Airplane shell material wind power detection device

Abstract

The invention discloses an aircraft shell material wind power detection device, and belongs to the technical field of aircraft shell material detection, the aircraft shell material wind power detection device comprises a base mechanism, the base mechanism comprises a workbench, the workbench is mounted at the top end of the base mechanism, mounting plates are mounted on the side walls of the two ends of the workbench, and fixing plates are mounted at the top ends of the mounting plates; and a rotating rod is rotationally installed in the fixing plate through a bearing, an air blower body is installed at one end of the top end of the base mechanism, a display screen body is installed on the side wall of one side of the base mechanism, and a single chip microcomputer is installed on the side wall of one side of the base mechanism. The device has the beneficial effects that the two sets of threaded sleeves slide to drive the device to rotate, meanwhile, the first sliding blocks are matched with the first sliding grooves, the first sliding blocks are driven to slide in the first sliding grooves while rotating, and therefore a positioning plate is driven to position and fix an aircraft shell material body in the mounting frame.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft shell material detection, in particular to a wind force detection device for aircraft shell material. Background Art

[0002] The aircraft shell is an important part of the aircraft. Its main function is to fix the wings, tail, landing gear and other parts to form a whole. At the same time, it is also used to carry personnel (crew members, passengers), cargo, fuel and various equipment. The fuselage structure of modern aircraft is composed of longitudinal elements (along the longitudinal axis of the fuselage) - long stringers, girders and transverse elements perpendicular to the longitudinal axis of the fuselage - bulkheads and skins. Its structural forms include frame type, hard shell type and semi-hard shell type. The main materials of the aircraft shell include aluminum alloy, titanium alloy and composite materials. When using the aircraft shell material, it is necessary to first test the wind resistance of the aircraft shell material. Therefore, a wind force detection device for aircraft shell material is needed to meet people's use needs.

[0003] Wind force detection devices for aircraft shell materials usually simulate the wind pressure intensity at high altitudes by using the intensity of the blower. The blower blows the air directly to the aircraft shell material to be tested, and the deformation effect of the aircraft shell material under different wind pressures is recorded by the recorder to perform the detection. This traditional wind force detection device is not convenient for the operator to position and fix the aircraft shell material, and is also unable to detect the wind pressure resistance data of the aircraft shell material at different angles, thereby affecting the effect of the wind pressure resistance data of the aircraft shell material. Summary of the invention

[0004] The object of the present invention is to provide a wind force detection device for aircraft shell materials to solve the problem that the wind force detection device for aircraft shell materials proposed in the above-mentioned background technology usually simulates the wind pressure intensity at high altitude by using the intensity of the blower, and blows the blower directly to the aircraft shell material to be detected, and records the deformation effect of the aircraft shell material under different wind pressures by recorders to perform detection. This traditional wind force detection device is not convenient for operators to position and fix the aircraft shell materials, and at the same time cannot detect the data of the aircraft shell materials' resistance to wind pressure at different angles, thereby affecting the effect of the data of the aircraft shell materials' resistance to wind pressure.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a wind force detection device for aircraft shell material, comprising a base mechanism, which comprises a workbench, the top of the base mechanism is equipped with a workbench, and the side walls at both ends of the workbench are equipped with mounting plates, the top of the mounting plate is equipped with a fixed plate, and the inside of the fixed plate is rotatably equipped with a rotating rod through a bearing, a blower body is installed at one end of the top of the base mechanism, a display screen body is installed on the side wall of one side of the base mechanism, a single-chip microcomputer is installed on the side wall of one side of the base mechanism, and a PCL controller is installed on the side wall of one side of the base mechanism;

[0006] A positioning and fixing mechanism, comprising a mounting frame and a positioning plate, wherein the mounting frame is mounted at one end of the rotating rod, and a positive and negative screw rod body is rotatably mounted at the top and bottom ends of the mounting frame through bearings, and a threaded sleeve is sleeved on the outer wall of the positive and negative screw rod body, and the outer wall of the threaded sleeve is hinged, and a pressure sensor body is mounted on the side wall of one end of the inner part of the mounting frame;

[0007] A limiting mechanism, comprising a support plate, the support plate being mounted on a side wall of one side of a fixed plate, a first through hole being opened inside the support plate, and a second sliding rod being arranged inside the first through hole, a disc body being mounted on the top end of the second sliding rod, a spring body being sleeved on the outer wall of the second sliding rod, and the top and bottom ends of the spring body being fixedly connected to the disc body and the side wall of the support plate respectively;

[0008] The distance adjustment mechanism comprises a first groove, which is opened at the top of the mounting plate, a mounting block is arranged inside the first groove, and the internal thread of the mounting block is connected with a threaded rod which passes through the side wall of one side of the mounting plate.

