Integrated assembly of binary adjustable air inlet passage and an aircraft forebody and design method

A technology for air intakes and aircraft, which is applied in the direction of aircraft parts, air intake combustion of power devices, power devices on aircraft, etc. It can solve the problems of increasing the weight of the airframe and flight resistance, so as to improve the sideslip performance and improve the uniformity. sex, performance-improving effect

Active Publication Date: 2021-07-23
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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  • Integrated assembly of binary adjustable air inlet passage and an aircraft forebody and design method
  • Integrated assembly of binary adjustable air inlet passage and an aircraft forebody and design method
  • Integrated assembly of binary adjustable air inlet passage and an aircraft forebody 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 assembly of a binary adjustable air inlet passage and an aircraft forebody. The integrated assembly comprises a first-stage fixed compression wedge surface, a second-stage adjustable compression wedge surface, a throat section, an expansion section, a lip mask, a driving motor, a connecting rod component and a side plate, the aircraft forebody comprises a first-stage bump, a second-stage bump, a transition molded surface and a strake wing. According to the integration method disclosed by the invention, the binary adjustable air inlet channel and the aircraft fuselage are highly fused, so that the external resistance of the aircraft is effectively reduced; the two-stage bulge molded surface of the fuselage not only can effectively eliminate the developed thick boundary layer of the fuselage, but also can decelerate and pressurize the supersonic airflow and improve the performance of the air inlet channel.

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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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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