CN113739750B - Airplane control surface measuring device and measuring method - Google Patents
Airplane control surface measuring device and measuring method Download PDFInfo
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- CN113739750B CN113739750B CN202110983664.4A CN202110983664A CN113739750B CN 113739750 B CN113739750 B CN 113739750B CN 202110983664 A CN202110983664 A CN 202110983664A CN 113739750 B CN113739750 B CN 113739750B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
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Abstract
The invention provides a measuring device and a measuring method for a control surface of an airplane, wherein the measuring device comprises a transverse sliding rail; the longitudinal sliding rail is slidably arranged on the transverse sliding rail; the first clamp is used for clamping the control surface and is slidably arranged on the longitudinal sliding rail; the first linear displacement sensor is arranged on the longitudinal sliding rail; the second linear displacement sensor is arranged on the first clamp; the measuring method based on the device comprises the following steps: s1, giving a control command to control the control surface of the aircraft to deflect upwards or downwards; s2, according to data measured by the first linear displacement sensor, obtaining transverse displacement X of the outer end of the control surface of the aircraft, and according to data measured by the second linear displacement sensor, obtaining longitudinal displacement Y of the outer end of the control surface of the aircraft; and S3, obtaining a deflection angle A=2 arctan (X/Y) of the control surface of the aircraft according to the triangle principle. The invention greatly improves the safety, has simpler operation and high measurement precision, and does not need on-site calibration.
Description
Technical Field
The invention relates to the technical field of angle measurement, in particular to an aircraft control surface measuring device and an aircraft control surface measuring method.
Background
Aircraft include many control surfaces such as a horizontal tail, aileron, flap, front wing, and the like. The control surface is a control surface of the aircraft, and the deflection angle of the control surface of the aircraft is required to be continuously adjusted in the flight process so as to control the attitude and the flight track of the aircraft; in the debugging process of the aircraft control system, not only is the deflection angle and the stroke of each direction input mechanism of the control system required to be accurately debugged and measured, but also the deflection angle of each corresponding control surface is required to be debugged and measured, and if the working angle of the deflection control surface is not in the specified numerical range, the corresponding adjusting mechanism is required to be readjusted to meet the specified value.
The traditional control surface measurement usually adopts a chord length method or a heavy hammer method; the chord length method has the advantages that the calibration process is complicated, the positioning reference error is larger, the calibration precision is lower, and workers need to operate in high air for a long time, so that the method is quite unsafe; the heavy hammer method has the advantages of complicated calibration process, low calibration precision, high-altitude operation and unsafe operation.
In view of this, new methods for measuring the control surface of an aircraft are currently presented, for example, a method for measuring the deflection angle of the control surface of an aircraft is disclosed in the patent with publication number of CN112729221a, and a method for measuring the control surface of an aircraft is also disclosed in the university of western-style industry, for example, 2 nd month in 2006, by author He Sen, and in the university of the national institute of technology for calibrating aircraft elevators, ailerons and flap angle, both of which adopt methods based on visual image technology, but the methods are complex and require the establishment of an analytical calculation model. Therefore, a more simple control surface measuring device and a measuring method thereof are needed.
Disclosure of Invention
The invention aims to provide an aircraft control surface measuring device and an aircraft control surface measuring method, which greatly improve the safety, are simpler to operate, have high measuring precision and do not need on-site calibration.
The embodiment of the invention is realized by the following technical scheme:
the invention provides two aircraft control surface measuring devices:
the first aircraft control surface measuring device provided by the invention comprises a transverse sliding rail; the longitudinal sliding rail is slidably arranged on the transverse sliding rail; the first clamp is used for clamping the control surface and is slidably arranged on the longitudinal sliding rail; the first linear displacement sensor is arranged on the longitudinal sliding rail; and the second linear displacement sensor is arranged on the first clamp.
Further, the device also comprises a data processing unit and a terminal display unit, wherein the first linear displacement sensor and the second linear displacement sensor are electrically connected with the data processing unit, and the terminal display unit is electrically connected with the data processing unit.
