Optical performance detection device for aircraft cockpit glass

Abstract

The invention discloses an optical performance detection device for aircraft cockpit glass. The optical performance detection device comprises a base, a rotating disc, a connecting frame, a turnover frame, a plurality of bow-shaped clamp assemblies, a camera assembly and a target plate. According to the technical scheme, the aircraft cockpit glass is fixed to the turnover frame capable of rotating horizontally and rotating in a pitching mode, the camera simulating the vision of a pilot is fixed to the supporting rod in the middle of the aircraft cockpit glass optical performance detection device, and the cockpit glass is located at different positions by rotating the turnover frame; the method comprises the following steps: taking a picture of a grid optical target plate outside aircraft cabin glass by using a camera, processing a camera image, finding out a grid line with maximum grid bending deformation, and finding out the maximum slope of the curve by using a ruler. And the tangent line is drawn at the tangent point, and the optical distortion value is represented by the maximum slope of the optical distortion value by the number of horizontal (vertical) grids required by the tangent line to cross a complete vertical (horizontal) grid, so that the aim of quantitative inspection is fulfilled. The detection device is simple in structure, convenient to use and high in detection precision.

Description

Technical Field

[0001] The present application relates to the technical field of optical performance testing equipment for aircraft cockpit glass, and in particular to an optical performance testing device for aircraft cockpit glass. Background Art

[0002] As part of the fuselage structure, the aircraft cockpit glass must not only meet the requirements of smooth streamlines of the fuselage shape and airtightness of the cabin, but also provide the necessary field of vision for cabin lighting and cabin occupants. There are corresponding requirements for the optical distortion and optical angle deviation of the aircraft cockpit glass. When the optical distortion of the aircraft cockpit glass is severe, the aircraft will deviate from the runway during landing, posing a flight safety hazard.

[0003] The existing aircraft cockpit glass optical performance inspection device has the following defects: 1. The structure size is large and the operation is inconvenient. 2. The clamping device for fixing the cockpit cover glass is a rigid structure. The cockpit cover glass is easily deformed when fixed on the clamp, causing the curvature of the cockpit cover glass to change, affecting the accuracy of the measurement. 3. The test result is that the inspector observes the deformation of the optical target plate grid through the cockpit cover glass with the naked eye. There is no quantitative test data, and the optical performance of the cockpit glass cannot be accurately measured. Summary of the invention

[0004] The embodiment of the present application provides an aircraft cockpit glass optical property detection device, which can solve the technical problems of inconvenient operation and inaccurate detection of aircraft cockpit glass detection devices in the prior art. The technical solution is as follows:

[0005] An optical property testing device for aircraft cockpit glass, wherein the aircraft cockpit glass is an arcuate thin-walled member, and the two downward ends of the arcuate thin-walled member are flush, and the optical property testing device for aircraft cockpit glass comprises:

[0006] A base having a plurality of rollers arranged on the upper surface of the base, the rotating shaft of each roller is parallel to the radial direction of the turntable, and a vertical rotating shaft is arranged at the center of the base; a turntable, the center of the turntable has a first shaft hole, the turntable is sleeved on the base through the first shaft hole, and the lower surface of the base is in contact with the plurality of rollers; a connecting frame comprising a bottom ring and two columns vertically connected to the upper surface of the bottom ring; the bottom ring is fixedly connected to the turntable, and the upper ends of the two columns are each provided with a first hinge hole; a flip frame having two parallel fixing rods, each fixing rod having a first hinge hole on it. It has a horizontal ear axis, two ear axes are collinear, and the flip frame is hinged on the two columns through the two ear axes inserted into the first hinge holes; a plurality of bow-shaped clamp assemblies are respectively arranged on the two fixing rods; the bow-shaped clamp assemblies are used to clamp the aircraft cabin glass to be tested; a camera assembly includes a support rod and a camera arranged at the top of the support rod; the camera is located between the flip frame and the aircraft cabin glass to be tested; and a target plate, the target plate is arranged outside the aircraft cabin glass to be tested and in front of the camera.

