Device for testing wind resistance of fixed-wing aircraft

Abstract

The utility model discloses a device for testing the wind resistance of a fixed-wing aircraft, and relates to the technical field of aircraft manufacturing and testing devices. According to the technical scheme, the device is characterized by comprising a base, a fixing assembly used for fixing an airplane is arranged at one end of the surface of the base, an air blowing assembly blowing air towards the fixing assembly is arranged at the other end of the surface of the base, the fixing assembly comprises supporting plates arranged on the two sides of the surface of the base, and a positioning ring is arranged between the two supporting plates; rotating shafts rotationally connected to the supporting plate are arranged on the two sides of the positioning ring, the first driving part is used for driving the positioning ring to rotate, a fixing plate is further arranged in the positioning ring, and the second driving part is used for driving the fixing plate to deflect in the circumferential direction of the positioning ring. The utility model aims to provide a device for testing the wind resistance of a fixed-wing aircraft.

Description

Technical Field

[0001] This utility model relates to aircraft manufacturing testing equipment, and more specifically, it relates to a testing device for the wind resistance performance of fixed-wing aircraft. Background Technology

[0002] Fixed-wing aircraft, also known as fixed-wing drones, are a type of fixed-wing micro-drone. They are widely used due to their low noise and good stealth capabilities. After the production and processing of fixed-wing aircraft are completed, in order to ensure their normal take-off and landing, it is necessary to test their wind resistance performance during take-off and landing, which requires the use of wind resistance testing equipment.

[0003] Chinese Patent No. CN114720085B discloses a wind resistance performance testing device for fixed-wing aircraft, including a blower mechanism, a base, a fixing mechanism, and a testing mechanism. The blower mechanism includes a support plate fixed to one side of the outer wall of the top of the base, and a circular groove is formed on one side of the outer wall of the support plate. The blower mechanism, the fixing mechanism, and the testing mechanism are located above the base.

[0004] The above-mentioned technical solution can ensure the stability of the aircraft during testing through the fixed mechanism, but it cannot adjust the pitch angle and roll angle of the aircraft. Therefore, it cannot simulate the various states of the aircraft during takeoff and landing, and thus cannot test the wind resistance performance of the aircraft during takeoff and landing.

[0005] Therefore, a new technical solution is urgently needed to solve the above-mentioned technical problems. Utility Model Content

[0006] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide a testing device for the wind resistance performance of fixed-wing aircraft.

[0007] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a testing device for the wind resistance performance of a fixed-wing aircraft, characterized in that: it includes a base, a fixing component for fixing the aircraft is provided at one end of the surface of the base, and a blowing component for blowing air toward the fixing component is provided at the other end of the surface of the base. The fixing component includes support plates provided on both sides of the surface of the base, a positioning ring is provided between the two support plates, and a rotating shaft rotatably connected to the support plates is provided on both sides of the positioning ring. It also includes a first driving member for driving the positioning ring to rotate, a fixing plate is provided inside the positioning ring, and a second driving member for driving the fixing plate to deflect along the circumferential direction of the positioning ring.

[0008] The present invention is further configured such that: the positioning ring has an annular groove along its inner circumference, a rotating ring is rotatably connected in the annular groove, the fixing plate is disposed in the rotating ring and fixedly connected to the inner walls of both sides of the rotating ring, and the second driving member is used to drive the rotating ring to rotate in the annular groove.

[0009] The present invention is further configured such that: the first driving component includes a guide strip disposed on the surface of the base and located below the positioning ring; a guide groove is provided on the upper surface of the guide strip; a guide block is slidably connected in the guide groove; a lead screw is rotatably connected in the guide groove; the lead screw passes through and is threadedly connected to the guide block; a first motor for driving the lead screw is provided at one end of the guide strip; a bottom rod is provided at the top of the guide block, horizontally and perpendicular to the guide strip; vertical plates are provided at both ends of the bottom rod; a limit groove is provided on the vertical plate along the vertical direction; a horizontal limit rod is provided on the outer wall of the positioning ring located below the rotating shaft; the limit rod passes through and is slidably connected in the limit groove.

[0010] The present invention is further configured such that: the second driving member includes a second motor disposed on the top of the positioning ring, the output shaft of the second motor is provided with a gear, the rotating ring is provided with an annular groove along its outer circumference, the annular groove is uniformly provided with toothed rings, the top of the positioning ring is provided with a through groove that passes through the annular groove, and the gear passes through the through groove and meshes with the toothed rings.