Further, a second support is arranged at the bottom of the transverse sliding rail, and the transverse sliding rail is rotationally connected with the second support, so that the transverse sliding rail can rotate around the second support in a transverse plane.
Further, a plurality of adjusting column feet are arranged on the support, and the adjusting column feet are connected with the support through threads.
The second aircraft control surface measuring device provided by the invention comprises a transverse sliding rail; the longitudinal sliding rail is slidably arranged on the transverse sliding rail; the second clamp is used for clamping the control surface; the force application mechanism is used for applying a pushing force or a pulling force to the second clamp in the longitudinal direction and is slidably arranged on the longitudinal sliding rail; the force sensor is connected between the second clamp and the force application mechanism; the first linear displacement sensor is arranged on the longitudinal sliding rail; the second linear displacement sensor is arranged on the force application mechanism.
Further, the device also comprises a data processing unit and a terminal display unit, wherein the first linear displacement sensor, the second linear displacement sensor and the force sensor are electrically connected with the data processing unit, and the terminal display unit is electrically connected with the data processing unit.
Further, the force application mechanism comprises a push rod, a screw nut linear pair, a first support and a motor, wherein the first support is slidably arranged on the longitudinal sliding rail, the motor is arranged on the first support and is connected with a screw of the screw nut pair, the push rod is connected with a nut of the screw nut linear pair, and the force sensor is connected between the push rod and the second clamp.
Further, a second support is arranged at the bottom of the transverse sliding rail, and the transverse sliding rail is rotationally connected with the second support, so that the transverse sliding rail can rotate around the second support in a transverse plane.
The invention also provides a first aircraft control surface measuring method based on the first aircraft control surface measuring device, which comprises the following steps:
s1, giving a control command to control the control surface of the aircraft to deflect upwards or downwards;
s2, according to data measured by the first linear displacement sensor, obtaining transverse displacement X of the outer end of the control surface of the aircraft, and according to data measured by the second linear displacement sensor, obtaining longitudinal displacement Y of the outer end of the control surface of the aircraft;
and S3, obtaining a deflection angle A=2 arctan (X/Y) of the control surface of the aircraft according to the triangle principle.
The invention also provides a second aircraft control surface measuring method based on the second aircraft control surface measuring device, which comprises the following steps:
s1, applying a pushing force or a pulling force to a second clamp in the longitudinal direction through a force application mechanism, and measuring the pulling force or the pushing force F through a force sensor;
s2, according to data measured by the first linear displacement sensor, obtaining transverse displacement X of the outer end of the aircraft control surface under the action of the pulling force or the pushing force F, and according to data measured by the second linear displacement sensor, obtaining longitudinal displacement Y of the outer end of the aircraft control surface under the action of the pulling force or the pushing force F;
and S3, obtaining a clearance angle A' =2 arctan (X/Y) of the control surface of the aircraft under the action of the pulling force or the pushing force F according to the triangle principle.
The invention has at least the following advantages and beneficial effects:
1. the two aircraft measuring devices provided by the invention have simple structures, do not need the high-altitude operation of measuring personnel, and greatly improve the measuring safety;
2. the first aircraft control surface measuring method provided by the invention can measure the deflection angle of the aircraft control surface, the second aircraft control surface measuring method provided by the invention can measure the clearance angle of the aircraft control surface, and the transverse displacement X of the outer end of the aircraft control surface and the longitudinal displacement Y of the outer end of the aircraft control surface are obtained only according to the first linear displacement sensor and the second linear displacement sensor during measurement, and the deflection angle (clearance angle) A (A')=2 arctan (X/Y) is obtained by combining a triangle principle.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural diagram of an aircraft control surface measuring device according to a first embodiment;
FIG. 2 is an enlarged view of FIG. 1 at D;
FIG. 3 is a schematic view of the connection structure of the first support and the turntable;
FIG. 4 is a cross-sectional view of the connection structure of the first support and the turntable;
FIG. 5 is a schematic diagram of the measurement principle;
FIG. 6 is a control schematic diagram of the first embodiment;
fig. 7 is a schematic structural diagram of an aircraft control surface measurement device according to a second embodiment;
FIG. 8 is an enlarged view at E in FIG. 7;
FIG. 9 is a schematic view of a second clamp;
fig. 10 is a control schematic diagram of the second embodiment;
icon: 1-supporting platform, 2-transverse sliding rail, 3-longitudinal sliding rail, 4-first clamp, 401-first connecting block, 402-first clamping block, 403-first adjusting rod, 404-first pressing block, 5-first linear displacement sensor, 6-second linear displacement sensor, 7-second support, 8-turntable, 9-adjusting column foot, 10-data processing unit, 101-first acquisition module, 102-second acquisition module, 103-third acquisition module, 104-AC/DC power module, 105-PLC control module, 11-terminal display unit, 12-force application mechanism, 1201-push rod, 1202-lead screw nut linear pair, 1203-first support, 13-second clamp, 1301-second clamping block, 1302-second adjusting rod, 1303-second pressing block, 14-force sensor, 15-second connecting block, 16-plane rudder surface.
