Method for checking installation size of airborne device of airplane

Abstract

The invention belongs to the aeronautical manufacturing industry, and relates to a method for checking the installation size of an airborne device of an airplane. The device can be freely switched between a manual measurement mode and an automatic measurement mode, automatic measurement can be carried out according to a set path in the automatic measurement mode, and the device is suitable for multi-rack repeated inspection work. In order to reduce the interference of human factors on measurement data and the judgment of measurement results, the measurement method adopts a 10-bit ADC (Analog to Digital Converter) singlechip chip, and automatically judges the correctness of the size through a program. In the process of checking the installation size of the airborne device of the airplane, an inspector implements the checking method and adopts the special measuring tool in the implementation process, so that the situation that unqualified products flow into the next stage for assembly due to the fact that the installation size of the airborne device of the airplane is wrong or the measurement is inaccurate is effectively avoided; and the time for processing and removing faults due to quality problems is reduced, the product delivery cycle is shortened, especially the inspection working time is shortened by more than 65%, and the product quality stability is ensured.

Description

Technical Field

[0001] The invention belongs to the aviation manufacturing industry and relates to a method for checking the installation dimensions of an aircraft onboard device. Background Art

[0002] In the field of aviation manufacturing, aircraft assembly is an important production stage. The so-called aircraft assembly is the process of combining and connecting a large number of aircraft structural parts, components, airborne devices and standard parts according to the requirements of drawings, digital models and technical conditions, following a certain method and sequence, and gradually forming a higher level of assembly parts or complete machines. As an important link in the aircraft development process, it has the characteristics of involving a wide range of technologies, covering a lot of content, and high technical difficulty. Compared with the assembly of general mechanical products, the labor of aircraft assembly accounts for about 30%-45% of the total labor (general mechanical products account for about 20%), and aircraft assembly accounts for more than 40% of the entire aircraft manufacturing cycle.

[0003] Aircraft onboard devices are important components of aircraft, and are key components of aircraft automatic control and integration. They play an important role in aircraft systems. The correctness of aircraft onboard device installation directly affects the stability of aircraft product quality, and is an important embodiment of ensuring the long-term safe use of aircraft in high-strength, high-load, and complex environments. Limited by unfavorable factors such as the small internal space and complex structure of the aircraft, the installation size inspection of aircraft onboard devices is mainly based on manual operation. In practice, there are two main commonly used measurement methods, namely quantitative inspection method and qualitative inspection method. When using the quantitative inspection method, it is generally based on the product drawing to mark the size or digital model to measure the size, use general measuring tools (such as rulers, tape measures, vernier calipers, etc.), measure the actual installation size of the aircraft onboard device at the corresponding position, compare the theoretical size with the actual measured size, and combine the tolerance to manually judge the correctness of the installation size of the onboard device. When using the qualitative inspection method, it is generally based on the use of special measuring tools (such as onboard device tooling, onboard device templates and special gauges, etc.), fix the special measuring tools according to the use requirements, and use them to qualitatively judge the correctness of the actual installation of the aircraft onboard device. The above two methods for measuring the installation dimensions of aircraft onboard devices have defects such as poor measurement accuracy, low measurement efficiency, and great influence from human factors, and cannot meet the needs of spatial position measurement. In particular, the qualitative inspection method requires additional design and manufacture of special measurement tools, which have poor versatility, high cost, and long production cycle.

[0004] Therefore, a measurement method is needed to quickly determine the correctness of the installation dimensions of aircraft-mounted devices, realize the digitization of measurement results, and automate the measurement process. Summary of the invention

[0005] In order to meet the requirements of quickly judging the correctness of the installation dimensions of aircraft onboard devices and realize automation and digitization, a method for checking the installation dimensions of aircraft onboard devices was invented. This method uses the axiom of solid geometry to judge the installation dimensions of aircraft onboard devices, and a set of special measuring tools was developed. During the implementation of the inspection method, the special measuring tools were calibrated using the principle of light reflection. This inspection method and special measuring tools can measure the installation dimensions of aircraft internal and external onboard devices and judge the correctness of the installation dimensions of aircraft onboard devices.

