A ground measurement method, device and medium for aircraft control surface deflection angle

Abstract

The present invention relates to the field of aviation technology, and discloses a ground measurement method, device, and medium for the deflection angle of an aircraft rudder. The method comprises establishing a coordinate system; selecting two points A and B as marks on the lower surface of the rudder, and recording the distance between the two points A and B; recording the projection points A' and B' of the two points A and B on the horizontal plane, recording the distance between A' and B', and calculating the angle between the projection line and the second vertical plane, and calculating the calculated angle, recording the calculated angle before the rudder deflection and the calculated angle after the deflection, and calculating the deflection angle. The device comprises a coordinate system establishment mechanism, a measuring mechanism, a storage unit, and a calculation unit. By establishing a three-dimensional coordinate system, the rudder deflection angle is calculated in combination with the change in the projection angle of the measuring point, which is applicable to ground conditions and improves the convenience and versatility of measurement.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to a ground measurement method, device and medium for the deflection angle of an aircraft control surface. Background Art

[0002] During actual flight, the error between the control angle of the control surface and the actual deflection angle will directly affect the aircraft's flight performance. Therefore, during ground maintenance and repair of the aircraft, the control surface must be inspected to ensure the accuracy of the deflection angle.

[0003] Currently, aircraft control surface measurement is typically performed using mechanical, sensor, or image-based methods. Mechanical or sensor-based methods require measurement personnel to use an elevator to reach the height of the control surface and then install the measuring equipment on the control surface for measurement. Image detection methods, such as the industrial camera-based measurement method proposed in patent publication number CN112729221A, use an industrial photogrammetry camera to measure the spatial motion trajectory of a marker point affixed to the aircraft control surface, simulate the motion trajectory of the marker point, and then obtain the aircraft control surface deflection angle.

[0004] However, the measurement methods in the existing technology still have certain problems: the mechanical and sensor-based measurement methods require personnel to use elevators to climb up to install and measure the equipment, which is cumbersome to operate, inconvenient to read, and there are safety risks in working at heights; the image detection method is complex to calculate and has high hardware costs. In addition, due to the long wings of the aircraft, when parked on the ground, the deflection axis of the rudder is not completely parallel to the ground. The existing measurement method leads to large deviations when measuring the deflection angle of the rudder on the ground. Summary of the Invention

[0005] The purpose of the present invention is to provide a ground measurement method, device and medium for the deflection angle of an aircraft rudder surface, so as to solve the problems in the prior art of safety risks in equipment installation and measurement after climbing up, and the problem that the calculation is complex when measuring using an image detection method and the non-horizontal axis of the rudder surface is not taken into account, resulting in large deviations in the rudder surface deflection angle.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] In a first aspect, the present invention provides a ground-based measurement method for an aircraft control surface deflection angle, comprising the following steps:

[0008] Step S1, establishing a coordinate system on the ground, the coordinate system including a horizontal plane, a first vertical plane, and a second vertical plane perpendicular to each other, wherein the horizontal plane is arranged horizontally, and the first vertical plane is arranged parallel to the deflection axis of the rudder surface to be measured;

[0009] Step S2: Select two points A and B on the intersection of the lower surface of the rudder surface and the normal plane of the rudder surface deflection axis, mark them, and record the straight-line distance L between the two points A and B;

[0010] Step S3: record the projection points A' and B' of points A and B on the horizontal plane, record the straight-line distance S of the line K connecting A' and B', and calculate the angle between the projection line K and the second vertical plane. , and calculate the angle using the following formula :

[0011] ;

[0012] Step S4: Record the calculated angle before the rudder deflects Calculated angle after deflection , calculate the deflection angle , .

[0013] Preferably, step S2 includes the following steps:

[0014] Step S2-1, take point A at the intersection of the second vertical plane and the lower surface of the rudder and mark it;

[0015] Step S2-2: Rotate the rudder surface while ensuring that the coordinate system is rotated while the first vertical plane is fixed, so that point A is always on the second vertical plane;

[0016] Step S2-3: The rudder surface and the coordinate system stop rotating, and point B is taken at the intersection of the transformed second vertical plane and the lower surface of the rudder surface and marked and recorded;

[0017] Step S2-4: Use the transformed second vertical plane as the normal plane of the rudder surface deflection axis, adjust the coordinate system to the state before the change, and record the straight-line distance L between points A and B.

