Aircraft level measurement method and device, method of use, medium

Abstract

The application relates to the field of aerospace technology, in particular to a kind of aircraft horizontal measurement method and device, use method, medium, including four measurement modules, four reference construction systems and processing units, the reference construction system is respectively arranged below the measurement module, and is electrically connected with the height adjusting system, the reference construction system includes lifting mechanism and horizontal reference controller arranged on the height adjusting structure;Processing unit is used to collect the data of sensor, and algorithm solving is carried out.The above structure of the application can complete the measurement of all measured points at one time, without measuring and counting each point respectively, in addition, because the flatness of the ground cannot be particularly good, the horizontal reference controller is used to generate simulated data horizontal reference surface, so that the reference surface in the measurement process is more accurate, and the measurement result error is smaller.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically, to an aircraft level measurement method and apparatus, method of use, and medium. Background Technology

[0002] Aircraft level measurement is one of the important means of controlling the shape quality of aircraft. Level measurement is carried out on each aircraft at different times. Aircraft level measurement, also known as aircraft feature point measurement, is a measurement work carried out on specified aircraft level measurement points to ensure that the relative position and symmetry between various components of the aircraft, as well as the position and attitude of the aircraft components themselves, have sufficient accuracy.

[0003] Aircraft leveling is fundamental to aircraft leveling measurements. It involves longitudinal and lateral leveling, meaning adjusting the aircraft's attitude to ensure that the leveling reference points (measuring points representing the aircraft's levelness) are at the same horizontal level. The accuracy of aircraft leveling directly affects the verification results of the relative position accuracy of the aircraft's components in leveling measurements.

[0004] However, current aircraft level inspection generally involves multiple measurements of each test point using sensors, followed by comparison to obtain the inspection results. This inspection method is quite cumbersome and involves a huge workload. Summary of the Invention

[0005] The purpose of this invention is to provide an aircraft level measurement method, device, usage method, and medium to solve the problem that the existing detection methods are cumbersome and involve a huge workload.

[0006] The embodiments of the present invention are achieved through the following technical solutions:

[0007] In a first aspect, the present invention provides an aircraft level measuring device, comprising:

[0008] Four measurement modules are respectively set at the left, right, front and rear of the aircraft for collecting aircraft angle data. The measurement modules include positioning sensors and displacement sensors.

[0009] Four reference construction systems are respectively set below the measurement module. Each reference construction system includes a lifting mechanism and a horizontal reference controller set on the lifting mechanism. The lifting mechanism is used to drive the horizontal reference controller to move up and down. The horizontal reference controller is electrically connected to the corresponding measurement module and is used to construct the horizontal reference of the entire system.

[0010] The processing unit is electrically connected to the measurement module and the reference construction system, and is used to collect sensor data and perform algorithm solutions.

[0011] In one embodiment of the present invention, a first auxiliary connecting device is further included, comprising a first connecting rod and a second connecting rod, wherein the first connecting rod is hinged to the second connecting rod, one end of the first connecting rod is provided with an adhesive block for connecting to the rear of the aircraft, and the other end of the second connecting rod is provided with a measuring module.

[0012] In one embodiment of the present invention, a second auxiliary connecting device is further included. The second auxiliary connecting device includes an auxiliary connecting block. A wedge-shaped notch is provided in the middle of the auxiliary connecting block, and a positioning sink is provided on one side opposite to the wedge-shaped notch.

[0013] In one embodiment of the present invention, the lifting mechanism includes a container bucket, an electric lifting module, a manual lifting module, and a triangular support frame. The container bucket is disposed on the electric lifting module, the bottom of the electric lifting module is connected to the manual lifting module, and the triangular support frame is connected to the bottom of the manual lifting module.

[0014] In one embodiment of the present invention, the top of the container is provided with a plurality of proximity switches, and the bottom of the container is provided with a connecting pipe, the connecting pipe being provided with a connecting valve.

[0015] In one embodiment of the present invention, a scale is provided on the manual lifting module.

[0016] Secondly, the present invention also provides a method of using an aircraft level measuring device, including the above-mentioned aircraft level measuring device;

[0017] The aircraft is supported and lifted off the ground using a lifting mechanism;

[0018] The four measurement modules are respectively set at the four measurement points at the front, rear, left, and right of the aircraft;

[0019] The four benchmark construction systems are respectively positioned vertically below the four measurement modules and aligned accordingly;

[0020] Adjust the height of the benchmark construction system so that it is within the measurement range of the measurement module;

[0021] Connect the data transmission lines of the measurement module and the benchmark construction system to the signal bus processing controller. After integration by the signal bus processing controller, connect to the processing unit to complete the construction of the measurement system.