[0006] The technical solution of the present invention is as follows:

[0007] In view of the appearance characteristics of the aircraft onboard device surface, which is mostly composed of six planes, the basic method of the present invention is to determine the correctness of its installation position by measuring the spatial position of a plane of the aircraft onboard device. The specific method is to use the solid geometry axiom of determining a plane using three points that are not on the same straight line, as shown in the attached figure. Figure 1 As shown in the figure, a laser rangefinder is used to measure three measuring points on a plane of the airborne device. The principle of selecting the measuring points is the intersection of the outer contour line of the aircraft airborne device with an equidistant distance of 1-2.5 mm inward, as shown in the figure. Figure 2 As shown. Finally, the circuit system can be judged and the circuit system can set the tolerance. If the dimensions of the three measuring points from the reference plane and the dimensions given in the product drawing meet the requirements at the same time, it is judged to be qualified, otherwise it is judged to be unqualified, and then the correctness of the installation position of the aircraft onboard device is judged.

[0008] A method for checking the installation dimensions of an aircraft onboard device, the steps are as follows:

[0009] Step 1: Determine the measurement datum. Open the product drawing and select the measurement datum. The measurement datum usually includes the aircraft bulkhead axis plane, aircraft horizontal datum plane, aircraft symmetry axis plane, and aircraft matching finishing surface.

[0010] Step 2: Select the measurement points of each aircraft airborne device to be tested. Generally, the measurement points are three points on the same surface of the aircraft airborne device, and the three points are not on the same straight line. If the aircraft airborne device has a complex structure, or the area is small, resulting in a short distance between the three points, or there is an obstruction between the airborne devices, the number of measurement points can be increased to measure multiple surfaces.

[0011] Step 3: Measure and record the dimensions from the measuring point to the measuring reference on the product drawing.

[0012] Step 4: Measurement path setting. Use the computer simulation module to plan the measurement path and perform simulation to simulate the measurement process to avoid blocking or exceeding the measurement range. The measurement path should take into account the installation error of the aircraft onboard device. Aircraft onboard devices with the same error are grouped together for group measurement.

[0013] Step 5: Fix the assembly with the onboard device of the aircraft under test and the measuring device to make them stable and ensure that the relative positions of the two are fixed.

[0014] Step 6: Turn on the measuring device and set the running track of the measuring device according to the planned route.

[0015] Step 7: Use the measuring device to measure the data of the measuring points on the onboard device of the aircraft to be tested.

[0016] Step 8: Compare data and draw conclusions.

[0017] A method for checking the installation dimensions of an aircraft onboard device uses a special measuring tool during implementation, and the special measuring tool includes a measuring instrument and a controller.

[0018] Measuring instrument as attached Figure 3 , Figure 4 and Figure 5 As shown, it includes a longitudinal drive motor, a longitudinal bracket, a longitudinal lead screw, a longitudinal slider, a transverse slider, a transverse lead screw, a transverse drive motor, a laser ranging probe, a fixed base, a light-transmitting plate bracket, a transverse bracket, a light-transmitting plate, a calibration laser transmitter and a correction target plate.

[0019] The measuring instrument is a special measuring tool actuator. Among them, the fixed base is the support and measurement reference of the measuring instrument. One surface is connected to the longitudinal bracket and the light-transmitting plate bracket by bolts, and the other surface is connected to the auxiliary bracket by bolts. The calibration laser transmitter is connected to the longitudinal bracket by screws, and is used in conjunction with the light-transmitting plate and the correction target plate. It uses the principle of light reflection to calibrate the position of the measuring instrument before measurement. The center of the light-transmitting plate is engraved with a bull's eye with a diameter of Φ5. The correction target plate is made of metal with a smooth surface and can fully reflect the light beam. The longitudinal lead screw and the transverse lead screw are respectively installed in the longitudinal bracket and the transverse bracket, and the connection is connected in the form of bearings. The longitudinal drive motor and the transverse drive motor are respectively connected to the outside of the longitudinal bracket and the transverse bracket by bolts. They rotate according to the electrical signal transmitted from the controller part, drive the lead screw to rotate, and drive the longitudinal slider and the transverse slider to move respectively. The laser ranging probe is installed on the transverse slider, which is used to measure the distance by emitting and capturing lasers, and feedback to the controller in real time.