[0018] Preferably, in step S2, the marking of points A and B is performed by laser engraving.

[0019] Preferably, in step S1, when establishing the coordinate system, the first vertical plane is arranged to be parallel and coincident with the deflection axis of the rudder surface to be measured.

[0020] In a second aspect, the present invention further provides a ground-based measurement device for an aircraft control surface deflection angle, comprising:

[0021] A coordinate system establishment mechanism is used to establish a measurement coordinate system on the ground, wherein the coordinate system includes a horizontal plane, a first vertical plane, and a second vertical plane that are perpendicular to each other, wherein the horizontal plane is horizontally arranged, and the first vertical plane is parallel to the deflection axis of the rudder surface to be measured;

[0022] The measuring mechanism is used to select and mark two points A and B on the intersection of the lower surface of the rudder surface and the normal plane of the rudder surface deflection axis, measure the straight-line distance L between the two points A and B, and record the projection points of the two measurement points on the horizontal plane and the angle between the line connecting them on the second vertical plane;

[0023] A storage unit for storing the spatial position information of the two points A and B, the straight-line distance L, the distance S of the projection line on the horizontal plane, the angle and the calculated angle before and after the rudder deflection 、 information;

[0024] The calculation unit is used to calculate the angle between the projection line of points A and B and the second vertical plane using a preset formula based on the information obtained by the measurement unit. , further calculate the angle difference before and after the rudder deflection to obtain the rudder deflection angle .

[0025] Preferably, the coordinate system establishing mechanism is a 12-line or 16-line laser level.

[0026] Preferably, the measuring mechanism includes a leveling unit and a horizontal adjustment unit; the horizontal adjustment unit is arranged on the leveling unit.

[0027] Preferably, the horizontal adjustment unit includes a rotating table, a movable table and two laser emitters, the laser emitter is used to emit a vertically set laser beam, the lower end of the rotating table is fixedly set on the leveling unit, the upper end of the rotating table can be rotatably set, the lower end of the movable table is fixedly set on the upper end surface of the rotating table, and the laser emitter is set on the movable table and can move back and forth along the length direction of the movable table.

[0028] Preferably, both the movable stage and the rotating stage are provided with scales.

[0029] In a third aspect, the present application provides a storage medium storing computer instructions. When a computer reads the computer instructions in the storage medium, the computer executes the ground measurement method for the deflection angle of the aircraft control surface as described in the first aspect.

[0030] Compared with the prior art, the present invention has the following beneficial effects:

[0031] By establishing a three-dimensional coordinate system with a clear relationship with the rudder deflection axis, the rudder deflection angle is calculated in combination with the change in the projection angle of the measuring point. The measurement method is simple and applicable to ground conditions, which improves the convenience and versatility of measurement. It avoids the use of mechanical and sensor-based measurement methods that require personnel to use elevators to climb up to install and measure equipment, which is cumbersome to operate, inconvenient to read, and poses safety risks when working at heights. It also avoids the complex calculations and high hardware costs of using image detection methods. At the same time, it avoids the problem that due to the long wings of the aircraft, the rudder deflection axis is not completely parallel to the ground when parked on the ground, and the existing measurement methods result in large deviations when measuring the rudder deflection angle on the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the technical solution of the present invention, the following is a brief introduction to the drawings required for the description. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0033] Figure 1 This is a schematic diagram of angle calculation in a specific embodiment of the present invention;

[0034] Figure 2 The structure of the horizontal adjustment unit in the specific embodiment of the present invention is shown in FIG. Figure 1 ;

[0035] Figure 3 The structure of the horizontal adjustment unit in the specific embodiment of the present invention is shown in FIG. Figure 2 .

[0036] In the figure: 1. Rotating table; 2. Moving table; 3. Laser transmitter; 4. Scale; 5. Primary adjustment rod; 6. Secondary adjustment rod; 7. Rack; 8. Slide; 9. Gear table; 10. Adjustment rod; 11. Locking rod. DETAILED DESCRIPTION

[0037] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0038] During actual flight, the error between the control angle of the control surface and the actual deflection angle will directly affect the aircraft's flight performance. Therefore, during ground maintenance and repair of the aircraft, the control surface must be inspected to ensure the accuracy of the deflection angle.