Detailed Description
Example 1
The embodiment provides an aircraft control surface 16 measuring device, including horizontal slide rail 2, the bottom of horizontal slide rail 2 is equipped with second support 7, and second support 7 bottom sets up supporting platform 1, and supporting platform 1 plays to raise whole height to and play the effect that supports whole measuring device, supporting platform 1's height designs according to actual demand.
The transverse sliding rail 2 is rotationally connected with the second support 7, so that the transverse sliding rail 2 can rotate around the second support 7 in a transverse plane, specifically, the top of the second support 7 is connected with a turntable 8 through a bearing, the transverse sliding rail 2 is arranged on the top surface of the turntable 8, the bearing adopts a pair of high-precision angular contact ball bearings, the bearing can eliminate measurement errors caused by gaps through eliminating gaps, and because the rolling bodies of the bearing are balls, the friction moment is small, the measurement errors are reduced, the turntable 8 and the support are manufactured by processing aviation aluminum with higher tensile strength, and the weight is reduced under the condition of ensuring the rigidity.
Be equipped with a plurality of regulation column feet 9 on the support, adjust column feet 9 and support and pass through threaded connection, adjust different regulation column feet 9 through rotating, can reach the effect that reaches the leveling, avoid having slight slope and then leading to whole unstability because of the uneven supporting platform 1 that leads to in ground, be equipped with two nuts in support bottom position on adjusting column feet 9, play the locking effect, improve the security.
The transverse sliding rail 2 is provided with a slidable longitudinal sliding rail 3, the longitudinal sliding rail 3 is provided with a first clamp 4 capable of sliding for clamping a control surface, the first clamp 4 comprises a first connecting block 401 and a first clamping block 402 with a clamping groove, the first clamping block 402 is fixedly connected with the first connecting block 401, one side wall of the clamping groove is connected with a first adjusting rod 403 through threads, one end of the first adjusting rod 403 in the clamping groove is provided with a first pressing block 404, and when the aircraft control surface 16 is used, one side of the aircraft control surface is abutted against one side wall of the clamping groove, and the other side of the aircraft control surface is pressed by the first pressing block 404.
The longitudinal sliding rail 3 is provided with a first linear displacement sensor 5, the first clamp 4 is provided with a second linear displacement sensor 6, and specifically, the first linear displacement sensor 5 is arranged at one side of the bottom end of the longitudinal sliding rail 3, moves along the transverse sliding rail 2 along with the longitudinal sliding rail 3, and measures transverse displacement; the second linear displacement is arranged on the first connecting block 401 of the first clamp 4, and the second linear displacement is measured along the longitudinal sliding rail 3 along with the sliding of the first connecting block 401.
In this embodiment, the electronic device further includes a data processing unit 10 and a terminal display unit 11, where the first linear displacement sensor 5 and the second linear displacement sensor 6 are electrically connected to the data processing unit 10, and the terminal display unit 11 is electrically connected to the data processing unit 10.