[0009] Furthermore, the positioning plate includes a first slide groove, which is opened on the side wall of one end of the positioning plate, a first slider is arranged inside the first slide groove, and one end of the first slider away from the first slide groove is hinged to one end.

[0010] Furthermore, a first sliding rod is installed at the top and bottom ends of the installation frame, and a sliding sleeve is sleeved on the outer wall of the first sliding rod, and the outer wall of the sliding sleeve is fixedly connected to the outer wall of the threaded sleeve.

[0011] Furthermore, a threaded hole is provided inside the threaded sleeve, and the threaded hole is threadedly connected to the forward and reverse screw rod bodies.

[0012] Furthermore, the hinge rod is fixedly mounted on the side wall of the fixed plate, a first clamping block is rotatably mounted on the outer wall of the hinge rod, and the top end of the first clamping block is hinged to the bottom end of the second sliding rod.

[0013] Furthermore, a first ratchet is installed on the outer wall of the rotating rod, and the first ratchet is engaged with the first clamping block.

[0014] Furthermore, the side walls at both ends of the first groove are provided with second slide grooves, and the second slide groove is provided with a second slider inside, and one end of the second slider away from the second slide groove is fixedly connected to the side wall of the mounting block.

[0015] Furthermore, there are two groups of the installation frames of the same structure, and the two groups of installation frames are respectively installed at one end of the rotating rod close to each other, and the interior of the installation frame is provided with a main body of aircraft shell material.

[0016] Furthermore, the output end of the pressure sensor body is electrically connected to the input end of the single-chip microcomputer through a wire, and the output end of the single-chip microcomputer is electrically connected to the input end of the PCL controller through a wire, and the output end of the PCL controller is electrically connected to the input end of the display screen body through a wire.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] (1) This aircraft shell material wind force detection device is arranged by placing the main body of the aircraft shell material inside the installation frame, and rotating the main body of the forward and reverse screw rod, and the main body of the forward and reverse screw rod is threadedly connected with the threaded hole, and the first sliding rod and the sliding sleeve cooperate with each other, so that the main body of the forward and reverse screw rod rotates to drive two groups of threaded sleeves to slide on the outer wall of the main body of the forward and reverse screw rod through the sliding sleeve and the first sliding rod, so that the two groups of threaded sleeves slide to drive the rotation, and at the same time, the first slider cooperates with the first sliding groove to drive the first slider to slide inside the first sliding groove while rotating, so as to drive the positioning plate to position and fix the main body of the aircraft shell material inside the installation frame.

[0019] (2) The wind force detection device for aircraft shell material first drives the installation frame to rotate by rotating the rotating rod, thereby causing the rotating rod to rotate to drive the first ratchet to rotate at the same time, and the first ratchet cooperates with the first clamping block, and the first clamping block is rotatably connected to the hinged rod, so that when the first ratchet rotates clockwise, the first ratchet will not engage with the first clamping block, which is convenient for the rotating rod to rotate clockwise to adjust the angle of the installation frame, and is convenient for the aircraft shell material to detect wind pressure data at different angles. At the same time, the first ratchet engages with the first clamping block to prevent the rotating rod and the first ratchet from rotating counterclockwise.

[0020] (3) This aircraft shell material wind force detection device is threadedly connected to the threaded rod through a mounting block, and through the mutual cooperation of the second slide groove and the second slider, the threaded rod is rotated to drive the mounting block to slide on the outer wall of the threaded rod through the second slider and the second slide groove, so that the mounting block can slide to adjust the distance of the fixing plate, so that the distance between the mounting frames can be adjusted according to the length of the aircraft shell material. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the main structure of the wind force detection device for aircraft shell materials of the present invention;

[0022] Figure 2 This is a schematic diagram of the internal structure of the installation frame of the wind force detection device for aircraft shell materials of the present invention;

[0023] Figure 3 This is a schematic diagram of the installation frame structure of the wind force detection device for aircraft shell materials of the present invention;

[0024] Figure 4 This is a schematic diagram of the angle adjustment structure of the positioning and fixing mechanism of the wind force detection device for aircraft shell materials of the present invention;

[0025] Figure 5 This is a schematic diagram of the support plate structure of the wind force detection device for aircraft shell materials of the present invention;

[0026] Figure 6 The invention is a wind force detection device for aircraft shell material Figure 1 Enlarged structural diagram of point A in the middle

[0027] Figure 7 The figure is a schematic diagram of the circuit structure of the wind force detection device for aircraft shell materials of the present invention.