[0007] Optionally, the fixing rod is provided with a hinge axis parallel to the length direction of the fixing rod; the bow clamp assembly includes a C-shaped clamp body, the C-shaped clamp body is provided with a second hinge hole, the C-shaped clamp body is hinged to the fixing rod, the C-shaped clamp body has two clamp arms, one of the clamp arms is provided with a first screw hole, and a first handle screw is screwed into the first screw hole.

[0008] Optionally, two bow-shaped clamp assemblies are provided on each of the fixing rods, wherein the second hinge holes of the C-shaped clamp bodies of the two bow-shaped clamp assemblies on one of the fixing rods are round holes, and the second hinge holes of the two bow-shaped clamp assemblies on the other fixing rod are waist-shaped holes, and the length direction of the waist-shaped holes is perpendicular to the length direction of the fixing rods.

[0009] Optionally, the flip frame has a positioning block, the positioning block is located on the fixing rod, and the upper surface of the positioning rod is a plane.

[0010] Optionally, the aircraft cabin glass optical property detection device also includes a pitch angle control reduction mechanism, the pitch angle control reduction mechanism includes a reducer, the reducer is fixedly connected to one of the columns, the input shaft of the reducer is connected to a hand wheel, and the output shaft of the reducer is connected to the ear shaft.

[0011] Optionally, the pitch angle control reduction mechanism further includes an angle disc and a pointer, wherein the angle disc is fixedly connected to the column, and the pointer is connected to the other end of the reducer output shaft.

[0012] Optionally, the aircraft cabin glass optical property detection device also includes a horizontal rotation locking device, which includes a C-shaped clamp, the C-shaped clamp has a vertical second axial hole, the C-shaped clamp has two arms, and the two arms are respectively provided with second screw holes, and a second handle bolt is provided in one of the second screw holes.

[0013] Optionally, the support rod is a retractable support rod.

[0014] Optionally, a plurality of locking universal wheels are provided on the lower surface of the base.

[0015] Optionally, the target plate has a mesh grid.

[0016] The beneficial effects brought by the technical solution provided by the embodiment of the present application include at least:

[0017] An optical performance testing device for aircraft cockpit glass includes: a base, a turntable, a connecting frame, a flip frame, a plurality of bow-shaped clamp assemblies, a camera assembly and a target plate. In the technical solution of the present application, the aircraft cockpit glass is fixed on a flip frame that can rotate horizontally and pitch, a camera simulating the pilot's vision is fixed on a supporting rod in the middle of the aircraft cockpit glass optical performance testing device, the flip frame is rotated to make the cockpit glass in different positions, the camera is used to take pictures of the square optical target plate outside the aircraft cockpit glass, the camera image is processed, the grid line with the largest bending deformation of the grid is found, and the maximum slope of the curve is found using a ruler (software). The tangent is drawn at the tangent point, and the optical distortion value is represented by the maximum slope and the number of horizontal (vertical) grids required for the tangent to cross a complete vertical (horizontal) grid, so as to achieve the purpose of quantitative inspection. The optical performance testing device for aircraft cockpit glass has a simple structure, is easy to use, and has high detection accuracy.

[0018] Other features and advantages of the present disclosure will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 It is a three-dimensional schematic diagram of the aircraft cockpit glass;

[0021] Figure 2 Schematic diagram of the principle of the optical performance testing device for aircraft cockpit glass of the present application;

[0022] Figure 3 is a three-dimensional schematic diagram of an aircraft cockpit glass optical property detection device provided in an embodiment of the present application;

[0023] Figure 4 is a side view of an aircraft cockpit glass optical property detection device provided in an embodiment of the present application;

[0024] Figure 5 yes Figure 3 Top view of the center turntable;

[0025] Figure 6 yes Figure 3 A three-dimensional schematic diagram of the middle connecting frame;

[0026] Figure 7 It is a side view of a flip frame provided by an embodiment of the present application;

[0027] Figure 8 is a top view of a flip frame provided by an embodiment of the present application;

[0028] Fig. 9 yes Figure 8 A directional view of the bow clamp assembly at AA in the middle;

[0029] Fig.10 yes Figure 8 A directional view of the bow clamp assembly at the middle BB;

[0030] Fig.11 is a three-dimensional schematic diagram of a reducer provided in an embodiment of the present application;

[0031] Fig.12 It is a front view of the connecting frame and the pitch angle control speed reduction mechanism provided in the embodiment of the present application;

[0032] Fig.13 is a partial top view of an aircraft cabin glass inspection device provided by an embodiment of the present application;

[0033] Fig.14 yes Fig.13 View from CC in the middle.