The data processing unit 10 includes a first acquisition module 101 for acquiring signals of the first linear displacement sensor 5, a second acquisition module 102 for acquiring signals of the second linear displacement sensor 6, an AC/DC power module 104 and a PLC control module 105, where the AC/DC power module 104 is used to supply power to the first acquisition module 101, the second acquisition module 102 and the PLC control module 105, the PLC control module 105 is electrically connected with the first acquisition module 101 and the second acquisition module 102, processes data acquired by the first acquisition module 101 and the second acquisition module 102, generates results, and sends the results to the terminal display unit 11 through USB or ethernet, and the terminal display unit 11 may be an industrial personal computer with a display device, and is capable of controlling a control surface and processing measurement signals in real time, and displaying, storing and outputting the data according to user requirements.
The embodiment also provides a method for measuring the aircraft control surface 16 based on the measuring device, specifically, the method can measure the deflection angle A of the aircraft control surface 16, and the method comprises the following steps:
s1, giving a control command to control the control surface 16 of the aircraft to deflect upwards or downwards;
s2, when the aircraft control surface 16 deflects, the first clamp 4 is driven to move upwards or downwards along the longitudinal sliding block, and meanwhile, the longitudinal sliding block is driven to move leftwards or rightwards along the transverse sliding rail 2, so that the transverse displacement X of the outer end of the aircraft control surface 16 is obtained according to data measured by the first linear displacement sensor 5, and the longitudinal displacement Y of the outer end of the aircraft control surface 16 is obtained according to data measured by the second linear displacement sensor 6;
s3, referring to FIG. 5, there is +.a=tan (X/Y) according to the trigonometric function;
according to the angular relationship of the right triangle, the angle a plus minus B=90 degrees minus A plus minus B plus minus a is not difficult to obtain, and the angle a plus minus A plus minus 2 is obtained;
the deflection angle a=2 arctan (X/Y) of the aircraft control surface 16 can be obtained from the arctangent function.
Example two
The embodiment provides another aircraft control surface 16 measuring device, including horizontal slide rail 2, the bottom of horizontal slide rail 2 is equipped with second support 7, and second support 7 bottom sets up supporting platform 1, and supporting platform 1 plays to raise whole height to and play the effect of supporting whole measuring device, supporting platform 1's height design according to actual demand.
The transverse sliding rail 2 is rotationally connected with the second support 7, so that the transverse sliding rail 2 can rotate around the second support 7 in a transverse plane, specifically, the top of the second support 7 is connected with a turntable 8 through a bearing, the transverse sliding rail 2 is arranged on the top surface of the turntable 8, the bearing adopts a pair of high-precision angular contact ball bearings, the bearing can eliminate measurement errors caused by gaps through eliminating gaps, and because the rolling bodies of the bearing are balls, the friction moment is small, the measurement errors are reduced, the turntable 8 and the support are manufactured by processing aviation aluminum with higher tensile strength, and the weight is reduced under the condition of ensuring the rigidity.
Be equipped with a plurality of regulation column feet 9 on the support, adjust column feet 9 and support and pass through threaded connection, adjust different regulation column feet 9 through rotating, can reach the effect that reaches the leveling, avoid having slight slope and then leading to whole unstability because of the uneven supporting platform 1 that leads to in ground, be equipped with two nuts in support bottom position on adjusting column feet 9, play the locking effect, improve the security.
The horizontal slide rail 2 is provided with a slidable longitudinal slide rail 3, the longitudinal slide rail 3 is provided with a slidable force application mechanism 12, the force application mechanism 12 comprises a push rod 1201, a screw nut linear pair 1202, a first support 1203 and a motor, the first support 1203 is slidably arranged on the longitudinal slide rail 3, further, the first support 1203 is connected with a second connecting block 15, the second connecting block 15 is slidably arranged on the longitudinal slide rail 3, the motor is arranged on the first support 1203 and is connected with a screw of the screw nut pair, in order to save space, the motor is arranged in the first support 1203, the push rod 1201 is connected with a nut of the screw nut linear pair 1202, the force sensor 14 is connected between the push rod 1201 and the second clamp 13, and when in use, the push rod 1201 can be driven by the motor to move along a screw of the screw nut linear pair 1202, so that pushing force or pulling force is applied to the aircraft control surface 16.