[0020] Controller as attached Figure 6 , Figure 7 and Figure 8 As shown, it includes a transmission line, a shell, an upper cover, a touch display screen, self-tapping screws, a confirmation button, a joystick, a measurement result indicator light, a charging socket, a power switch, a working indicator light, a data input / output socket, a calibration laser emission switch, a mode selection button, a reset button, a path planning button, a battery module, a main control board, a data storage module, a control sensor, a speaker and a charging module.

[0021] The controller is a special measuring tool control mechanism. Among them, the shell and the upper cover are the main supporting components of the controller part. They are made of PLA material by 3D printing and are tightened and fixed by 4 self-tapping screws. According to the structural requirements, the shell reserves space for the battery module, main control board, data storage module, control sensor, speaker and charging module, and reserves openings for the charging socket, power switch, working indicator light and data input / output socket. The upper cover reserves openings for the touch screen, joystick, measurement result indicator light, calibration laser emission switch, mode selection button, reset button and path planning button. The battery module uses a DC 3.7V lithium battery, which is boosted to 5V by a boost module to drive the longitudinal drive motor and the lateral drive motor, and at the same time power the laser ranging probe, calibration laser emitter, touch screen, measurement result indicator light, working indicator light and main control board; one end of the charging module is connected to the battery module, and the other end is connected to the charging socket, and the battery can be charged by connecting a data cable.

[0022] When working, the laser rangefinder transmits the measurement data to the main control board; to judge the correctness of the data, the measurement result indicator light has two colors, green and red. When the data exceeds the preset limit value, it lights up red, otherwise it lights up green; the speaker can issue voice prompts such as "qualified", "unqualified", "mode 1", "mode 2", etc., and the touch screen displays relevant content. The mode selection button is used to switch the measurement mode. This special measurement tool presets two measurement modes, namely manual measurement mode and automatic measurement mode. The system defaults to manual measurement mode, and measurement modes can be added later as needed. Among them, before the automatic measurement mode, the path planning button needs to be used to preset the measurement path. Theoretical data can be imported through the data input / output socket, or manually entered through the touch screen, and the data information is stored in the data storage module. The reset button is used for calibration before measurement.

[0023] A method for checking the installation dimensions of an aircraft airborne device uses an auxiliary bracket during implementation. The schematic diagram of the auxiliary bracket structure is shown in the attached figure. Fig. 9 As shown, the auxiliary bracket includes a platform, an outer sleeve, a latch, an inner sleeve, a chassis, a retractable component and a roller component.

[0024] An opening is set on the platform for connecting the measuring instrument. A pin hole is opened on the outer sleeve, and a plurality of equidistant pin holes are opened on the inner sleeve. The outer sleeve is sleeved on the outside of the inner sleeve. The outer sleeve and the inner sleeve can be telescopically adjusted in length. The pins are inserted into the openings of the outer sleeve and the inner sleeve to fix the length of the sleeve. The chassis is made of solid metal to ensure the stability of the auxiliary bracket. The upper part is connected to the inner sleeve, and the lower part is connected to three groups of telescopic components. The main body of the telescopic component is a threaded structure, and the height can be adjusted separately by rotating the thread to adjust the platform posture; the lower part of the telescopic component is connected to the roller assembly to achieve 360-degree movement.

[0025] Beneficial effects of the present invention:

[0026] The measuring tool of the present invention comprises a measuring instrument and an auxiliary bracket, which has the characteristics of simple structure, compact appearance, convenient operation, wide application environment, etc., and can be freely switched between manual measurement mode and automatic measurement mode, wherein the automatic measurement mode can automatically measure according to the set path, and is suitable for repeated inspections of multiple flights. In order to reduce the interference of human factors on the measurement data and the judgment of the measurement results, the measurement method adopts a 10-bit ADC single-chip microcomputer chip, and automatically judges the correctness of the size through the program.

