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CN-121973927-A - Low-loss high-efficiency aircraft control surface jet exciter

CN121973927ACN 121973927 ACN121973927 ACN 121973927ACN-121973927-A

Abstract

The application discloses a low-loss high-efficiency aircraft control surface jet exciter in the technical field of jet flow control, which particularly comprises a jet cavity and a jet slit, the jet flow cavity is arranged in the control surface along the direction of the spreading direction of the control surface, and the jet flow seam is arranged on the upper surface of the control surface along the direction of the spreading direction of the control surface; a transition flow channel is arranged between the jet flow seam and the jet flow cavity, one end of the transition flow channel is communicated with the jet flow seam, the other end of the transition flow channel is communicated with the jet flow cavity, and the transition flow channel part extends to the inside of the jet flow cavity. According to the application, by extending the transition flow passage into the jet flow cavity, the flow separation at the joint position of the transition flow passage and the jet flow cavity is effectively avoided, so that the flow separation of the compressed air can be restrained on the control surface, and the integral lift coefficient of the aircraft is improved.

Inventors

  • JIANG YUBIAO
  • SU XINLIN
  • TANG KUN
  • PAN JIAXIN
  • QIN CHEN
  • ZHAO XINHAI
  • HUANG YONG
  • WANG WANBO
  • WU FUZHANG
  • LI CHAOQUN
  • LIU YAN
  • BIE YUNPENG

Assignees

  • 中国空气动力研究与发展中心低速空气动力研究所

Dates

Publication Date
20260505
Application Date
20260408

Claims (10)

  1. 1. The low-loss high-efficiency aircraft control surface jet exciter is applied to a control surface (100) of an aircraft and is characterized by comprising a jet cavity (200) and a jet slit (400), wherein the jet cavity (200) is arranged in the control surface (100) along the direction of the spanwise direction of the control surface (100), and the jet slit (400) is arranged on the upper surface of the control surface (100) along the direction of the spanwise direction of the control surface (100); A transition flow channel (500) is arranged between the jet flow slit (400) and the jet flow cavity (200), one end of the transition flow channel (500) is communicated with the jet flow slit (400), the other end of the transition flow channel (500) is communicated with the jet flow cavity (200), and part of the transition flow channel (500) extends to the inside of the jet flow cavity (200).
  2. 2. The low loss high efficiency aircraft control surface jet exciter of claim 1, wherein the inlet orientation of the transition flow passage (500) is obliquely disposed relative to the outlet orientation of the jet slot (400); And/or the transition flow channel (500) narrows gradually from one end close to the jet cavity (200) to one end close to the jet slit (400).
  3. 3. The low loss high efficiency aircraft control surface jet exciter of claim 2, wherein said transition flow passage (500) includes a first transition surface (510) and a second transition surface (520), said first transition surface (510) being located on a side of said transition flow passage (500) remote from said jet slot (400) outlet, said second transition surface (520) being located on a side of said transition flow passage (500) proximate to said jet slot (400) outlet; The first transition surface (510) is distributed in a Vickers Xin Si curve on the cross section of the control surface (100), and the first transition surface (510) extends into the jet cavity (200) partially; The second transition surface (520) transitions smoothly from the fluidic slot (400) to the fluidic chamber (200).
  4. 4. A low loss, high efficiency aircraft control surface jet actuator as defined in claim 3, wherein said first transition surface (510) is smoothly transitioned to an interior wall of said jet cavity (200).
  5. 5. The low-loss high-efficiency aircraft control surface jet exciter according to claim 1, wherein a plurality of rectifying partitions (300) are arranged in the jet slit (400), and the rectifying partitions (300) are distributed along the direction of the control surface (100) and divide the outlet of the jet slit (400) into a plurality of rectifying gaps (410).
  6. 6. The low-loss high-efficiency aircraft control surface jet exciter of claim 5, wherein a plurality of rectifying partitions (300) cover 15% -25% of the outlet area of the jet slot (400).
  7. 7. The low-loss high-efficiency aircraft control surface jet exciter of claim 5, wherein a plurality of said rectifying partitions (300) are equally spaced along the direction of the control surface (100).
  8. 8. The low-loss high-efficiency aircraft control surface jet exciter according to any of claims 5 to 7, characterized in that the ratio of the width of the rectifying partition (300) in the direction of the control surface (100) to the height of the jet slot (400) is 2.5 to 10.
  9. 9. The low-loss high-efficiency aircraft control surface jet actuator of any one of claims 5 to 7, wherein the ratio of the length of the rectifying partition (300) in the fluid flow direction to the height of the jet slit (400) is 2 to 5.
  10. 10. The low-loss high-efficiency aircraft control surface jet exciter according to any one of claims 5 to 7, wherein a plurality of the rectifying partitions (300) are all positioned on the equal straight section of the jet slit (400), and the end surfaces of the rectifying partitions (300) are flush with the plane of the outlet of the jet slit (400).