[0034] Description of Reference Numerals

[0035] 1-base; 101-roller; 102-locked universal wheel; 2-turntable; 201-first axial hole; 3-connecting frame; 301-bottom ring; 302-column; 303-first hinge hole; 4-turn frame; 401-fixed rod; 402-ear shaft; 403-positioning block; 5-bow clamp assembly; 501-C-shaped clamp body; 502-second hinge hole; 503-clamp arm; 504-first handle screw; 6-camera assembly; 601-support rod; 602-camera; 7-target plate; 8-pitch angle control speed reduction mechanism; 801-speed reducer; 802-input shaft; 803-handwheel; 804-output shaft; 805-angle disk; 806-pointer; 9-horizontal rotation locking device; 901-C-shaped clamp; 902-arm; 903-second handle bolt; 10-aircraft cockpit glass. DETAILED DESCRIPTION

[0036] The specific implementation of the present disclosure is described in detail below in conjunction with the accompanying drawings. It should be understood that the specific implementation described herein is only used to illustrate and explain the present disclosure, and is not used to limit the present disclosure.

[0037] In the present disclosure, unless otherwise stated, directional words such as "upper" and "lower" generally refer to the "upper" and "lower" of the corresponding parts in the use state relative to the direction of gravity, and "inside" and "outside" refer to the "inside" and "outside" relative to the corresponding parts' own contours. In addition, the terms "first", "second", etc. used in the present disclosure are to distinguish one element from another and do not have order and importance. In the following description, when referring to the drawings, unless otherwise explained, the same figure numbers in different drawings represent the same or similar elements.

[0038] refer to Figure 1 As shown, the aircraft cabin glass 10 is an arcuate thin-walled member, and the two downward ends of the arcuate thin-walled member are flush.

[0039] As a part of the aircraft structure, the aircraft cockpit glass 10 not only meets the requirements of smooth streamline of the aircraft body shape and airtightness of the cabin, but also needs to provide necessary vision for the aircraft cabin lighting and the cabin occupants. There are corresponding requirements for the optical distortion and optical angle deviation of the aircraft cockpit glass 10. When the optical distortion of the aircraft cockpit glass 10 is relatively serious, the aircraft will deviate from the runway during landing, causing a flight safety hazard.

[0040] The existing cockpit glass optical performance inspection device has the following defects:

[0041] 1. The structure is large and inconvenient to operate. 2. The clamping device for fixing the aircraft cockpit glass is a rigid structure. The aircraft cockpit glass is easily deformed when fixed on the clamp, which changes the curvature of the aircraft cockpit glass and affects the accuracy of the measurement. 3. The test results are the inspector's naked eyes through the cockpit cover glass to observe the deformation of the optical target plate grid. There is no quantitative test data, and the optical properties of the aircraft cockpit glass cannot be accurately measured.

[0042] According to an embodiment of the present application, referring to Figures 2 to 8 , provides an aircraft cockpit glass optical performance testing device, the aircraft cockpit glass optical performance testing device includes: a base 1, a turntable 2, a connecting frame 3, a flip frame 4, a plurality of bow clamp assemblies 5, a camera assembly 6, and a target plate 7.

[0043] Among them, reference Figure 3 and Figure 4 The base 1 has a plurality of rollers 101 disposed on the upper surface of the base 1, the rotation axis of each roller 101 is parallel to the radial direction of the turntable 2, and a vertical rotation axis is disposed at the center of the base 1; Figure 5 The center of the turntable 2 has a first axial hole 201, and the turntable 2 is sleeved on the base 1 through the first axial hole 201, and the lower surface of the base 1 is in contact with multiple rollers 101; in this way, the turntable 2 can rotate in a horizontal plane relative to the base 1.

