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CN-115817796-B - Aircraft speed reducer based on airfoil profile

CN115817796BCN 115817796 BCN115817796 BCN 115817796BCN-115817796-B

Abstract

The invention provides an aircraft speed reducer based on an airfoil profile, which comprises a machine body, a speed reducer body, a first actuator cylinder and a second actuator cylinder, wherein one side of the machine body is provided with a containing groove, the speed reducer body is movably connected with the containing groove, one end of the first actuator cylinder is connected with the containing groove, the other end of the first actuator cylinder is connected with the bottom of the speed reducer body, one end of the second actuator cylinder is connected with the containing groove, the other end of the second actuator cylinder is connected with the middle part or the top of the speed reducer body, and the longitudinal profile of the speed reducer body is an inverted airfoil. When the wind tunnel force measuring device works, the first actuating cylinder is started to lift the front edge of the speed reducing plate body, the front edge of the speed reducing plate body is guaranteed to protrude out of the machine body to a certain height, the second actuating cylinder is started to enable the speed reducing plate body to rotate around a supporting point of the first actuating cylinder on the speed reducing plate body to an opening and closing angle, and wind tunnel force measuring tests of different opening and closing angles relative to the flat plate speed reducing plate are conducted. The invention has obvious resistance increasing effect and strong practicability.

Inventors

  • LI QIAN
  • ZHANG QIUSHI
  • ZHANG WEI
  • LI XIANGZHENG
  • ZHANG JIABAO
  • LU WEI
  • JIA YI

Assignees

  • 中国航天空气动力技术研究院

Dates

Publication Date
20260508
Application Date
20221226

Claims (8)

  1. 1. The aircraft speed reducing plate based on the wing profile is characterized by comprising a machine body (1), a speed reducing plate body (2), a first actuating cylinder (3) and a second actuating cylinder (5), wherein a containing groove is formed in one side of the machine body (1), the speed reducing plate body (2) is movably connected with the containing groove, one end of the first actuating cylinder (3) is connected with the containing groove, the other end of the first actuating cylinder is connected with the bottom of the speed reducing plate body (2), one end of the second actuating cylinder (5) is connected with the containing groove, the other end of the second actuating cylinder is connected with the middle part or the top of the speed reducing plate body (2), the longitudinal profile of the speed reducing plate body (2) is an inverted wing profile, the lower edge of the speed reducing plate body (2) is a front edge, one surface with a large wing profile protruding radian is located on the leeward surface of the speed reducing plate body (2), and the front edge of the speed reducing plate body (2) protrudes out of the machine body (1) by 1-30mm.
  2. 2. Aerofoil section based aircraft speed reducing plate according to claim 1, wherein the first actuator cylinder (3) is connected to the speed reducing plate body (2) by a speed reducing plate rotational shaft (4).
  3. 3. Aerofoil section based aircraft speed reducing plate according to claim 1, wherein the fuselage (1) is cuboid.
  4. 4. The aerofoil section based aircraft speed reduction plate of claim 1, wherein the receiving slot is a cuboid.
  5. 5. Aerofoil section based aircraft speed reduction plate according to claim 1, wherein the opening and closing angle of the speed reduction plate body (2) is 20 ° to 60 °.
  6. 6. Aerofoil section based aircraft speed reduction plate according to claim 5, wherein the opening and closing angle of the speed reduction plate body (2) is 30 °.
  7. 7. Aerofoil section based aircraft speed reduction plate according to claim 5, wherein the opening and closing angle of the speed reduction plate body (2) is 45 °.
  8. 8. Aerofoil section based aircraft speed reducing plate according to claim 1, wherein the second actuator cylinder (5) is a telescopic cylinder.

Description

Aircraft speed reducer based on airfoil profile Technical Field The invention relates to the technical field of aerospace, in particular to an aircraft speed reducer based on an airfoil profile. Background The aircraft speed reducing plate is a pneumatic device for realizing the speed reduction of the aircraft, and is widely applied to fighters, civil airliners and reusable space vehicles. When the fighter plane lands and falls, the speed reducing plate is opened to increase resistance, and the running distance is shortened so as to improve landing characteristics, and the landing gear can also be used for rapid speed reduction before maneuvering turning in the air. The speed reducing plate of the civil aircraft is also called a spoiler and a resistance plate, is arranged on the upper surface of the wing, increases resistance when landing, and shortens the landing and running distance. The reusable space vehicle generally combines a plurality of deceleration plates to form a deceleration system, and the deceleration is assisted in the recovery and descent process. The speed reducing plate can be embedded into the machine body or the wing through the recovery device when not in use, and then opened to play a role in increasing resistance and reducing speed when in use. The existing aircraft speed reducing plate mainly increases the size of the speed reducing plate, increases the opening and closing angles and the like. However, the oversized speed reducer plate and the oversized opening and closing angle require additional support and hinge moment, which causes problems of overall weight gain and flight control of the structure. In addition, the conventional speed reducing plate is mostly flat in longitudinal section, and the effective acting area of the leeward vortex cannot be effectively increased. Disclosure of Invention The invention provides a novel speed reducing plate based on an airfoil profile, wherein the longitudinal profile of the speed reducing plate is an inverted airfoil profile, the lower edge of the speed reducing plate is an airfoil leading edge, the surface with larger radian of an airfoil bulge is positioned on the leeward surface of the speed reducing plate, the effective area of the leeward surface is increased, the distance between the lower edge of the speed reducing plate and a machine body is adjusted, so that the flow bypasses the lower edge to form lower edge vortex similar to the vortex of the front edge of the airfoil, the lower edge vortex can further reduce the negative pressure on the leeward side, thereby increasing the resistance of the speed reducing plate, generating the beneficial effect that the hinge moment around the front edge point is not increased while the resistance is increased due to the suction effect of the lower edge vortex, and reducing the control difficulty. The invention provides an aircraft speed reducer based on an airfoil profile, which comprises a machine body, a speed reducer body, a first actuator cylinder and a second actuator cylinder, wherein one side of the machine body is provided with a containing groove, the speed reducer body is movably connected with the containing groove, one end of the first actuator cylinder is connected with the containing groove, the other end of the first actuator cylinder is connected with the bottom of the speed reducer body, one end of the second actuator cylinder is connected with the containing groove, the other end of the second actuator cylinder is connected with the middle part or the top of the speed reducer body, and the longitudinal profile of the speed reducer body is an inverted airfoil. Preferably, the first actuator cylinder is connected with the speed reducing plate body through a speed reducing plate rotating shaft. Preferably, the lower edge of the speed reducing plate body is an airfoil front edge, and the surface with larger airfoil protruding radian is positioned on the leeward surface of the speed reducing plate body. Preferably, the body is a cuboid. Preferably, the accommodating groove is cuboid. Preferably, the opening and closing angle of the speed reducing plate body is 20-60 degrees. Preferably, the opening and closing angle of the speed reducing plate body is 30 degrees. Preferably, the opening and closing angle of the speed reducing plate body is 45 degrees. Preferably, after starting, the front edge of the speed reducer body protrudes 30mm from the body. Preferably the second actuator is a telescopic cylinder. Compared with the prior art, the invention has the beneficial effects that: 1. the speed reducing plate body adopts an airfoil profile, so that the actual area of the leeward surface of the speed reducing plate body, namely the effective acting area of the leeward side vortex, is increased, and the resistance is increased; 2. the front edge of the speed reducing plate body is at a certain height from the machine body through the first actuating cylinder, so that the flow is incre