[0011] The present invention is further configured such that: the inner walls of the two support plates are provided with arc-shaped grooves for sliding connection of the limiting rod.

[0012] This utility model has the following beneficial effects: When conducting testing, the aircraft to be tested is placed on the surface of the fixed plate using a lifting device, and the aircraft is positioned using a fixing component. The fixing component can be a customized lock or other existing technology, which will not be described in detail in this embodiment. After the aircraft is fixed, the pneumatic blower mechanism blows air. During the test, the pitch and roll angles of the aircraft can be adjusted by the first and second drive components, thereby enabling a more comprehensive test of the aircraft's wind resistance performance. Attached Figure Description

[0013] Figure 1 This is a three-dimensional structural diagram of this embodiment;

[0014] Figure 2 This is a schematic diagram of the positioning ring in this embodiment;

[0015] Figure 3 This is a schematic diagram of the structure of the fixed plate and the rotating ring in this embodiment;

[0016] Figure 4 This is a partial structural diagram of the base in this embodiment.

[0017] Figure descriptions: 1. Base; 2. Fixing assembly; 3. Blowing assembly; 4. Support plate; 5. Positioning ring; 6. Rotating shaft; 7. Fixing plate; 8. Annular groove; 9. Rotating ring; 10. Guide bar; 11. Guide block; 12. Lead screw; 13. First motor; 14. Base rod; 15. Vertical plate; 16. Limiting rod; 17. Second motor; 18. Gear; 19. Gear ring; 20. Arc groove. Detailed Implementation

[0018] The present invention will be further described in detail below with reference to the accompanying drawings.

[0019] Identical parts are indicated by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "up," and "down" used in the following description refer to directions in the accompanying drawings, while the terms "bottom surface," "top surface," "inner," and "outer" refer to directions toward or away from the geometric center of a specific part, respectively.

[0020] As shown in the figure, a testing device for the wind resistance performance of a fixed-wing aircraft includes a base 1. A fixing component 2 for fixing the aircraft is provided at one end of the surface of the base 1, and a blowing component 3 for blowing air toward the fixing component 2 is provided at the other end of the surface of the base 1. The fixing component 2 includes support plates 4 provided on both sides of the surface of the base 1, a positioning ring 5 provided between the two support plates 4, and rotating shafts 6 rotatably connected to the support plates 4 on both sides of the positioning ring 5. It also includes a first driving component for driving the positioning ring 5 to rotate, a fixing plate 7 provided inside the positioning ring 5, and a second driving component for driving the fixing plate 7 to deflect along the circumferential direction of the positioning ring 5.

[0021] During testing, the aircraft to be tested is placed on the surface of the fixed plate 7 using lifting equipment, and positioned using fasteners. The fasteners can be existing technologies such as customized locks, which will not be elaborated in this embodiment. After the aircraft is fixed, the pneumatic blower mechanism blows air. During the test, the pitch and roll angles of the aircraft can be adjusted by the first and second drive components, so as to more comprehensively test the wind resistance performance of the aircraft.

[0022] The positioning ring 5 has an annular groove 8 along its inner circumference. A rotating ring 9 is rotatably connected in the annular groove 8. The fixing plate 7 is disposed in the rotating ring 9 and fixedly connected to the inner walls on both sides of the rotating ring 9. The second driving member is used to drive the rotating ring 9 to rotate in the annular groove 8.

[0023] The first driving component includes a guide bar 10 disposed on the surface of the base 1 and located below the positioning ring 5. A guide groove is provided on the upper surface of the guide bar 10. A guide block 11 is slidably connected in the guide groove. A lead screw 12 is rotatably connected in the guide groove. The lead screw 12 passes through and is threadedly connected to the guide block 11. A first motor 13 for driving the lead screw 12 is provided at one end of the guide bar 10. A bottom rod 14 is provided at the top of the guide block 11, which is horizontal and perpendicular to the guide bar 10. Vertical plates 15 are provided at both ends of the bottom rod 14. Limiting grooves are provided in the vertical direction of the vertical plates 15. A horizontally arranged limiting rod 16 is provided on the outer wall of the positioning ring 5 located below the rotating shaft 6. The limiting rod 16 passes through and is slidably connected in the limiting groove.