[0027] In the inspection of the installation dimensions of aircraft onboard devices, the inspectors implement the above-mentioned inspection method and use the above-mentioned special measuring tools during the implementation process to effectively prevent unqualified products from entering the next stage of assembly due to incorrect installation dimensions of aircraft onboard devices or inaccurate measurements, reduce the time for handling and troubleshooting quality problems, shorten the product delivery cycle, and especially shorten the inspection work time by more than 65%, thereby ensuring the stability of product quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 Schematic diagram of measurement principle;

[0029] Figure 2 Schematic diagram of the principle of selecting measurement points;

[0030] Figure 3 It is a schematic diagram of the structure of the special measuring tool measuring instrument (excluding the calibration target plate);

[0031] Figure 4 Schematic diagram of target plate calibration for special measuring tool measuring instrument;

[0032] Figure 5 This is a schematic diagram of a light-transmitting plate of a special measuring tool measuring instrument;

[0033] Figure 6 and Figure 7 This is a schematic diagram of the external structure of the special measuring tool controller;

[0034] Figure 8It is a schematic diagram of the internal structure of the special measuring tool controller;

[0035] Fig. 9 This is a schematic diagram of the auxiliary bracket for the special measuring tool.

[0036] Among them, 1-longitudinal drive motor, 2-longitudinal bracket, 3-longitudinal lead screw, 4-longitudinal slider, 5-transverse slider, 6-transverse lead screw, 7-transverse drive motor, 8-laser ranging probe, 9-fixed base, 10-light-transmitting plate bracket, 11-transverse bracket, 12-light-transmitting plate, 13-calibration laser transmitter, 14-calibration target plate, 15-transmission line, 16-housing, 17-upper cover, 18 touch screen, 19-self-tapping screw, 20-confirmation button, 21-control lever, 22-measurement result indicator light , 23-charging socket, 24-power switch, 25-working indicator light, 26-data input / output socket, 27-calibration laser emission switch, 28-mode selection button, 29-reset button, 30-path planning button, 31-battery module, 32-main control board, 33-data storage module, 34-control sensor, 35-speaker, 36-charging module, 37-platform, 28-outer sleeve, 39-latch, 40-inner sleeve, 41-chassis, 42-retractable component, 43-roller component. DETAILED DESCRIPTION

[0037] Taking the measurement of the size of an aircraft onboard device with a tolerance of ±1mm in automatic measurement mode as an example, the specific measurement method is as follows:

[0038] Step 1: Assembly. Install the measuring instrument onto the platform 37 of the auxiliary bracket and secure it with bolts.

[0039] Step 2: Preparation. Place the product to be tested on the aircraft horizontal measuring table fixing frame, adjust the posture of the product to ensure that it is placed horizontally. Move the measuring instrument and auxiliary bracket to the front of the product to be tested, and adjust the height of the measuring instrument.

[0040] Step 3: Calibration. Turn on the controller power switch 24, press the calibration laser emission switch 27, and the calibration laser emitter 13 emits a laser beam, which is projected onto the surface of the calibration target plate 14 through the light-transmitting plate 12. The calibration target plate 14 reflects the beam onto the light-transmitting plate 12, and by adjusting the height of the three retractable components 42, the reflected light is projected into the Φ5 bull's eye on the light-transmitting plate 12.

[0041] Step 4: Route setting. Press the path planning button 30 on the controller to adjust the beam projection position, move it to the first measurement point of the first aircraft airborne device to be tested, set the first measurement point, and set other measurement points in turn by analogy, and the path setting is completed.

[0042] Step 5: Measure. Press the mode selection button 28 on the controller once to enter the manual measurement mode, and move the control stick 21 on the controller to move the beam projection position to the plane of the aircraft reference part, and manually record the measured value h, as shown in the attached figure. Figure 1 As shown. Press the mode selection button 28 on the controller twice to enter the automatic measurement mode. On the touch screen 18, enter the reference dimension h, dimension tolerance ±1, select measurement path 1, and then press and hold the confirmation button 20 for three seconds to start the automatic measurement program. The system automatically records the distance L from each measuring point to the reference part plane, L = measured dimension - h.

