Special air bag-based axially-symmetrical deformable air inlet channel

An inlet and axisymmetric technology, applied in the field of inlets, can solve the problems of poor cruise performance of fixed-geometry supersonic inlets and high additional cost of adjustable inlets, so as to make full use of internal space, improve cruise performance, Additional cost-effective effects

Inactive Publication Date: 2012-05-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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  • Application Information

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Problems solved by technology

[0005] In order to solve the shortcomings of the existing fixed-geometry supersonic inlets such as poor cruise performance and high additional cost of adjustable inlets, the present invention provides an axisymmetrically

Method used

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  • Special air bag-based axially-symmetrical deformable air inlet channel
  • Special air bag-based axially-symmetrical deformable air inlet channel

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Embodiment Construction

[0010] see figure 1 As shown, the present invention discloses an axisymmetric deformable air inlet based on a special airbag, which includes a front cone 1, an air inlet lip 2 located outside the front cone 1 and surrounding the front cone 1, and a front The special airbag 3 connected by the cone tip 1, the high-pressure air source 8, the intake pipe 9 connecting the high-pressure air source 8 and the special airbag 3, the inflation valve 7 arranged on the intake pipe 9, the deflation valve 6 and the connection deflation valve 6 and The deflation pipe 12 of the special airbag 3. An air inlet throat 10 is formed between the special airbag 3 and the air inlet lip cover 2 . The special airbag 3 is provided with a metal core 5 and an elastic layer 13 covering the metal core 5 , the elastic layer 13 and the metal core 5 enclose an air cavity 11 . The elastic layer 13 is made of heat-resistant rubber, and the inner braid 4 is accommodated in the elastic layer 13, and the deformati...

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Abstract

The invention provides a special air bag-based axially-symmetrical deformable air inlet channel, which comprises a front conical tip, an air inlet channel lip cover, a special air bag, a high-pressure air source and an air inlet pipe, wherein the air inlet channel lip cover is positioned on the outer side of the front conical tip; the special air bag is connected with the front conical tip; the air inlet pipe is connected with the high-pressure air source and the special air sag; and an air inlet channel throat is formed between the special air bag and the air inlet channel lip cover. According to the invention, the throat area of the air inlet channel throat can be adjusted by adjusting the size of the special air bag, so that high total pressure recovering coefficient of the air inlet channel can be ensured, the improvement on the cruising performance of an aerocraft is facilitated, the size of the special air bag is convenient and easy to adjust, the additional adjusting cost is low, the internal space of the aerocraft is utilized fully, and the deformable air inlet channel is easy to realize.

Description

technical field [0001] The invention relates to an air inlet, in particular to a deformable air inlet used on an aircraft. Background technique [0002] As one of the important components of the propulsion system of a supersonic vehicle, the inlet is responsible for many functions such as capturing incoming flow, decelerating, boosting, and rectifying the incoming flow, so its design is quite critical. Its total static pressure recovery characteristics, flow capture The characteristics and resistance characteristics directly affect the working efficiency and operation capability of the propulsion system. At present, it is generally believed that the total pressure recovery coefficient of the intake port has the most direct influence on the thrust of the engine, and every 1% increase in the total pressure recovery coefficient corresponds to a 1.5% increase in engine thrust. However, in order to ensure the starting performance at low Mach number, conventionally designed fixed...

Claims

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Application Information

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IPC IPC(8): F02C7/04F02C7/057
Inventor 谭慧俊张悦孙姝李程鸿张启帆童悦曾平君周唯阳
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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