Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet

A bistable and air inlet technology, applied in mechanical equipment, gas turbine devices, jet propulsion devices, etc., can solve problems such as the inability to change the shape of the bulge, the decline in the efficiency of the inlet port and the matching characteristics of the advance, and achieve a solution to the compression profile Non-adjustable problem, effect of changing throat area

Inactive Publication Date: 2012-06-27
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the shape of the bulge cannot be changed, and it can only exert its maximum characteristics at the design flight speed level. When the flight speed changes, it still faces the problem of declining air intake efficiency and launch matching characteristics.

Method used

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  • Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet
  • Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet
  • Bistable air inlet, its application as aircraft air inlet and design method of bistable air inlet

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Embodiment 1

[0035] Such as figure 1 As shown, the bistable air inlet of this embodiment includes an air inlet wall 1 on which a bistable structural region 2 is arranged. The bistable structural region 2 is a bistable structural region having a first stable configuration and a second stable configuration. When the bistable structural region 2 is in the first stable configuration, it reaches the airway wall 1 The distance is A0, when the bistable structure region 2 is in the second stable configuration, the distance from it to the airway wall 1 is A1, A0

Embodiment 2

[0037] Such as figure 2As shown, the bistable air intake in this embodiment includes an air intake area composed of an air intake cover 3 and an aircraft fuselage bulge profile 4, and the aircraft fuselage bulge profile 4 is provided with at least one Bistable structure region 41 . The bistable structure area 41 is located in the bulge area 42 of the bulge profile 4 of the aircraft fuselage. Between the highest point of the bulge area 42 and the air inlet cover 3 is the position of the throat. When the bistable structure region 41 is in the first stable configuration, the distance from the bulge region 42 to the airway cover 3 is A0; when the bistable structure region 41 is in the second stable configuration, the distance from the bulge region 42 to the airway cover The distance of 3 is A1, A0

[0038] When the bistable air inlet of the above embodiment is applied to the air inlet of an aircraft, when the aircraft is flying at high speed, the bistable configuration is ...

Embodiment 3

[0040] This embodiment relates to the design method of the bistable structure area in the bistable inlet duct, specifically:

[0041] (1) Select the profile of the throat area of ​​the bulging inlet as the deformed profile, select the appropriate bistable thin shell structural mechanical model according to the shape of the deformed profile, and determine the shape design parameters of the model.

[0042] In the throat area of ​​the bulging inlet duct, a deformed surface with a circular boundary is selected, and the mechanical model of a shallow spherical shell with a round bottom is used to design the bistable structure. The shape parameters of the model include: the diameter of the bottom surface is 2a, the arch height is h, and the thickness is t .

[0043] (2) Using the comprehensive design technology of theoretical calculation and numerical simulation, the deformation mechanism and mechanical properties of the bistable structural mechanics model under different driving mod...

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PUM

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Abstract

The invention discloses an aircraft air inlet with a bistable structure, and simultaneously relates to a design method of the bistable air inlet. The bistable structure area is designed differently according to different forms of aircraft air inlets. When an aircraft has an independent air inlet pipeline, the bistable structure can be arranged on the wall of the inlet pipeline; when the air inlet area of the aircraft is formed by an air inlet enclosure and an airframe bump profile, the bistable structure can be disposed in a bump area of the airframe bump profile. The design method designs the bistable structure area, and finally determines its structural parameters. The air inlet of the invention with a bistable and deformable structure realizes local concave-convex deformation of an air inlet, such as the compression profile of a bump air inlet, so that the throat area of the air inlet is changed, and the problem of an unadjustable compression profile of the bump air inlet is solved. Thus, under different flying states, the aircraft can have the optimal air inlet performance and inlet-engine matching property.

Description

technical field [0001] The invention relates to an aircraft inlet structure, in particular to an aircraft inlet with a bistable structure, and at the same time relates to a design method of the bistable inlet and its application as an aircraft inlet. Background technique [0002] The propulsion system is an important part of military aircraft. It is related to the combat performance and safety of the aircraft. The air intake is the most important part of the propulsion system. It has a great impact on the flight performance and life cycle of the aircraft. Especially for supersonic fighters with wide speed range and high maneuverability, the inlet must maintain good aerodynamic performance and launch matching characteristics under a wide range of flight speeds and angles of attack. [0003] The existing supersonic inlet design process often faces the contradiction between high and low speed aerodynamic configuration: at low speed, the inlet needs a large flow area and blunt l...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/042
Inventor 张平邱涛周丽
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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