[0043] Step 6: Data comparison. The theoretical data is imported into the data storage module 33 through the data input / output socket 26, and the main control board 32 compares the theoretical data with the measured data, and determines the correctness of the installation size of the aircraft onboard device in combination with the set tolerance range.

[0044] A method for checking the installation dimensions of an aircraft onboard device uses a special measuring tool during implementation, and the special measuring tool includes a measuring instrument and a controller.

[0045] Measuring instrument as attached Figure 3 , Figure 4 and Figure 5 As shown, it includes a longitudinal drive motor 1, a longitudinal bracket 2, a longitudinal screw 3, a longitudinal slider 4, a transverse slider 5, a transverse screw 6, a transverse drive motor 7, a laser ranging probe 8, a fixed base 9, a light-transmitting plate bracket 10, a transverse bracket 11, a light-transmitting plate 12, a calibration laser emitter 13 and a correction target plate 14.

[0046] The measuring instrument is a special measuring tool actuator. Among them, the fixed base 9 is the support and measurement reference of the measuring instrument. One surface is connected to the longitudinal bracket 2 and the light-transmitting plate bracket 10 by bolts, and the other surface is connected to the auxiliary bracket by bolts. The calibration laser emitter 13 is connected to the longitudinal bracket 2 by screws, and is used in conjunction with the light-transmitting plate 12 and the correction target plate 14. It uses the principle of light reflection to calibrate the position of the measuring instrument before measurement. The center of the light-transmitting plate 12 is engraved with a bull's eye with a diameter of Φ5. The correction target plate 14 is made of metal with a smooth surface and can fully reflect the light beam. The longitudinal lead screw 3 and the transverse lead screw 6 are respectively installed in the longitudinal bracket 2 and the transverse bracket 11, and the connection is connected in the form of bearings. The longitudinal drive motor 1 and the transverse drive motor 7 are respectively connected to the outside of the longitudinal bracket 2 and the transverse bracket 11 by bolts, and rotate according to the electrical signal transmitted from the controller part, driving the lead screw to rotate, and respectively driving the longitudinal slider 4 and the transverse slider 5 to move. The laser ranging probe 8 is installed on the transverse slider 5, which is used to measure the distance by emitting and capturing lasers, and to provide real-time feedback to the controller.

[0047] Controller as attached Figure 6 , Figure 7 and Figure 8 As shown, it includes a transmission line 15, a shell 16, an upper cover 17, a touch display screen 18, a self-tapping screw 19, a confirmation button 20, a control lever 21, a measurement result indicator light 22, a charging socket 23, a power switch 24, a working indicator light 25, a data input / output socket 26, a calibration laser emission switch 27, a mode selection button 28, a reset button 29, a path planning button 30, a battery module 31, a main control board 32, a data storage module 33, a control sensor 34, a speaker 35 and a charging module 36.

[0048] The controller is a special measuring tool control mechanism. Among them, the shell 16 and the upper cover 17 are the main supporting components of the controller part, both of which are made of PLA material by 3D printing and are tightened and fixed by 4 self-tapping screws 19. According to the structural requirements, positions are reserved in the shell 16 for the battery module 31, the main control board 32, the data storage module 33, the control sensor 34, the speaker 35 and the charging module 36, and openings are reserved for the charging socket 23, the power switch 24, the working indicator light 25 and the data input / output socket 26. The upper cover 17 reserves openings for the touch display screen 18, the control lever 21, the measurement result indicator light 22, the calibration laser emission switch 27, the mode selection button 28, the reset button 29 and the path planning button 30. The battery module 31 uses a DC 3.7V lithium battery, which is boosted to 5V by a boost module, and is used to drive the longitudinal drive motor 1 and the lateral drive motor 7, and at the same time power the laser ranging probe 8, the calibration laser transmitter 13, the touch display screen 18, the measurement result indicator light 22, the working indicator light 25 and the main control board 32; one end of the charging module 36 is connected to the battery module 31, and the other end is connected to the charging socket 23, and the battery can be charged by connecting a data cable.