[0044] refer to Figure 6 The connecting frame 3 includes a bottom ring 301 and two upright posts 302 vertically connected to the upper surface of the bottom ring 301; the bottom ring 301 is fixedly connected to the turntable 2, and the upper ends of the two upright posts 302 are each provided with a first hinge hole 303; Figure 7 and Figure 8 The flip frame 4 has two parallel fixing rods 401, each fixing rod 401 has a horizontal ear shaft 402, and the two ear shafts 402 are collinear. The flip frame 4 is hinged on the two columns 302 through the two ear shafts 402 inserted into the first hinge holes 303; a plurality of bow-shaped clamp assemblies 5 are respectively arranged on the two fixing rods 401; the bow-shaped clamp assemblies 5 are used to clamp the aircraft cabin glass 10 to be inspected. Figure 3 and Figure 4 The camera assembly 6 includes a support rod 601 and a camera 602 arranged at the top of the support rod 601; the camera 602 is located between the flip frame 4 and the aircraft cabin glass 10 to be inspected; the target plate 7 is arranged outside the aircraft cabin glass 10 to be inspected and in front of the camera 602.

[0045] In the above embodiment, when the aircraft cockpit glass 10 needs to be inspected, the aircraft cockpit glass 10 is fixed to the flip frame 4 through a plurality of bow-shaped clamp assemblies 5. Since the turntable 2 has a first axial hole (201), the upper surface of the base 1 has a plurality of rollers 101, and the connecting frame 3 is fixedly connected to the turntable 2. In this way, by turning the connecting frame 3, the flip frame 4 connected to the connecting frame 3 can be driven to rotate horizontally. Since the flip frame 4 is hinged to the column 302 of the connecting frame 3 through two ear shafts 402, the flip frame 4 can achieve a pitching motion in a vertical plane, thereby achieving a pitching motion of the aircraft cockpit glass 10. The camera assembly 6 is arranged in the space between the flip frame 4 and the aircraft cockpit glass 10. The camera 602 can take photos of the aircraft cockpit glass 10 at various angles such as the horizontal direction and the vertical direction. By comparing the target plate photos taken by the camera 602 with the actual target plate 7, the optical performance of the aircraft cockpit glass 10 can be judged. In the technical solution of the present application, the aircraft cockpit glass 10 is fixed on a flip frame 4 that can rotate horizontally and pitch, and a camera 602 that simulates the pilot's vision is fixed on a support rod 601 in the middle of the aircraft cockpit glass optical performance detection device. The flip frame 4 is rotated to make the cockpit glass in different positions, and the camera 602 is used to take pictures of the square optical target plate 7 outside the aircraft cockpit glass 10, and the camera image is processed to find the grid line with the largest bending deformation of the grid, and the maximum slope of the curve is found using a ruler (software). Draw its tangent at the tangent point, and its optical distortion value is represented by its maximum slope and the number of horizontal (vertical) grids required for the tangent to cross a complete vertical (horizontal) grid, so as to achieve the purpose of quantitative inspection. The aircraft cockpit glass optical performance detection device has a simple structure, is easy to use, and has high detection accuracy.

[0046] In the examples of this application, reference is made to Figures 8 to 10 The fixing rod 401 is provided with a hinge axis parallel to the length direction of the fixing rod 401; the bow-shaped clamp assembly 5 includes a C-shaped clamp body 501, the C-shaped clamp body 501 is provided with a second hinge hole 502, the C-shaped clamp body 501 is hinged on the fixing rod 401, and the C-shaped clamp body 501 has two clamp arms 503, one of the clamp arms 503 is provided with a first screw hole, and a first handle screw 504 is screwed in the first screw hole. In this way, the aircraft cockpit glass 10 can be quickly clamped.