[0039] Currently, aircraft control surface measurement is typically performed using mechanical, sensor, or image-based methods. Mechanical or sensor-based methods require measurement personnel to use an elevator to reach the height of the control surface and then install the measuring equipment on the control surface for measurement. Image detection methods, such as the industrial camera-based measurement method proposed in patent publication number CN112729221A, use an industrial photogrammetry camera to measure the spatial motion trajectory of a marker point affixed to the aircraft control surface, simulate the motion trajectory of the marker point, and then obtain the aircraft control surface deflection angle.

[0040] However, the measurement methods in the existing technology still have certain problems: the mechanical and sensor-based measurement methods require personnel to use elevators to climb up to install and measure the equipment, which is cumbersome to operate, inconvenient to read, and there are safety risks in working at heights; the image detection method is complex to calculate and has high hardware costs. In addition, due to the long wings of the aircraft, when parked on the ground, the deflection axis of the rudder is not completely parallel to the ground. The existing measurement method leads to large deviations when measuring the deflection angle of the rudder on the ground.

[0041] The purpose of the present invention is to provide a ground measurement method, device and medium for the deflection angle of an aircraft rudder surface, so as to solve the problems in the prior art of safety risks in equipment installation and measurement after climbing up, and the problem that the calculation is complex when measuring using an image detection method and the non-horizontal axis of the rudder surface is not taken into account, resulting in large deviations in the rudder surface deflection angle.

[0042] See also Figure 1-Figure 2 The present invention provides a ground measurement method for the deflection angle of an aircraft control surface, and the specific implementation steps are as follows:

[0043] Step S1, constructing a three-dimensional measurement reference: An orthogonal coordinate system consisting of a horizontal plane, a first vertical plane, and a second vertical plane is established on the ground or a fixed reference system. The horizontal plane serves as the reference plane and remains horizontal. The first vertical plane must remain parallel to the deflection axis of the rudder being measured. This orientation method ensures that subsequent measurement data is directly related to the actual motion axis of the rudder. The second vertical plane, together with the first two planes, forms a three-dimensional rectangular coordinate system, providing a spatial reference frame for angle calculations.

[0044] When establishing the coordinate system, the first vertical plane is set parallel to and coincides with the deflection axis of the rudder surface being measured;

[0045] By establishing an orthogonal coordinate system encompassing the horizontal, first, and second vertical planes, the measured data is directly correlated with the actual axis of motion of the rudder surface. This orientation method not only improves measurement accuracy, but the three-dimensional rectangular coordinate system formed by the second vertical plane, the horizontal, and first vertical planes provides a comprehensive and accurate spatial reference framework for subsequent angle calculations. Furthermore, the alignment of the first vertical plane parallel to and coincident with the measured rudder surface's deflection axis further ensures the accuracy and reliability of the measured data.

[0046] Step S2: Select two points A and B on the intersection of the lower surface of the rudder surface and the normal plane of the rudder surface deflection axis, mark them, and record the straight-line distance L between the two points A and B;

[0047] The marking of points A and B is done by laser engraving;

[0048] A laser tracker is used to measure the straight-line distance L between points A and B;

[0049] When selecting the structural feature points of the rudder surface, two marking points, A and B, need to be determined on the intersection of the lower surface of the rudder surface and the normal plane of the deflection axis. The normal plane here refers to the plane perpendicular to the deflection axis of the rudder surface. Its intersection with the lower surface of the rudder surface reflects the geometric characteristics of the rudder surface in that axial direction. By measuring the straight-line distance L between points AB, the geometric reference parameters of the rudder surface in its original state are established. This distance L serves as the raw data for subsequent calculations.

[0050] Laser engraving was used to mark points A and B, ensuring their accuracy and durability, facilitating subsequent measurement and recording. Furthermore, a laser tracker was used to measure the linear distance L between points A and B, providing highly accurate geometric reference parameters and laying a solid foundation for subsequent calculations and analysis. Furthermore, the intersection of the normal plane and the lower surface of the rudder surface reflects the geometric characteristics of the rudder surface along the deflection axis, helping to more accurately capture its actual motion.

[0051] Step S3: record the projection points A' and B' of points A and B on the horizontal plane, record the straight-line distance S of the line K connecting A' and B', and calculate the angle between the projection line K and the second vertical plane. , and calculate the angle using the following formula :

[0052] ;

[0053] By measuring the straight line length S of K, we obtain the horizontal projection of line segment AB. Now, we need to calculate the angle between the projected line K and the second vertical plane. This angle reflects the orientation of line segment AB in three-dimensional space. Combined with the right triangle relationship, this step converts the three-dimensional spatial relationship into a calculable plane angle.