[0049] When working, the laser rangefinder probe 8 transmits the measurement data to the main control board 32; to judge the correctness of the data, the measurement result indicator light 22 has two colors, green and red. When the data exceeds the preset limit value, it lights up red, otherwise it lights up green; the speaker 35 can issue voice prompts such as "qualified", "unqualified", "mode 1", "mode 2", etc., and the touch screen 18 displays relevant content. The mode selection button 28 is used to switch the measurement mode. This special measurement tool presets two measurement modes, namely manual measurement mode and automatic measurement mode. The system defaults to manual measurement mode, and measurement modes can be added later as needed. Among them, before the automatic measurement mode, the path planning button 30 needs to be used to preset the measurement path. Theoretical data can be imported through the data input / output socket 26, or manually entered through the touch screen 18, and the data information is stored in the data storage module 33. The reset button 29 is used for calibration before measurement.

[0050] A method for checking the installation dimensions of an aircraft airborne device uses an auxiliary bracket during implementation. The schematic diagram of the auxiliary bracket structure is shown in the attached figure. Fig. 9 As shown, the auxiliary bracket includes a platform 37 , an outer sleeve 38 , a latch 39 , an inner sleeve 40 , a chassis 41 , a retractable component 42 and a roller component 43 .

[0051] An opening is provided on the platform 37 for connecting a measuring instrument, a pin hole is provided on the outer sleeve 38, and a plurality of equidistant pin holes are provided on the inner sleeve 40. The outer sleeve 38 is sleeved on the outside of the inner sleeve 40. The outer sleeve 38 and the inner sleeve 40 can be telescopically adjusted in length. The pin 39 is inserted into the openings of the outer sleeve 38 and the inner sleeve 40 to fix the length of the sleeve. The chassis 41 is made of solid metal to ensure the stability of the auxiliary bracket. The upper part thereof is connected to the inner sleeve 40, and the lower part is connected to three groups of telescopic components 42. The main body of the telescopic components 42 is a threaded structure, and the height can be adjusted separately by rotating the thread, which is used to adjust the posture of the platform 37; the lower part of the telescopic component 42 is connected to the roller component 43 to achieve 360-degree movement.

Claims

1. A method for inspecting the installation dimensions of an aircraft onboard device, characterized in that: Here are the steps: Step 1: Determine the measurement datum; open the product drawing and select the measurement datum. The measurement datum includes the aircraft bulkhead axis plane, aircraft horizontal datum plane, aircraft symmetry axis plane and aircraft matching finishing surface; Step 2: Select the measurement points of each aircraft airborne device to be tested; the measurement points are three points on the same surface of the aircraft airborne device, and the three points are not on the same straight line. When the aircraft airborne device has a complex structure, or the area is small, resulting in a short distance between the three points, or there is an obstruction between the airborne devices, increase the number of measurement points and measure multiple surfaces; Step 3: Measure and record the dimensions from the measuring point to the measuring reference on the product drawing; Step 4: Measurement path setting: Use the computer simulation module to plan the measurement path and perform simulation to simulate the measurement process to avoid occlusion or exceeding the measurement range; Step 5: Fix the assembly with the onboard device of the aircraft under test and the measuring device to ensure that the relative positions of the two are fixed; Step 6: Turn on the measuring device and set the running track of the measuring device according to the planned route; Step 7: Use the measuring device to measure the data of the measuring point on the onboard device of the aircraft to be tested; Step 8: Compare data and draw conclusions.

2. A method for inspecting the installation dimensions of an aircraft-mounted device according to claim 1, characterized in that: In the fourth step, the measurement path must take into account the installation error of the aircraft onboard device, and the aircraft onboard devices with the same error are grouped together and measured in groups.