[0047] Since the deformation of the aircraft cockpit glass 10 may affect the optical properties of the aircraft cockpit glass 10, that is, if the aircraft cockpit glass 10 is under compression deformation, its optical properties cannot be truly reflected. In order to prevent the aircraft cockpit glass 10 from being compressed in a direction perpendicular to the two fixing rods 401, refer to Figure 8 and Fig. 9Two bow-shaped clamp assemblies 5 are disposed on each fixing rod 401 , and the second hinge holes 502 of the C-shaped clamp bodies 501 of the two bow-shaped clamp assemblies 5 on one fixing rod 401 are round holes.

[0048] refer to Figure 8 and Fig.10 , the second hinge holes 502 of the two arch-shaped clamp assemblies 5 on the other fixing rod 401 are waist-shaped holes, and the length direction of the waist-shaped holes is perpendicular to the length direction of the fixing rod 401. In this way, when the aircraft cockpit glass 10 is clamped on the flip frame 4, since the second hinge holes 502 of the two arch-shaped clamps on the fixing rod 401 on one side are waist-shaped holes, the aircraft cockpit glass 10 can drive the arch-shaped clamps with waist-shaped second hinge holes 502 to move adaptively, so that the aircraft cockpit glass 10 is not subjected to pressure in the direction perpendicular to the two fixing rods 401, thereby ensuring that the optical performance of the aircraft cockpit glass 10 tested is more accurate and true.

[0049] In the examples of this application, reference is made to Figure 7 The flip frame 4 has a positioning block 403, which is located on the fixing rod 401, and the upper surface of the positioning rod is a plane. In this way, during installation, the lower side of the aircraft cabin glass 10 can be reliably contacted with the upper surface of the fixing rod 401, and one end of the aircraft cabin glass 10 is fitted with the positioning block 403, thereby achieving accurate positioning of the aircraft cabin glass 10.

[0050] In the examples of this application, reference is made to Figure 3 , Figure 6 , Fig.11 and Fig.12 The aircraft cockpit glass optical property detection device further includes a pitch angle control speed reduction mechanism 8, which may include a speed reducer 801, which is fixedly connected to one of the columns 302, an input shaft 802 of the speed reducer 801 is connected to a hand wheel 803, and an output shaft 804 of the speed reducer 801 is connected to the ear shaft 402. The speed reducer 801 can reduce the rotation speed of the hand wheel 803, thereby realizing precise control of the pitch angle of the flip frame 4.

[0051] In order to facilitate the staff to adjust the angle between the flip frame 4 and the horizontal plane, and to facilitate the staff to record the pitch angle, refer to Fig.12 The pitch angle control reduction mechanism 8 may further include an angle disc 805 and a pointer 806 . The angle disc 805 is fixedly connected to the column 302 , and the pointer 806 is connected to the other end of the output shaft 804 of the reducer 801 . The angle disc 805 is provided with a scale.

[0052] In the examples of this application, reference is made to Figure 3 , Fig.13 and Fig.14The pitch angle control reducer 801 structure 8 may also include a horizontal rotation locking device 9, which includes a C-shaped clamp 901, the C-shaped clamp 901 has a vertical second shaft hole, and the C-shaped clamp 901 has two arms 902, and the two arms 902 are respectively provided with second screw holes, and one of the second screw holes is provided with a second handle bolt 903. The horizontal rotation locking device 9 can lock or unlock the horizontal angle of rotation of the aircraft cabin glass 10, so that it is convenient for the staff to take pictures in this fixed state.

[0053] In the examples of this application, reference is made to Figure 3 , the support rod 601 is a retractable support rod 601. Since the aircraft cockpit glass optical performance detection device of the present application simulates the pilot's perspective for optical performance detection, thus, the support rod 601 is set to be retractable, which can simulate the optical performance of the aircraft cockpit glass 10 from the perspective of pilots of different heights, so that the staff can conduct research on the correlation between the optical performance of the aircraft cockpit glass 10 and the pilot's height.

[0054] In the examples of this application, reference is made to Figure 3 In order to facilitate the staff to move the aircraft cabin glass optical performance testing device, a plurality of locking universal wheels 102 are provided on the lower surface of the base 1.