[0028] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0029] 1. Base mechanism; 101. Workbench; 102. Mounting plate; 103. Fixing plate; 104. Rotating rod; 105. First ratchet; 106. Aircraft shell material body; 107. Blower body; 108. Display screen body; 109. Single chip microcomputer; 1010. PCL controller;

[0030] 2. Positioning and fixing mechanism; 201. Mounting frame; 202. Forward and reverse screw rod body; 203. Threaded sleeve; 2031. Threaded hole; 204. Articulated rod; 205. Positioning plate; 2051. First slide groove; 2052. First slider; 206. First sliding rod; 207. Sliding sleeve; 208. Pressure sensor body;

[0031] 3. Limiting mechanism; 301. Support plate; 302. First through hole; 303. Second sliding rod; 304. Disc body; 305. Spring body; 306. First clamping block; 307. Articulated rod.

[0032] 4. Distance adjustment mechanism; 401. First groove; 402. Mounting block; 403. Threaded rod; 404. Second slide groove; 405. Second slide block. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] Embodiment 1, as Figure 1-7 As shown, it includes a base mechanism 1, which includes a workbench 101, the workbench 101 is installed on the top of the base mechanism 1, and the side walls at both ends of the workbench 101 are installed with mounting plates 102, the top of the mounting plate 102 is installed with a fixing plate 103, and the inside of the fixing plate 103 is rotatably installed with a rotating rod 104 through a bearing, a blower body 107 is installed at one end of the top of the base mechanism 1, a display screen body 108 is installed on the side wall of one side of the base mechanism 1, a single-chip computer 109 is installed on the side wall of one side of the base mechanism 1, and a PCL controller 1010 is installed on the side wall of one side of the base mechanism 1;

[0035] The positioning and fixing mechanism 2 comprises a mounting frame 201 and a positioning plate 205. The mounting frame 201 is mounted at one end of the rotating rod 104. The top and bottom ends of the mounting frame 201 are rotatably mounted with a positive and negative screw rod body 202 through bearings, and the outer wall of the positive and negative screw rod body 202 is sleeved with a threaded sleeve 203, and the outer wall of the threaded sleeve 203 is hinged with 204. A pressure sensor body 208 is mounted on the side wall of one end of the mounting frame 201, and a threaded hole 2031 is opened inside the threaded sleeve 203, and the threaded hole 2031 is threadedly connected with the positive and negative screw rod body 202;

[0036] The top and bottom of the installation frame 201 are both installed with a first sliding rod 206, and the outer wall of the first sliding rod 206 is sleeved with a sliding sleeve 207, and the outer wall of the sliding sleeve 207 is fixedly connected to the outer wall of the threaded sleeve 203. There are two groups of installation frames 201 with the same structure, and the two groups of installation frames 201 are respectively installed at the ends of the rotating rod 104 close to each other, and the interior of the installation frame 201 is provided with an aircraft shell material body 106;

[0037] The positioning plate 205 includes a first slide groove 2051, which is provided on a side wall at one end of the positioning plate 205, and a first slider 2052 is provided inside the first slide groove 2051, and one end of the first slider 2052 away from the first slide groove 2051 is hinged to one end of 204;

[0038] The output end of the pressure sensor body 208 is electrically connected to the input end of the single-chip microcomputer 109 through a wire, and the output end of the single-chip microcomputer 109 is electrically connected to the input end of the PCL controller 1010 through a wire, and the output end of the PCL controller 1010 is electrically connected to the input end of the display screen body 108 through a wire. First, the aircraft shell material body 106 is fixed inside the installation frame 201 and tightly fits with the pressure sensor body 208, and the data of the pressure sensor body 208 is reset to zero. When the blower body 107 is started to simulate the high-altitude wind pressure to blow the aircraft shell material body 106, when the pressure sensor body 208 is subjected to pressure, the information is transmitted to the single-chip microcomputer 109, and the data is analyzed and transmitted to the PCL controller 1010 through the single-chip microcomputer 109, so that the data is displayed on the display screen body 108 through the PCL controller 1010 for observation.