3. A method for inspecting the installation dimensions of an aircraft-mounted device according to claim 1 or 2, characterized in that: The measuring device comprises a measuring instrument and a controller; The measuring instrument comprises a longitudinal drive motor (1), a longitudinal bracket (2), a longitudinal lead screw (3), a longitudinal slider (4), a transverse slider (5), a transverse lead screw (6), a transverse drive motor (7), a laser distance measuring probe (8), a fixed base (9), a light-transmitting plate bracket (10), a transverse bracket (11), a light-transmitting plate (12), a calibration laser transmitter (13) and a calibration target plate (14); The fixed base (9) is a support and measurement reference of the measuring instrument. One surface is connected to the longitudinal bracket (2) and the light-transmitting plate bracket (10) by bolts, and the other surface is connected to the auxiliary bracket by bolts. The calibration laser emitter (13) is connected to the longitudinal bracket (2) by screws and is used in conjunction with the light-transmitting plate (12) and the calibration target plate (14). The longitudinal lead screw (3) and the transverse lead screw (6) are respectively installed in the longitudinal bracket (2) and the transverse bracket (11), and the connection is connected in the form of bearings. The longitudinal drive motor (1) and the transverse drive motor (7) are respectively connected to the outside of the longitudinal bracket (2) and the transverse bracket (11) by bolts. The laser distance measuring probe (8) is installed on the transverse slider (5).

4. A method for inspecting the installation dimensions of an aircraft-mounted device as claimed in claim 3, characterized in that: The center of the light-transmitting plate (12) is engraved with a bull's eye with a diameter of Φ5. The correction target plate (14) is made of metal and has a smooth surface, and is capable of totally reflecting light beams.

5. A method for inspecting the installation dimensions of an aircraft-mounted device according to claim 1 or 2, characterized in that: The measuring device comprises a measuring instrument and a controller; The controller comprises a transmission line (15), a housing (16), an upper cover (17), a touch screen (18), a self-tapping screw (19), a confirmation button (20), a control lever (21), a measurement result indicator light (22), a charging socket (23), a power switch (24), a working indicator light (25), a data input / output socket (26), a calibration laser emission switch (27), a mode selection button (28), a reset button (29), a path planning button (30), a battery module (31), a main control board (32), a data storage module (33), a control sensor (34), a speaker (35) and a charging module (36); The housing (16) has reserved positions for a battery module (31), a main control board (32), a data storage module (33), a control sensor (34), a speaker (35) and a charging module (36), and reserved openings for a charging socket (23), a power switch (24), a working indicator light (25) and a data input / output socket (26). The upper cover (17) has reserved openings for a touch display screen (18), a joystick (21), a measurement result indicator light (22), a calibration laser emission switch (27), a mode selection button (28), a reset button (29) and a path planning button (30).

6. A method for inspecting the installation dimensions of an aircraft-mounted device according to claim 5, characterized in that: The housing (16) and the upper cover plate (17) are made of PLA material by 3D printing and are fastened by four self-tapping screws (19).

7. A method for inspecting the installation dimensions of an aircraft-mounted device as claimed in claim 5, characterized in that: The battery module (31) uses a DC 3.7V lithium battery, which is boosted to 5V by a boost module, and is used to drive the longitudinal drive motor (1) and the transverse drive motor (7), and at the same time, it supplies power to the laser ranging probe (8), the calibration laser transmitter (13), the touch display screen (18), the measurement result indicator light (22), the working indicator light (25) and the main control board (32); one end of the charging module (36) is connected to the battery module (31), and the other end is connected to the charging socket (23), and the battery is charged by connecting a data cable.

8. An auxiliary bracket for a method for inspecting the installation dimensions of an aircraft-mounted device, comprising a platform (37), an outer sleeve (38), a latch (39), an inner sleeve (40), a chassis (41), a retractable assembly (42) and a roller assembly (43); An opening is provided on the platform (37) for connecting a measuring instrument, a latch hole is provided on the outer sleeve (38), a plurality of equidistant latch holes are provided on the inner sleeve (40), the outer sleeve (38) is sleeved on the outside of the inner sleeve (40), a latch (39) is inserted into the openings of the outer sleeve (38) and the inner sleeve (40), the upper part of the chassis (41) is connected to the inner sleeve (40), and the lower part is connected to three groups of telescopic components (42), and the lower part of the telescopic components (42) is connected to the roller component (43), so that 360-degree movement can be achieved.

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