[0024] The first motor 13 drives the lead screw 12 to rotate, which in turn drives the guide block 11 to slide along the guide groove, thereby driving the bottom rod 14 and the vertical plate 15 to move, and finally driving the limit rod 16 to move, while driving the positioning ring 5 to deflect, thereby adjusting the pitch angle of the aircraft.

[0025] The second driving component includes a second motor 17 disposed at the top of the positioning ring 5. The output shaft of the second motor 17 is equipped with a gear 18. A groove is formed along the outer circumference of the rotating ring 9, and toothed rings 19 are evenly arranged within the groove. A through slot is formed at the top of the positioning ring 5, penetrating the groove. The gear 18 passes through the through slot and meshes with the toothed rings 19. The second motor 17 drives the toothed rings 19 via the gear 18, thereby causing the rotating ring 9 to rotate along the annular groove 8, thus adjusting the aircraft's roll angle.

[0026] The inner walls of the two support plates 4 are provided with arc-shaped grooves 20 for sliding connection of the limiting rod 16. When the positioning ring 5 deflects, the end of the limiting rod 16 slides along the arc-shaped groove 20 to improve the stability of the equipment during testing.

[0027] The specific embodiments are merely explanations of this utility model and are not intended to limit it. After reading this specification, those skilled in the art can make modifications to these embodiments without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this utility model.

Claims

1. A test apparatus for the wind resistance of a fixed-wing aircraft, characterized by: The device includes a base (1), a fixing component (2) for fixing an aircraft is provided at one end of the surface of the base (1), and a blowing component (3) for blowing air toward the fixing component (2) is provided at the other end of the surface of the base (1). The fixing component (2) includes support plates (4) provided on both sides of the surface of the base (1), a positioning ring (5) is provided between the two support plates (4), and a rotating shaft (6) rotatably connected to the support plate (4) is provided on both sides of the positioning ring (5). The device also includes a first driving member for driving the positioning ring (5) to rotate. A fixing plate (7) is also provided inside the positioning ring (5). The device also includes a second driving member for driving the fixing plate (7) to deflect along the circumferential direction of the positioning ring (5).

2. The test device for the wind resistance performance of a fixed-wing aircraft according to claim 1, characterized in that: The positioning ring (5) has an annular groove (8) along its inner circumference. A rotating ring (9) is rotatably connected in the annular groove (8). The fixing plate (7) is provided inside the rotating ring (9) and fixedly connected to the inner walls on both sides of the rotating ring (9). The second driving member is used to drive the rotating ring (9) to rotate in the annular groove (8).

3. The test apparatus for the wind resistance performance of a fixed-wing aircraft according to claim 1, characterized in that: The first driving component includes a guide bar (10) disposed on the surface of the base (1) and located below the positioning ring (5). A guide groove is provided on the upper surface of the guide bar (10). A guide block (11) is slidably connected in the guide groove. A lead screw (12) is rotatably connected in the guide groove. The lead screw (12) passes through and is threadedly connected to the guide block (11). A first motor (13) for driving the lead screw (12) is provided at one end of the guide bar (10). A bottom rod (14) is horizontal and perpendicular to the guide bar (10) at the top of the guide block (11). Vertical plates (15) are provided at both ends of the bottom rod (14). A limit groove is provided in the vertical direction of the vertical plate (15). A horizontal limit rod (16) is provided on the outer wall of the positioning ring (5) located below the rotating shaft (6). The limit rod (16) passes through and is slidably connected in the limit groove.

4. The test apparatus for the wind resistance performance of a fixed-wing aircraft according to claim 2, characterized in that: The second driving component includes a second motor (17) disposed on the top of the positioning ring (5). The output shaft of the second motor (17) is provided with a gear (18). The rotating ring (9) has an annular groove along its outer circumferential wall. Gear rings (19) are evenly disposed in the annular groove. The top of the positioning ring (5) has a through groove that passes through the annular groove. The gear (18) passes through the through groove and meshes with the gear ring (19).

5. The device for testing the wind resistance of a fixed-wing aircraft according to claim 4, characterized in that: The two support plates (4) have arc-shaped grooves (20) on their opposite inner walls for sliding connection of the limiting rod (16).

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