[0054] By measuring the straight-line distance S of the projection line K, the horizontal projection component of line segment AB is obtained, providing the necessary data for subsequent angle calculations. Simultaneously, calculating the angle between projection line K and the second vertical plane reveals the orientation of line segment AB in three-dimensional space, contributing to a more comprehensive understanding of the spatial attitude of the control surface. Furthermore, by incorporating the relationship between right triangles, the three-dimensional spatial relationship is converted into a calculable plane angle, significantly simplifying the calculation process and improving efficiency.

[0055] Step S4: Record the calculated angle before the rudder deflects Calculated angle after deflection , calculate the deflection angle , ;

[0056] The final deflection angle calculation needs to be implemented in two stages: when the rudder is in its initial position, the initial calculated angle is measured according to the above method; when the rudder deflects, the measurement point is kept unchanged and the projection measurement is repeated to obtain the calculated angle after deflection. The actual deflection angle of the rudder is the difference between the two measured angles. This method effectively isolates the translational component of the rudder by combining a fixed reference point with dynamic projection analysis, focusing on capturing pure rotational motion around the deflection axis. It is suitable for engineering scenarios such as aircraft rudder debugging that require non-contact, high-precision angle measurement.

[0057] By measuring and calculating the angle in two stages, the accuracy of the deflection angle calculation is ensured. Maintaining the measurement point position unchanged before and after the rudder deflection effectively eliminates the impact of position changes on the measurement results. Furthermore, by combining a fixed reference point with dynamic projection analysis, the translational component of the rudder surface is successfully isolated, allowing the calculation to focus more on pure rotational motion about the deflection axis. This method not only improves measurement accuracy and reliability but also has broad application prospects in engineering scenarios requiring non-contact, high-precision angle measurement, such as aircraft rudder surface commissioning.

[0058] In some embodiments, step S2 includes the following steps:

[0059] Step S2-1, take point A at the intersection of the second vertical plane and the lower surface of the rudder and mark it;

[0060] This step determines the intersection point A of the rudder surface with the second vertical plane when it is in its initial position. As part of the coordinate system, the intersection line of the second vertical plane with the lower surface of the rudder surface reflects the geometric characteristics of the rudder surface within this plane. By selecting point A on this intersection line and marking it, a stable initial reference point is established for subsequent measurements, ensuring the accuracy of the measurement starting position. This provides a reliable reference for the selection of point B and the measurement of the straight-line distance L in subsequent steps, helping to improve overall measurement accuracy.

[0061] Step S2-2: Rotate the rudder surface while ensuring that the coordinate system is rotated while the first vertical plane is fixed, so that point A is always on the second vertical plane;

[0062] During rudder surface rotation, the first vertical plane must be kept fixed to maintain the spatial orientation of the coordinate system. Simultaneously, the coordinate system is rotated to ensure that point A remains on the second vertical plane. This ensures that point A always serves as the intersection of the second vertical plane and the lower surface of the rudder surface during rudder surface deflection, providing a dynamic reference for the subsequent selection of point B. This setup maintains the position of point A by dynamically adjusting the coordinate system, ensuring that point B and point A are on the same reference plane, improving measurement consistency and accuracy and avoiding reference offsets caused by rudder surface rotation.

[0063] Step S2-3: The rudder surface and the coordinate system stop rotating, and point B is taken at the intersection of the transformed second vertical plane and the lower surface of the rudder surface and marked and recorded;

[0064] When the rudder surface rotates to the target position, the coordinate system stops rotating. At this point, point B is selected and marked at the intersection of the transformed second vertical plane (i.e., the rotated second vertical plane) and the lower surface of the rudder surface. The position of point B reflects the new geometric characteristics of the rudder surface after rotation, providing the necessary data point for the subsequent calculation of the rudder surface deflection angle. This setting obtains the new reference point B after the rudder surface rotates. Together with the initial point A, it forms the measurement baseline, providing key data for calculating the rudder surface deflection angle and ensuring the integrity of the measurement results.