[0022] In one embodiment of the present invention, the step of setting the four measuring modules at the four measuring points at the front, rear, left, and right of the aircraft includes:

[0023] The first auxiliary connecting device and the second auxiliary connecting device are respectively connected to the front and rear measuring points of the aircraft.

[0024] Two of the measurement modules are connected to the first auxiliary connection device and the second auxiliary connection device, respectively.

[0025] Thirdly, the present invention also provides a method for measuring the level of an aircraft, comprising:

[0026] Set up four test points for the aircraft to collect signals, including the front test point, the rear side point, the left test point, and the rear test point, and construct a reference horizontal plane, a positioning sensor measurement plane, and a displacement sensor reference plane.

[0027] Obtain the linear displacement of the front measuring point, the rear side point, the left measuring point, and the rear measuring point to the reference horizontal plane;

[0028] Using the reference horizontal plane as a reference, obtain the first attitude angle between the positioning sensor measurement plane and the reference horizontal plane;

[0029] The second attitude angle between the displacement sensor reference plane and the reference horizontal plane is obtained by using the attitude angle.

[0030] The linear displacements of the four test points and the offset angles between their corresponding vertical elevations are calculated using the second attitude angle and spatial geometric relationship.

[0031] The vertical elevations of the four test points are obtained by calculating the offset angle, and the vertical elevations of the four test points are compared to determine whether they are level.

[0032] Fourthly, the present invention also incorporates a computer-readable storage medium on which a computer program is stored, which, when executed by a processor, implements the aircraft level measurement method described above.

[0033] The technical solutions of the embodiments of the present invention have at least the following advantages and beneficial effects:

[0034] The structure of this invention mainly includes a measurement module, a reference construction system, and a processing unit. The reference construction system includes a lifting mechanism and a horizontal reference controller mounted on the height adjustment structure. With this device, all measured points can be measured at once, eliminating the need for separate measurement and statistics for each point. Furthermore, because the flatness of the ground cannot be perfectly achieved, the horizontal reference controller generates a simulated horizontal reference surface, making the reference surface during the measurement process more accurate and thus reducing measurement errors. Attached Figure Description

[0035] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0036] Figure 1 This invention relates to the principle of the aircraft level measurement system.

[0037] Figure 2 This is a schematic diagram of the structure of the first auxiliary connecting device of the present invention;

[0038] Figure 3 This is a schematic diagram of the structure of the second auxiliary connecting device of the present invention;

[0039] Figure 4 This is a schematic diagram of the structure of the benchmark construction system of the present invention;

[0040] Icons: 1-Adhesive block, 2-First connecting rod, 3-Second connecting rod, 4-Container, 5-Electric lifting module, 6-Manual lifting module, 7-Triangular support frame, 8-Auxiliary connecting block. Detailed Implementation

[0041] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0042] The terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. The naming or numbering of steps in this application does not imply that the steps in the method flow must be executed in the chronological / logical order indicated by the naming or numbering. The execution order of named or numbered process steps can be changed according to the desired technical objective, as long as the same or similar technical effect is achieved.

[0043] The independently described modules or submodules may or may not be physically separated; they may be implemented in software or hardware, and some modules or submodules may be implemented in software, with the processor calling the software to implement the function of these modules or submodules, while other modules or submodules may be implemented in hardware, such as through hardware circuits. Furthermore, some or all of the modules can be selected to achieve the purpose of this application's solution according to actual needs.

[0044] Please refer to Figures 1-4 The present invention provides an aircraft level measuring device, comprising:

[0045] Four measurement modules are respectively set at the left, right, front and rear four positions of the aircraft, namely the front measurement point, rear measurement point, left measurement point and right measurement point, for the acquisition of aircraft angle data. The measurement modules include positioning sensors and displacement sensors.

[0046] Four benchmark construction systems are respectively set below the measurement module and electrically connected to the height adjustment system. Each benchmark construction system includes a lifting mechanism and a horizontal benchmark controller set on the height adjustment structure. The lifting mechanism is used to drive the horizontal benchmark controller to move up and down. The horizontal benchmark controller is electrically connected to the corresponding measurement module and is used to construct the horizontal benchmark of the entire system.

[0047] The processing unit is electrically connected to the measurement module and the reference construction system, and is used to collect sensor data and perform algorithm solutions.