[0039] The specific working principle is as follows: first, the aircraft shell material body 106 is placed inside the installation frame 201, and rotated by rotating the forward and reverse screw rod body 202, and the forward and reverse screw rod body 202 is threadedly connected with the threaded hole 2031, and the first sliding rod 206 and the sliding sleeve 207 cooperate with each other to make the forward and reverse screw rod body 202 rotate to drive the two groups of threaded sleeves 203 to slide on the outer wall of the forward and reverse screw rod body 202 through the sliding sleeve 207 and the first sliding rod 206, so that the two groups of threaded sleeves 203 slide to drive 204 to rotate, and at the same time, the first slider 2052 cooperates with the first slide groove 2051 to make 204 drive the first slider 2052 to slide inside the first slide groove 2051 while rotating, so that 204 drives the positioning plate 205 to position and fix the aircraft shell material body 106 inside the installation frame 201.

[0040] Embodiment 2, as Figure 1 , Figure 4 and Figure 5 As shown, the limiting mechanism 3 includes a support plate 301, which is mounted on the side wall of one side of the fixed plate 103, a first through hole 302 is opened inside the support plate 301, and a second sliding rod 303 is arranged inside the first through hole 302, a disc body 304 is installed on the top of the second sliding rod 303, a spring body 305 is sleeved on the outer wall of the second sliding rod 303, and the top and bottom ends of the spring body 305 are respectively fixedly connected to the disc body 304 and the side wall of the support plate 301, a hinged rod 307 is fixedly mounted on the side wall of the fixed plate 103, a first clamping block 306 is rotatably mounted on the outer wall of the hinged rod 307, and the top end of the first clamping block 306 is hinged to the bottom end of the second sliding rod 303, a first ratchet 105 is installed on the outer wall of the rotating rod 104, and the first ratchet 105 and the first clamping block 306 are engaged with each other.

[0041] The specific working principle is that first, the installation frame 201 is driven to rotate by rotating the rotating rod 104, so that the rotating rod 104 rotates to drive the first ratchet 105 to rotate at the same time, and the first ratchet 105 cooperates with the first clamping block 306, and the first clamping block 306 is rotatably connected with the hinge rod 307, so that when the first ratchet 105 rotates clockwise, the first ratchet 105 will not be engaged with the first clamping block 306, so that the rotating rod 104 can be rotated clockwise to adjust the angle of the installation frame 201, so that the aircraft shell material can detect wind pressure data at different angles, and at the same time, the first ratchet 105 and the first clamping block 306 are engaged with each other to avoid The rotating rod 104 and the first ratchet 105 rotate counterclockwise, and at the same time, the second sliding rod 303 is driven to slide inside the first through hole 302 by pulling the disc body 304 upward, so that the disc body 304 drives the second sliding rod 303 to slide to squeeze the spring body 305 to deform, and at the same time, it is hinged to the bottom end of the second sliding rod 303 through the first clamping block 306, and is rotatably connected to the hinged rod 307 through the first clamping block 306, so that the second sliding rod 303 can be raised and lowered to drive the first clamping block 306 to rotate and no longer engage with the first ratchet 105, so that the operator can rotate the rotating rod 104 to drive the installation frame 201 to rotate at the same time, thereby adjusting the angle of the installation frame 201.

[0042] Embodiment 3, as Figure 1 , Figure 4 and Figure 6 As shown, the distance adjustment mechanism 4 includes a first groove 401, which is opened at the top of the mounting plate 102, and a mounting block 402 is arranged inside the first groove 401. The internal thread of the mounting block 402 is connected with a threaded rod 403 that penetrates the side wall of one side of the mounting plate 102, and the side walls at both ends of the first groove 401 are opened with a second slide groove 404, and the second slide groove 404 is provided with a second slider 405, and the end of the second slider 405 away from the second slide groove 404 is fixedly connected to the side wall of the mounting block 402.

[0043] The specific working principle is that, first, when it is necessary to adjust according to the aircraft shell material of different sizes, the threaded rod 403 is threadedly connected through the mounting block 402, and the second slide groove 404 and the second slider 405 cooperate with each other to make the threaded rod 403 rotate to drive the mounting block 402 to slide on the outer wall of the threaded rod 403 through the second slider 405 and the second slide groove 404, so that the mounting block 402 can slide to adjust the distance of the fixing plate 103, so that the distance between the mounting frames 201 can be adjusted according to the length of the aircraft shell material.

[0044] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, rather than to limit the scope of protection of the present invention. Simple modifications or equivalent substitutions of the technical solution of the present invention by ordinary technicians in this field do not deviate from the essence and scope of the technical solution of the present invention.