[0065] Step S2-4: Use the transformed second vertical plane as the normal plane of the rudder deflection axis, adjust the coordinate system to the state before the change, and record the straight-line distance L between points A and B;

[0066] In this step, the second vertical plane after rotation is treated as the normal plane to the rudder's deflection axis to accommodate the new spatial orientation of the rudder after rotation. Simultaneously, the coordinate system is restored to its initial state to maintain the consistency of the measurement benchmark. In this state, the straight-line distance L between points A and B is measured and recorded, providing basic data for subsequent calculations of the deflection angle. This setup, by returning the coordinate system to its initial state, ensures the consistency of the measurement benchmark and avoids measurement errors caused by coordinate system changes. Recording the straight-line distance L provides accurate data support for subsequent calculations of the deflection angle, helping to improve overall measurement accuracy.

[0067] For the analysis of the formula, refer to Figure 1After the operations of step S1 and step S2, we can obtain points A and B and their projection points A' and B' on the horizontal plane. At this time, points A and B are on the normal plane, and A' and B' are on the horizontal plane. A plane parallel to the horizontal plane is drawn through point A and intersects BB' at point C. A plane parallel to the horizontal plane is drawn through AC and intersects the normal plane at line AP. CD is drawn perpendicular to AP and BD is connected.

[0068] At this time, the length of AC and the length of A'B' are both S, the length of AB is L, and ∠CAD= , the length of AD is , and then calculate ∠BAD= ;

[0069] Through the above method, when When changes, Synchronous changes, and = ; and There is a linear correspondence between the angle change of the rudder deflection axis on the normal plane Will be directly reflected in the calculation angle The change of , and the change amount is equal, this relationship is important for measuring It is of great significance to indirectly reflect the deflection of the rudder surface.

[0070] In some embodiments, as Figure 2 and Figure 3 As shown, a ground-based measurement device for the deflection angle of an aircraft control surface is provided, comprising:

[0071] A coordinate system establishment mechanism is used to establish a measurement coordinate system on the ground, wherein the coordinate system includes a horizontal plane, a first vertical plane, and a second vertical plane that are perpendicular to each other, wherein the horizontal plane is horizontally arranged, and the first vertical plane is parallel to the deflection axis of the rudder surface to be measured;

[0072] The measuring mechanism is used to select and mark two points A and B on the intersection of the lower surface of the rudder surface and the normal plane of the rudder surface deflection axis, measure the straight-line distance L between the two points A and B, and record the projection points of the two measurement points on the horizontal plane and the angle between the line connecting them on the second vertical plane;

[0073] A storage unit, configured to store the spatial position information of points A and B, the straight-line distance L, the distance S of the projection line on the horizontal plane, the included angle, and the calculated angle before and after the rudder surface deflection;

[0074] The calculation unit is used to calculate the angle between the projection line of points A and B and the second vertical plane according to the information obtained by the measuring unit using a preset formula, and further calculate the angle difference before and after the rudder surface is deflected to obtain the rudder surface deflection angle.

[0075] In some embodiments, the coordinate system establishment mechanism is a 12-line or 16-line laser level;

[0076] In this embodiment, a 12-line laser level is selected.

[0077] In some embodiments, the measuring mechanism includes a leveling unit and a horizontal adjustment unit; the horizontal adjustment unit is arranged on the leveling unit, the leveling unit is a horizontal reference loading platform, and the adjustment unit is arranged on a horizontal pallet of the horizontal reference loading platform.

[0078] In some embodiments, the horizontal adjustment unit includes a rotating table 1, a moving table 2 and two laser emitters 3. The laser emitter 3 is used to emit a vertically set laser beam. The lower end of the rotating table 1 is fixedly set on the leveling unit, and the upper end of the rotating table 1 can be rotatably set. The rotating table 1 is provided with a primary adjustment rod 5 and a secondary adjustment rod 6. The primary adjustment rod 5 can be directly pushed by hand, and the secondary adjustment rod 6 adopts a rotatable screw. One end of the screw is used for rotation adjustment, and the other end of the screw is used to abut against the rotating disk of the rotating table 1. The lower end of the moving table 2 is fixedly set on the upper end surface of the rotating table 1, and a slide 8 is provided in the degree direction of the moving table 2. A rack 7 is provided on the slide 8, and two gear platforms 9 are provided on the rack 7. The laser emitter 3 is installed on the gear platform 9. An adjusting rod 10 is provided on the gear platform 9. The adjusting rod 10 is connected to a driving gear, and the driving gear is engaged with the rack 7. The laser emitter 3 is set in the slide 8 of the moving table 2 and moves back and forth along the length direction of the moving table 2.

