape of the outside flexible skin under current status and confirm the position of a profile of a bump; controlling the position of the profile of the bump according to the current flight speed of the airplane so as to regulate the area of an air inlet passage throat and match the area of the air inlet passage throat with the flow requirements of the engine.

Description

technical field [0001] The invention belongs to the technical field of aeronautical structure design, and relates to a method for controlling the shape of an adaptive bulge air inlet based on a flexible skin. Background technique [0002] Advanced supersonic fighter has the characteristics of wide speed range, high maneuverability and high stealth capability. In order to improve the stealth performance of the aircraft, the fourth-generation fighters generally adopt the ternary air inlet, such as the Bump (bulge) air inlet used by the F-35 aircraft of the United States. However, the three-dimensional profile of this air intake is not adjustable, and it can only achieve the best performance at the design flight speed, while the performance at non-design points becomes worse. If the air inlet can maintain high performance in the full flight envelope, the flight performance and combat capability of the supersonic fighter will be significantly improved. [0003] The adaptive bu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21D26/021
Inventor 邱涛周翌勋王鄢靳诚忠
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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