[0048] The structure of this invention mainly includes a measurement module, a reference construction system, and a processing unit. The reference construction system includes a lifting mechanism and a horizontal reference controller mounted on a height adjustment structure. In use, the lifting mechanism supports and lifts the aircraft off the ground. Four measurement modules are positioned at four measurement points on the front, rear, left, and right sides of the aircraft. Four reference construction systems are positioned vertically below the four measurement modules and aligned. The height of the reference construction systems is adjusted to be within the measurement range of the measurement modules. The data transmission lines of the measurement modules and reference construction systems are connected to a signal bus processing controller. After integration by the signal bus processing controller, the data is connected to the processing unit for measurement. This device allows for the simultaneous measurement of all measurement points without requiring individual measurement and statistics at each point. Furthermore, because ground flatness is often unpredictable, the horizontal reference controller generates a simulated horizontal reference surface, making the reference surface more accurate during measurement and thus reducing measurement errors.

[0049] In this embodiment, the rear point is located at the tail of the aircraft, where the aircraft waistline is relatively prominent. There is a distance difference between the measuring point in both the horizontal and vertical directions. Since the rear measuring point is too far from the aircraft waistline in the horizontal direction, if the direct measuring module is installed at the rear point, the laser at that point will not be able to be projected onto the laser reflective surface in the reference construction system. Therefore, a first auxiliary connection device is also provided to install the measuring module at the rear point.

[0050] Specifically, it includes a first connecting rod 2 and a second connecting rod 3. The first connecting rod 2 is hinged to the second connecting rod 3 so that the first connecting rod 2 and the second connecting rod 3 can rotate to ensure that the auxiliary second connecting rod 3 is always in the plumb line direction, which is used to eliminate the height difference between the front and rear measuring points. One end of the first connecting rod 2 is provided with an adhesive block 1 for connecting to the rear of the aircraft, and the other end of the second connecting rod 3 is provided with a measuring module.

[0051] The first connecting rod 2 has a total length of 435mm. The adhesive block 1 at one end of the first connecting rod 2 is a round block with a diameter of 40mm and a thickness of 8mm. On the side that connects to the aircraft, there is a positioning point with a diameter of 2mm and an outward protrusion of 0.5mm, so that the adhesive block 1 can be accurately and stably installed at the rear measuring point. The first connecting rod 2 adopts a hollow design to reduce the overall weight of the auxiliary connecting rod. The external structure of the second connecting rod 3 is a rectangle with a diameter of 10mm × 8mm, and the internal structure is a square with a side length of 6mm.

[0052] In this embodiment, since the front measuring point is located on the aircraft's waistline, the measuring module cannot be directly installed at the measuring point. Therefore, an auxiliary connecting block 8 is provided at the measuring point to ensure that the measuring module can be stably installed at the measuring point.

[0053] Specifically, the auxiliary connecting block 8 can be designed as a cube with dimensions of 66mm×33mm×32mm. The side of the auxiliary connecting block 8 that connects to the aircraft is designed with a 121° wedge-shaped notch to ensure that the auxiliary connecting block 8 can be stably attached to the aircraft surface. A positioning sink is designed at the center of the side that connects to the measurement module for positioning with the measurement module. The positioning sink has a diameter of 2mm and a sinking of 0.5mm.

[0054] In one embodiment of the present invention, the lifting mechanism includes a container 4, an electric lifting module 5, a manual lifting module 6, and a triangular support frame 7. The container 4 is provided with a laser reflective surface. The container 4 is disposed on the electric lifting module 5. The bottom of the electric lifting module 5 is connected to the manual lifting module 6. The triangular support frame 7 is connected to the bottom of the manual lifting module 6.

[0055] Container 4 has an inner diameter of 50mm and a net height of 50mm. Container 4 is equipped with an end cap, which is screwed on for sealing when not in use. The end cap has a small hole for threading a wire, and a similar hole is designed on container 4 so that a thin string can be used to connect the end cap when it is opened, preventing loss. Container 4 is equipped with two proximity switches, which provide a judgment signal during electric lifting to prevent contact with the measuring module. Wiring for the proximity switches is also arranged on container 4 for easy connection to the circuit processing junction box. The bottom of container 4 has a 10mm inner diameter pipe for quick connection. A retraction switch is provided on this pipe, with a quick-connect fitting behind it for opening or closing the liquid flow. Regarding the selection of this switch, the switch should have an indication of the switching direction.

[0056] The electric lifting module 5 has a stroke of 0-500mm; the electric lifting module 5 needs to have position positioning accuracy, for example, by inputting 10mm through the control line, the electric lifting module 5 can rise by 10mm accordingly, and the accuracy of the rising height needs to be controlled within ±0.5mm; when the proximity switch receives a proximity signal feedback, it stops operating; a circuit processing junction box with a length and shape of approximately 150mm*150mm*70mm is set at a suitable position on the electric lifting module 5 to connect and process the circuits of the electric lifting module 5, sensor, and proximity switch.