[0079] In some embodiments, both the movable stage 2 and the rotating stage 1 are provided with scales 4 for reading the distance between the two laser emitters 3 and the angle between the line K between the two laser emitters 3 and the second vertical plane.

[0080] In some embodiments, the adjusting rod 10 , the primary adjusting rod 5 , and the secondary adjusting rod 6 are each provided with a corresponding locking rod 11 , which is used to lock the adjusting rod 10 , the primary adjusting rod 5 , and the secondary adjusting rod 6 .

[0081] In some embodiments, a 12-line laser level is used as a coordinate system establishment mechanism to establish an orthogonal coordinate system on the ground, consisting of a horizontal plane, a first vertical plane, and a second vertical plane. The horizontal plane remains horizontal, and the first vertical plane is parallel to the deflection axis of the rudder being measured, ensuring that subsequent measurement data is directly related to the actual motion axis of the rudder. This coordinate system establishment mechanism ensures the accuracy and reliability of the measurement benchmark, providing a solid foundation for subsequent measurements.

[0082] The measuring mechanism includes a leveling unit and a horizontal adjustment unit. The leveling unit is a horizontal reference loading platform, and the horizontal adjustment unit is set on the leveling unit;

[0083] The horizontal adjustment unit includes a rotating stage 1, a moving stage 2 and two laser emitters 3. The laser emitters 3 are used to emit vertically arranged laser beams to select and mark two points A and B.

[0084] The lower end of the rotating platform 1 is fixed on the leveling unit, and the upper end of the rotating platform 1 is rotatable. The lower end of the moving platform 2 is fixed on the upper end surface of the rotating platform 1, and the moving platform 2 is provided with a slide 8 and a rack 7;

[0085] Two laser emitters 3 are mounted on a gear platform 9, which is mounted on a rack 7 and meshes with the rack 7 via a drive pinion. Engineers adjust the position of the laser emitters 3 on the movable platform 2 using an adjustment lever 10 and lock the adjustment lever 11 to ensure the stability of the laser emitters 3.

[0086] Operate the measuring mechanism to select and mark points A and B on the intersection of the lower surface of the rudder and the normal plane of the rudder deflection axis. Use laser engraving to mark points A and B to ensure the accuracy and durability of the markings.

[0087] At the same time, a laser tracker is used to measure the straight-line distance L between points A and B, and to record the projections of the two measured points on the horizontal plane and the angle between their connecting line and the second vertical plane. The scales 4 on the movable stage 2 and the rotating stage 1 help engineers read the distance between the two laser emitters 3 and the angle between the connecting line K and the second vertical plane.

[0088] The measuring mechanism uses a laser emitter and laser tracker to precisely select and measure points A and B, improving measurement accuracy and efficiency. The laser engraving method ensures the durability of the marked points, facilitating subsequent measurement and recording.

[0089] The storage unit stores information such as the spatial position of points A and B, the straight-line distance L, the horizontal distance S of their projected connection, the included angle, and the calculated angles before and after the rudder deflection. This data provides the basis for subsequent angle calculations and analysis. The storage unit facilitates data storage and subsequent analysis, allowing engineers to access historical measurement data at any time for long-term tracking and analysis of the rudder's deflection angles.

[0090] The calculation unit calculates the angle between the projection line of points A and B and the second vertical plane using a preset formula based on the information obtained by the measuring mechanism;

[0091] The calculation unit calculates the angle difference before and after the rudder is deflected to obtain the rudder deflection angle. Engineers can use the data in the storage unit to compare and analyze the measurement results of the rudder at different deflection angles.

[0092] The calculation unit uses a preset formula to quickly calculate the deflection angle of the rudder surface, improving work efficiency. Based on the calculation results, the design and manufacturing process of the rudder surface can be adjusted in a timely manner to ensure that the product meets the design requirements.

[0093] In some embodiments, the present application provides a storage medium that stores computer instructions. When a computer reads the computer instructions in the storage medium, the computer executes a ground measurement method for the deflection angle of an aircraft control surface.