[0055] In the examples of this application, reference is made to Figure 2 , there are meshed squares on the target plate 7. By comparing the square photo taken by the camera 602 with the actual squares on the target plate 7, the optical performance of the aircraft cockpit glass 10 can be obtained.

[0056] In the embodiment of the present application, the technical solution of the present application is to fix the aircraft cockpit glass 10 on a flip frame 4 that can rotate horizontally and pitch, fix a camera 602 that simulates the pilot's vision on a support rod 601 in the middle of the aircraft cockpit glass optical performance detection device, rotate the flip frame 4 to make the cockpit glass in different positions, use the camera 602 to take pictures of the square optical target plate 7 outside the aircraft cockpit glass 10, process the camera 602 image, find out the grid line with the largest bending deformation of the grid, and use a ruler (software) to find the maximum slope of the curve. Draw its tangent at the tangent point, and its optical distortion value is represented by its maximum slope and the number of horizontal (vertical) grids required for the tangent to cross a complete vertical (horizontal) grid, so as to achieve the purpose of quantitative inspection. The aircraft cockpit glass optical performance detection device has a simple structure, is easy to use, and has high detection accuracy.

[0057] The following are the actual operating steps of the optical performance testing device for aircraft cockpit glass of this application:

[0058] 1. Adjust the flip frame 4 to a horizontal position, place the aircraft cockpit glass 10 on the fixing rod 401 of the flip frame 4, and make one end of the aircraft cockpit glass 10 fit with the positioning block 403 on the flip frame 4.

[0059] 2. Use two bow-shaped clamp assemblies 5 with circular second hinge holes 502 on the flip frame 4 to clamp one side of the cockpit glass; use the other bow-shaped clamp assembly 5 with waist-shaped second hinge holes 502 on the other side to clamp the other side of the cockpit glass, and fix the cockpit glass on the flip frame 4, so that the aircraft cockpit glass 10 remains fixed during horizontal and pitch rotation.

[0060] 3. Adjust the support rod 601 of the camera 602 to a specified height so that the camera 602 is aligned with the pilot's visual position and the camera 602 is aligned with the optical target plate 7.

[0061] 4. Adjust the aircraft cabin glass 10 to different angles in the horizontal direction and the pitch direction, and use the camera 602 to take pictures of the grid optical target plate 7.

[0062] 5. Process the camera image, find the grid line with the largest square bending deformation, and use a ruler (software) to find the maximum slope of the curve. Draw the tangent line at the tangent point, and the optical distortion value is represented by the number of horizontal (vertical) grids required for the tangent line to cross a complete vertical (horizontal) grid, so as to achieve the purpose of optical performance inspection of aircraft cockpit glass.

[0063] The preferred embodiments of the present disclosure are described in detail above in conjunction with the accompanying drawings; however, the present disclosure is not limited to the specific details in the above embodiments. Within the technical concept of the present disclosure, a variety of simple modifications can be made to the technical solution of the present disclosure, and these simple modifications all fall within the protection scope of the present disclosure.

[0064] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, the present disclosure will not further describe various possible combinations.

[0065] In addition, various embodiments of the present disclosure may be arbitrarily combined, and as long as they do not violate the concept of the present disclosure, they should also be regarded as the contents disclosed by the present disclosure.