Description

Low-loss high-efficiency aircraft control surface jet exciter Technical Field The invention relates to the technical field of jet flow control, in particular to a low-loss high-efficiency aircraft control surface jet exciter. Background The mechanical high-lift configuration of the transport aircraft mainly comprises structures such as a front edge slat, a main wing and a rear edge flap (single section or multiple sections), but the performance of the mechanical high-lift configuration is almost approaching to the limit at present, and the potential for continuously optimizing and improving the maximum lift coefficient of the mechanical high-lift configuration is limited. On this basis, the addition of active flow control techniques becomes an effective means of improving the lift coefficient of the flap. In the related art, gas is compressed and introduced into a jet exciter, jet with high speed is formed through a long and narrow jet slot, momentum is injected into a specific flow field above a flap, and nearby flow separation can be effectively eliminated, so that the lift force is remarkably improved. Because the jet flow seam needs to achieve the effect of jetting fluid, a transition flow channel is needed to be arranged in the jet flow exciter to compress gas and jet the gas through the jet flow seam, so that the reduction of the flow velocity caused by energy loss when the gas is jetted out of the jet flow seam is avoided. The related art has the advantage that the transition flow channel is arranged between the jet flow seam and the jet flow cavity as an intermediate connecting piece, so that the problem of partial energy loss can be solved. However, the connection between the transition flow passage and the jet cavity is blocked, which is unfavorable for the flow of compressed gas, and the gas consumes a great amount of kinetic energy before being ejected out of the jet slit. Disclosure of Invention The application discloses a low-loss high-efficiency aircraft control surface jet exciter, which aims to solve the technical problem of excessive energy loss when compressed gas in a jet cavity is ejected from a jet slot through a transition flow passage in the related technology. In order to solve the problems, the application adopts the following technical scheme: The application provides a low-loss high-efficiency aircraft control surface jet flow exciter which is applied to an aircraft control surface and particularly comprises a jet flow cavity and a jet flow seam, the jet flow cavity is arranged in the control surface along the direction of the spreading direction of the control surface, and the jet flow seam is arranged on the upper surface of the control surface along the direction of the spreading direction of the control surface; A transition flow channel is arranged between the jet flow seam and the jet flow cavity, one end of the transition flow channel is communicated with the jet flow seam, the other end of the transition flow channel is communicated with the jet flow cavity, and the transition flow channel part extends to the inside of the jet flow cavity. Further, the inlet orientation of the transition flow channel is obliquely arranged relative to the outlet orientation of the jet slit; And/or the transition flow channel is gradually narrowed from one end close to the jet cavity to one end close to the jet slit. Further, the transition flow channel comprises a first transition surface and a second transition surface, the first transition surface is positioned at one side of the transition flow channel far away from the jet slit outlet, and the second transition surface is positioned at one side of the transition flow channel near the jet slit outlet; the first transition surface is a View Xin Si curve on the cross section of the control surface, and the View Xin Si curve part extends into the jet cavity; the second transition surface smoothly transitions from the fluidic seam to the fluidic chamber. Further, the first transition surface and the inner wall of the jet cavity are in smooth transition. Further, a plurality of rectifying partitions are arranged in the jet flow seam, the rectifying partitions are distributed along the direction of the rudder surface and divide the jet flow seam outlet into a plurality of rectifying gaps. Further, the plurality of rectifying partitions cover 15% -25% of the outlet area of the jet flow seam. Furthermore, the plurality of rectifying partitions are distributed at equal intervals along the direction of the rudder surface. Further, the ratio of the width of the rectifying partition in the direction of the control surface to the height of the jet flow seam is 2.5-10. Further, the ratio of the length of the rectifying partition in the fluid flowing direction to the height of the jet flow seam is 2-5. Further, the rectifying partition is positioned at the equal straight section of the jet flow slot, and the end face of the rectifying partition is flu