[0094] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "includes," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0095] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A ground measurement method for the deflection angle of an aircraft control surface, characterized in that: The following steps are involved: Step S1, establishing a coordinate system on the ground, the coordinate system including a horizontal plane, a first vertical plane, and a second vertical plane perpendicular to each other, wherein the horizontal plane is arranged horizontally, and the first vertical plane is arranged parallel to the deflection axis of the rudder surface to be measured; Step S2: Select two points A and B on the intersection of the lower surface of the rudder surface and the normal plane of the rudder surface deflection axis, mark them, and record the straight-line distance L between the two points A and B; Step S3: record the projection points A' and B' of points A and B on the horizontal plane, record the straight-line distance S of the line K connecting A' and B', and calculate the angle between the projection line K and the second vertical plane. , and calculate the angle using the following formula : ； Step S4: Record the calculated angle before the rudder deflects Calculated angle after deflection , calculate the deflection angle , .

2. The ground measurement method for the deflection angle of an aircraft control surface according to claim 1, characterized in that: Step S2 includes the following steps: Step S2-1, take point A at the intersection of the second vertical plane and the lower surface of the rudder and mark it; Step S2-2: Rotate the rudder surface while ensuring that the coordinate system is rotated while the first vertical plane is fixed, so that point A is always on the second vertical plane; Step S2-3: The rudder surface and the coordinate system stop rotating, and point B is taken at the intersection of the transformed second vertical plane and the lower surface of the rudder surface and marked and recorded; Step S2-4: Use the transformed second vertical plane as the normal plane of the rudder surface deflection axis, adjust the coordinate system to the state before the change, and record the straight-line distance L between points A and B.

3. The ground measurement method for the deflection angle of an aircraft control surface according to claim 1, characterized in that: In step S2, the markings at points A and B are made by laser engraving.

4. The ground measurement method for the deflection angle of an aircraft control surface according to claim 1, characterized in that: In step S1, when establishing the coordinate system, the first vertical plane is arranged to be parallel and coincident with the deflection axis of the rudder surface to be measured.

5. A ground-based measurement device for the deflection angle of an aircraft control surface, characterized in that: include: A coordinate system establishment mechanism is used to establish a measurement coordinate system on the ground, wherein the coordinate system includes a horizontal plane, a first vertical plane, and a second vertical plane that are perpendicular to each other, wherein the horizontal plane is horizontally arranged, and the first vertical plane is parallel to the deflection axis of the rudder surface to be measured; The measuring mechanism is used to select and mark two points A and B on the intersection of the lower surface of the rudder surface and the normal plane of the rudder surface deflection axis, measure the straight-line distance L between the two points A and B, and record the projection points of the two measurement points on the horizontal plane and the angle between the line connecting them on the second vertical plane; A storage unit, configured to store the spatial position information of points A and B, the straight-line distance L, the distance S of the projection line on the horizontal plane, the included angle, and the calculated angle before and after the rudder surface deflection; The calculation unit is used to calculate the angle between the projection line of points A and B and the second vertical plane according to the information obtained by the measuring unit using a preset formula, and further calculate the angle difference before and after the rudder surface is deflected to obtain the rudder surface deflection angle.

6. The ground-based measurement device for the deflection angle of an aircraft control surface according to claim 5, characterized in that: The coordinate system establishment mechanism is a 12-line or 16-line laser level.

7. The ground-based measurement device for aircraft control surface deflection angle according to claim 5, characterized in that: The measuring mechanism comprises a leveling unit and a horizontal adjustment unit; the horizontal adjustment unit is arranged on the leveling unit.

8. The ground-based measurement device for the deflection angle of an aircraft control surface according to claim 5, characterized in that: The horizontal adjustment unit comprises a rotating table (1), a moving table (2) and two laser emitters (3), wherein the laser emitters (3) are used for emitting vertically arranged laser beams, the lower end of the rotating table (1) is fixedly arranged on the leveling unit, the upper end of the rotating table (1) is rotatably arranged, the lower end of the moving table (2) is fixedly arranged on the upper end surface of the rotating table (1), and the laser emitters (3) are arranged on the moving table (2) and can reciprocate along the length direction of the moving table (2).

9. The ground-based measurement device for aircraft control surface deflection angle according to claim 8, characterized in that: Scales (4) are provided on both the moving platform (2) and the rotating platform (1).

10. A storage medium, characterized in that: The storage medium stores computer instructions. When the computer reads the computer instructions in the storage medium, the computer executes the ground measurement method for the deflection angle of the aircraft control surface as claimed in claim 1.

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