[0057] The manual lifting module 6 is engraved with graduations to allow for easy manual coarse adjustments to the desired height. A weight block is designed beneath the triangular support frame 7 to prevent the structure from tipping over. With the electric lifting module 5 lowered to its lowest position, and in conjunction with appropriate adjustments to the manual lifting module 6, the total height can be adjusted within the range of 950mm-1750mm.

[0058] The present invention also provides a method of using an aircraft level measuring device, including the above-described aircraft level measuring device;

[0059] S101: The aircraft is supported and lifted off the ground by a lifting mechanism;

[0060] S102: Set the four measurement modules at the four measurement points at the front, rear, left, and right of the aircraft, respectively;

[0061] S103: Set the four reference construction systems vertically below the four measurement modules respectively, and align them;

[0062] S104: Adjust the height of the reference construction system so that it is within the measurement range of the measurement module;

[0063] S105: Connect the data transmission line of the measurement module and the benchmark construction system to the signal bus processing controller. After integration by the signal bus processing controller, it is connected to the processing unit to complete the construction of the measurement system.

[0064] In addition, the method of setting the four measurement modules at the four measurement points at the front, rear, left, and right of the aircraft includes:

[0065] The first auxiliary connecting device and the second auxiliary connecting device are respectively connected to the front and rear measuring points of the aircraft.

[0066] Two of the measurement modules are connected to the first auxiliary connection device and the second auxiliary connection device, respectively.

[0067] The present invention also provides a method for measuring the level of an aircraft, comprising:

[0068] S201: Set up the four test points for the aircraft to collect signals, including the front test point, the rear side point, the left test point and the rear test point, and construct the reference horizontal plane, the positioning sensor measurement plane and the displacement sensor reference plane.

[0069] S202: Obtain the linear displacement of the front measuring point, the rear side point, the left measuring point, and the rear measuring point to the reference horizontal plane;

[0070] S203: Using the reference horizontal plane as a reference, obtain the first attitude angle between the positioning sensor measurement plane and the reference horizontal plane;

[0071] S204: Obtain the second attitude angle between the displacement sensor reference plane and the reference horizontal plane by using the attitude angle;

[0072] S205: The linear displacement of the four test points and the offset angle between the corresponding vertical elevations are calculated by the second attitude angle meter and spatial geometric relationship;

[0073] S206: Calculate the vertical elevation of the four test points by offset angle, and compare the vertical elevation of the four test points to determine whether they are horizontal.

[0074] The steps described above will be further explained below;

[0075] Assuming the front, rear, left, and back measurement points are A, B, C, and D respectively, and plane A'B'C'D' is the reference horizontal plane, the plane is constructed by adjusting the height adaptive adjustment mechanism using an adaptive horizontal reference controller. The positioning sensor measurement plane is constructed using data collected by the positioning sensor. qi x qi y qi The displacement sensor reference plane is constructed using the data collected by the displacement sensor. ai x ai yai .

[0076] L a L b L c L d These represent the linear displacements measured by measurement modules A, B, C, and D, respectively; H a H b H c H d These are the vertical elevations of feature points A, B, C, and D, respectively.

[0077] During the measurement process, the micro-inertial compensation plumb bob height laser measurement module is first installed at each feature point. Then, the height adaptive adjustment mechanism below the module is adjusted vertically using an adaptive horizontal reference controller to construct the reference horizontal plane A'B'C'D'. Next, the laser measurement module measures the linear displacement (L) of feature points A, B, C, and D to the reference plane. a L b L c L d Simultaneously, the output attitude angles of the micro-inertial positioning sensor in the module are obtained as (α1, β1), (α2, β2), (α3, β3), and (α4, β4). Based on the spatial coordinate transformation theory, the attitude angle between the laser displacement sensor's reference plane and the horizontal plane can be obtained as follows:

[0078]

[0079] In the formula, ω i , λ i These are the pitch angle and roll angle of the reference plane for each laser displacement sensor, respectively.

