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A binary adjustable intake port and aircraft precursor integrated assembly and design method

An air intake and aircraft technology, which is applied in the directions of aircraft parts, air intake combustion of power units, power units on aircraft, etc., can solve the problems of increasing the weight of the body and flight resistance, and achieves improved sideslip performance and uniformity. performance, improve performance

Active Publication Date: 2022-04-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In the early days, in order to prevent the intake port from inhaling the boundary layer, the engineering would set up a partition between the intake port and the body. This method has many disadvantages, such as increasing the weight of the body and flight resistance.

Method used

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  • A binary adjustable intake port and aircraft precursor integrated assembly and design method
  • A binary adjustable intake port and aircraft precursor integrated assembly and design method
  • A binary adjustable intake port and aircraft precursor integrated assembly and design method

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Embodiment Construction

[0044] The technical solutions provided by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0045] see Figure 1 to Figure 3 As shown, the binary adjustable air inlet provided by the present invention and the integrated assembly of the aircraft precursor include the inlet of the air inlet, the two-stage adjustable compression wedge surface 4 located at the front of the inlet of the air inlet, and the two-stage adjustable compression wedge surface located at the front of the air inlet. The primary fixed compression wedge surface 3, the throat section 8, the expansion section 9, the connecting rod part 10 and the driving device 11 at the front part of the wedge surface 4. Wherein, the first-stage fixed compression wedge surface 3 is connected with the second-stage bulging trailing edge of the precursor, and its compression angle is 8°; Triangular staircase.

[0046] The front of the primary fixed compression wedge surface...

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Abstract

The invention discloses an integrated component of a binary adjustable air inlet and an aircraft precursor, comprising a first-stage fixed compression wedge surface, a second-stage adjustable compression wedge surface, a throat section, an expansion section, a lip cover, a drive motor, Connecting rod parts and side panels; the aircraft precursor includes a first-level bulge, a second-level bulge, a transition profile and side strip wings. The integration method described in the present invention highly integrates the binary adjustable air inlet with the aircraft fuselage, effectively reducing the external resistance of the aircraft; the two-stage bulging profile of the fuselage can not only effectively eliminate the thick boundary layer developed by the fuselage , and can decelerate and boost the supersonic airflow to improve the performance of the intake port.

Description

technical field [0001] The invention relates to the field of aircraft design, and in particular, the invention relates to an integrated assembly of an air inlet and a front body of an aircraft. Background technique [0002] As one of the key components of the air-breathing engine, the supersonic inlet mainly undertakes the task of capturing and compressing the free flow and providing a high-quality flow field to the downstream engine. Generally, when an aircraft is flying at high speed, the airframe will develop a thicker boundary layer. After the intake port absorbs the low-energy flow in the boundary layer, the performance of the intake port will drop sharply, which will eventually affect the performance of the engine. Therefore, the boundary layer developed by the precursor must be dealt with in the design of the inlet. [0003] In the early days, in order to prevent the inlet from inhaling the boundary layer, a partition was set between the inlet and the body in enginee...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D33/02
CPCB64D33/02B64D2033/0226B64D2033/026
Inventor 黄河峡汪昆林正康李灿民谭慧俊雷鸣李斌
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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