Claims

1. A wind force detection device for aircraft shell materials, characterized in that: include A base mechanism (1), comprising a workbench (101), the top of the base mechanism (1) being mounted with the workbench (101), and the side walls at both ends of the workbench (101) being mounted with mounting plates (102), the top of the mounting plate (102) being mounted with a fixing plate (103), and the interior of the fixing plate (103) being rotatably mounted with a rotating rod (104) via a bearing, a blower body (107) being mounted at one end of the top of the base mechanism (1), a display screen body (108) being mounted on the side wall of one side of the base mechanism (1), a single chip computer (109) being mounted on the side wall of one side of the base mechanism (1), and a PCL controller (1010) being mounted on the side wall of one side of the base mechanism (1); A positioning and fixing mechanism (2), comprising a mounting frame (201) and a positioning plate (205), wherein the mounting frame (201) is mounted on one end of a rotating rod (104), and a positive and negative screw rod body (202) is rotatably mounted on the top and bottom ends of the mounting frame (201) via bearings, and a threaded sleeve (203) is sleeved on the outer wall of the positive and negative screw rod body (202), and the outer wall of the threaded sleeve (203) is hinged with (204), and a pressure sensor body (208) is mounted on the side wall of one end of the mounting frame (201); A limiting mechanism (3), comprising a support plate (301), the support plate (301) being mounted on a side wall of a fixed plate (103), a first through hole (302) being provided inside the support plate (301), a second sliding rod (303) being provided inside the first through hole (302), a disc body (304) being mounted on the top end of the second sliding rod (303), a spring body (305) being sleeved on the outer wall of the second sliding rod (303), and the top end and the bottom end of the spring body (305) being fixedly connected to the disc body (304) and the side wall of the support plate (301) respectively; The distance adjustment mechanism (4) comprises a first groove (401), wherein the first groove (401) is opened at the top end of the mounting plate (102), a mounting block (402) is arranged inside the first groove (401), and the internal thread of the mounting block (402) is connected to a threaded rod (403) that passes through a side wall of one side of the mounting plate (102).

2. The wind force detection device for aircraft shell material according to claim 1, characterized in that; The positioning plate (205) includes a first slide groove (2051), which is opened on the side wall of one end of the positioning plate (205), and a first slider (2052) is arranged inside the first slide groove (2051), and one end of the first slider (2052) away from the first slide groove (2051) is hinged to one end of (204).

3. The wind force detection device for aircraft shell material according to claim 1, characterized in that: A first sliding rod (206) is installed at the top and bottom of the installation frame (201), and a sliding sleeve (207) is sleeved on the outer wall of the first sliding rod (206), and the outer wall of the sliding sleeve (207) is fixedly connected to the outer wall of the threaded sleeve (203).

4. The wind force detection device for aircraft shell material according to claim 1, characterized in that: A threaded hole (2031) is provided inside the threaded sleeve (203), and the threaded hole (2031) is threadedly connected to the forward and reverse screw rod body (202).

5. The wind force detection device for aircraft shell material according to claim 1, characterized in that: The hinge rod (307) is fixedly mounted on the side wall of the fixed plate (103), and a first clamping block (306) is rotatably mounted on the outer wall of the hinge rod (307), and the top end of the first clamping block (306) is hinged to the bottom end of the second sliding rod (303).

6. The wind force detection device for aircraft shell material according to claim 1, characterized in that: A first ratchet (105) is installed on the outer wall of the rotating rod (104), and the first ratchet (105) and the first clamping block (306) are engaged with each other.

7. The wind force detection device for aircraft shell material according to claim 1, characterized in that: The side walls at both ends of the first groove (401) are provided with second slide grooves (404), and a second slider (405) is provided inside the second slide groove (404). The end of the second slider (405) away from the second slide groove (404) is fixedly connected to the side wall of the mounting block (402).

8. The wind force detection device for aircraft shell material according to claim 1, characterized in that: There are two groups of the installation frames (201) of the same structure, and the two groups of installation frames (201) are respectively installed at one end of the rotating rod (104) close to each other, and the interior of the installation frame (201) is provided with an aircraft shell material body (106).

9. The wind force detection device for aircraft shell material according to claim 1, characterized in that: The output end of the pressure sensor body (208) is electrically connected to the input end of the single-chip microcomputer (109) via a wire, and the output end of the single-chip microcomputer (109) is electrically connected to the input end of the PCL controller (1010) via a wire, and the output end of the PCL controller (1010) is electrically connected to the input end of the display screen body (108) via a wire.

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