[0080] Based on the pitch and roll angles of the laser displacement sensor, the linear displacement (L) can be obtained by solving spatial geometric relationships. a L b L c L d ) and the vertical elevation (H) of the corresponding feature point a H b H c H d The offset angles between them are:

[0081]

[0082] Thus, the vertical elevations of each feature point are obtained as follows:

[0083]

[0084] Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0085] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. This computer software product, stored in a storage medium, includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0086] The above are merely preferred embodiments of the present invention and are not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft leveling measuring device, characterized in that, include Four measurement modules are set at the left, right, front, and rear positions of the aircraft, respectively, as front measurement point, rear side point, left measurement point and right measurement point, for collecting aircraft angle data. The measurement modules include positioning sensors and displacement sensors. Four reference construction systems are respectively set below the measurement module. Each reference construction system includes a lifting mechanism and a horizontal reference controller set on the lifting mechanism. The lifting mechanism is used to drive the horizontal reference controller to move up and down. The horizontal reference controller is electrically connected to the corresponding measurement module and is used to construct the horizontal reference of the entire system. The processing unit is electrically connected to the measurement module and the reference construction system, and is used to collect sensor data and perform algorithm solutions. The algorithm solution includes constructing a reference horizontal plane, a positioning sensor measurement plane, and a displacement sensor reference plane; Obtain the linear displacement of the front measuring point, rear measuring point, left measuring point, and right measuring point to the reference horizontal plane; Using the reference horizontal plane as a reference, obtain the first attitude angle between the positioning sensor measurement plane and the reference horizontal plane; The second attitude angle between the displacement sensor reference plane and the reference horizontal plane is obtained by using the first attitude angle; The linear displacements of the four test points and the offset angles between their corresponding vertical elevations are calculated using the second attitude angle and spatial geometric relationship. The vertical elevations of the four test points are obtained by calculating the offset angle, and the vertical elevations of the four test points are compared to determine whether they are level.

2. The aircraft leveling measuring device according to claim 1, characterized in that, It also includes a first auxiliary connection device, which includes a first connecting rod and a second connecting rod. The first connecting rod is hinged to the second connecting rod. One end of the first connecting rod is provided with an adhesive block for connection to the rear of the aircraft, and the other end of the second connecting rod is provided with one of the measuring modules.

3. The aircraft level measuring device according to claim 2, characterized in that, It also includes a second auxiliary connecting device, which includes an auxiliary connecting block. The auxiliary connecting block has a wedge-shaped notch in the middle and a positioning sink is provided on one side opposite to the wedge-shaped notch.

4. The aircraft level measuring device according to claim 1, characterized in that, The lifting mechanism includes a container barrel, an electric lifting module, a manual lifting module, and a triangular support frame. The container barrel is provided with a laser reflective surface. The container barrel is mounted on the electric lifting module. The bottom of the electric lifting module is connected to the manual lifting module. The triangular support frame is connected to the bottom of the manual lifting module.

5. The aircraft level measuring device according to claim 4, characterized in that, The container barrel is equipped with several proximity switches on its top and a connecting pipe at its bottom, which is equipped with a connecting valve.

6. The aircraft level measuring device according to claim 4, characterized in that, The manual lifting module is equipped with a scale.

7. A method of using the aircraft level measuring device as described in claim 3, characterized in that, include; The aircraft is supported and lifted off the ground using a lifting mechanism; The four measurement modules are respectively set at the four measurement points at the front, rear, left, and right of the aircraft; The four benchmark construction systems are respectively positioned vertically below the four measurement modules and aligned accordingly; Adjust the height of the benchmark construction system so that it is within the measurement range of the measurement module; Connect the data transmission lines of the measurement module and the benchmark construction system to the signal bus processing controller. After integration by the signal bus processing controller, connect to the processing unit to complete the construction of the measurement system.

8. The method of using the aircraft level measuring device according to claim 7, characterized in that, The method of setting the four measurement modules at the four measurement points at the front, rear, left, and right of the aircraft includes: The first auxiliary connecting device and the second auxiliary connecting device are respectively connected to the front and rear measuring points of the aircraft. Two of the measurement modules are connected to the first auxiliary connection device and the second auxiliary connection device, respectively.

9. A method for measuring the level of an aircraft level measuring device as described in any one of claims 1-6, characterized in that, include; Set up four test points for the aircraft to collect signals, including the front test point, the rear test point, the left test point, and the right test point, and construct a reference horizontal plane, a positioning sensor measurement plane, and a displacement sensor reference plane. Obtain the linear displacement of the front measuring point, rear measuring point, left measuring point, and right measuring point to the reference horizontal plane; Using the reference horizontal plane as a reference, obtain the first attitude angle between the positioning sensor measurement plane and the reference horizontal plane; The second attitude angle between the displacement sensor reference plane and the reference horizontal plane is obtained by using the first attitude angle; The linear displacements of the four test points and the offset angles between their corresponding vertical elevations are calculated using the second attitude angle and spatial geometric relationship. The vertical elevations of the four test points are obtained by calculating the offset angle, and the vertical elevations of the four test points are compared to determine whether they are level.

10. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium, which, when executed by a processor, implements the level measurement method as described in claim 9.

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