Claims

1. A device for testing the optical properties of aircraft cabin glass, wherein the aircraft cabin glass (10) is an arcuate thin-walled member, and the two downward ends of the arcuate thin-walled member are flush, characterized in that: The aircraft cockpit glass optical performance detection device comprises: A base (1) having a plurality of rollers (101) arranged on the upper surface of the base (1), the rotation axis of each roller (101) being parallel to the radial direction of the turntable (2), and a vertical rotation axis being arranged at the center of the base (1); A turntable (2), wherein the center of the turntable (2) has a first axial hole (201), the turntable (2) is sleeved on the base (1) through the first axial hole (201), and the lower surface of the base (1) is in contact with the plurality of rollers (101); The connecting frame (3) comprises a bottom ring (301) and two upright posts (302) vertically connected to the upper surface of the bottom ring (301); the bottom ring (301) is fixedly connected to the rotating disk (2), and the upper ends of the two upright posts (302) are both provided with first hinge holes (303); The turning frame (4) has two parallel fixing rods (401), each fixing rod (401) has a horizontal ear shaft (402), the two ear shafts (402) are collinear, and the turning frame (4) is hinged on the two upright posts (302) by inserting the two ear shafts (402) into the first hinge holes (303); A plurality of bow-shaped clamp assemblies (5) are respectively arranged on the two fixing rods (401); the bow-shaped clamp assemblies (5) are used to clamp the aircraft cabin glass (10) to be inspected; A camera assembly (6) comprises a support rod (601) and a camera (602) arranged at the top of the support rod (601); the camera (602) is located between the flip frame (4) and the aircraft cabin glass (10) to be inspected; and a target plate (7), wherein the target plate (7) is arranged outside the aircraft cockpit glass (10) to be inspected and in front of the camera (602).

2. The aircraft cabin glass optical performance detection device according to claim 1, characterized in that: The fixing rod (401) is provided with a hinge axis parallel to the length direction of the fixing rod (401); The bow-shaped clamp assembly (5) comprises a C-shaped clamp body (501), the C-shaped clamp body (501) is provided with a second hinge hole (502), the C-shaped clamp body (501) is hinged on the fixing rod (401), the C-shaped clamp body (501) has two clamp arms (503), one of the clamp arms (503) is provided with a first screw hole, and a first handle screw rod (504) is screwed into the first screw hole.

3. The optical performance testing device for aircraft cabin glass according to claim 2, characterized in that: Two bow-shaped clamp assemblies (5) are arranged on each of the fixing rods (401), wherein the second hinge holes (502) of the C-shaped clamp bodies (501) of the two bow-shaped clamp assemblies (5) on one of the fixing rods (401) are round holes, and the second hinge holes (502) of the two bow-shaped clamp assemblies (5) on the other fixing rod (401) are waist-shaped holes, and the length direction of the waist-shaped holes is perpendicular to the length direction of the fixing rod (401).

4. The aircraft cabin glass optical performance detection device according to claim 1, characterized in that: The turning frame (4) has a positioning block (403), the positioning block (403) is located on the fixing rod (401), and the upper surface of the positioning rod is a plane.

5. The aircraft cockpit glass optical performance detection device according to claim 1, characterized in that: The aircraft cockpit glass optical property detection device further comprises a pitch angle control speed reduction mechanism (8), wherein the pitch angle control speed reduction mechanism (8) comprises a speed reducer (801), wherein the speed reducer (801) is fixedly connected to one of the columns (302), wherein an input shaft (802) of the speed reducer (801) is connected to a hand wheel (803), and an output shaft (804) of the speed reducer (801) is connected to the ear shaft (402).

6. The aircraft cockpit glass optical performance detection device according to claim 5, characterized in that: The pitch angle control speed reduction mechanism (8) further comprises an angle disc (805) and a pointer (806), wherein the angle disc (805) is fixedly connected to the column (302), and the pointer (806) is connected to the other end of the output shaft (804) of the speed reducer (801).

7. The aircraft cabin glass optical performance testing device according to claim 1, characterized in that: The aircraft cabin glass optical property detection device also includes a horizontal rotation locking device (9), the horizontal rotation locking device (9) includes a C-shaped clamp (901), the C-shaped clamp (901) has a vertical second axial hole, the clamp has two arms (902), the two arms (902) are respectively provided with second screw holes, and a second handle bolt (903) is provided in one of the second screw holes.

8. The aircraft cabin glass optical performance testing device according to claim 1, characterized in that: The support rod (601) is a retractable support rod (601).

9. The aircraft cabin glass optical performance testing device according to claim 1, characterized in that: The lower surface of the base (1) is provided with a plurality of universal wheels (102) with locks.

10. The aircraft cabin glass optical performance detection device according to claim 1, characterized in that: The target plate (7) has mesh-like grids.

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