The second clamp 13 comprises a second clamping block 1301 with a clamping groove, the second clamping block 1301 is fixedly connected with a second connecting block 15, a second adjusting rod 1302 is connected to one side wall of the clamping groove through threads, a second pressing block 1303 is arranged at one end of the second adjusting rod 1302 in the clamping groove, and when the second clamp is used, one side of an aircraft control surface 16 is abutted to one side wall of the clamping groove, and the other side of the aircraft control surface is pressed through the second pressing block 1303.
The longitudinal sliding rail 3 is provided with a first linear displacement sensor 5, the force application mechanism 12 is provided with a second linear displacement sensor 6, specifically, the first linear displacement sensor 5 is arranged at one side of the bottom end of the longitudinal sliding rail 3, and moves along the transverse sliding rail 2 along with the longitudinal sliding rail 3 to measure transverse displacement; the second linear displacement is arranged on the second connecting block 15, and the second linear displacement is measured along the longitudinal sliding rail 3 along with the second connecting block 15.
In this embodiment, the electronic device further includes a data processing unit 10 and a terminal display unit 11, where the first linear displacement sensor 5 and the second linear displacement sensor 6 are electrically connected to the data processing unit 10, and the terminal display unit 11 is electrically connected to the data processing unit 10.
The data processing unit 10 comprises a first acquisition module 101 for acquiring signals of the first linear displacement sensor 5, a second acquisition module 102 for acquiring signals of the second linear displacement sensor 6, a third acquisition module 103 for acquiring signals of the force sensor 14, a servo driver, an AC/DC power module 104 and a PLC control module 105.
The AC/DC power module 104 is configured to supply power to the first collecting module 101, the second collecting module 102, the third collecting module 103, the servo driver and the PLC control module 105, where the PLC control module 105 is electrically connected with the first collecting module 101, the second collecting module 102, the third collecting module 103 and the servo driver, processes data collected by the first collecting module 101 and the second collecting module 102, generates a result, sends the result to the terminal display unit 11 through USB or ethernet, and performs closed-loop calculation on a signal collected by the third collecting module 103, generates a guiding quantity, controls the servo motor, and completes closed-loop driving to achieve a required thrust or pulling force F for a rudder surface.
The terminal display unit 11 may be an industrial personal computer with a display device, and is capable of controlling a control surface, processing measurement signals in real time, and displaying, storing and outputting data according to user requirements.
The embodiment also provides a method for measuring the aircraft control surface 16 based on the measuring device, specifically, the method can measure the clearance angle A' of the aircraft control surface 16, and the method comprises the following steps:
s1, pushing force or pulling force in the longitudinal direction is applied to a second clamp 13 through a force application mechanism 12, the pushing force or pulling force acts on an aircraft control surface 16 through the second clamp 13, and the pulling force or pushing force F is measured through a force sensor 14;
s2, when the aircraft control surface 16 receives thrust or tension, the aircraft control surface 16 deflects due to the existence of a gap of the aircraft control surface 16, drives the second clamp 13 to move upwards or downwards along the longitudinal sliding block, and simultaneously drives the longitudinal sliding block to move leftwards or rightwards along the transverse sliding rail 2, so that the transverse displacement X of the outer end of the aircraft control surface 16 is obtained according to data measured by the first linear displacement sensor 5, and the longitudinal displacement Y of the outer end of the aircraft control surface 16 is obtained according to data measured by the second linear displacement sensor 6;
s3, obtaining a clearance angle A' =2 arctan (X/Y) of the aircraft control surface 16 under the action of the pulling force or the pushing force F according to a triangle principle (the specific principle is detailed in the first embodiment and not repeated in the first embodiment).
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An aircraft control surface measurement device, comprising:
a transverse slide rail (2);
the longitudinal sliding rail (3) is slidably arranged on the transverse sliding rail (2);
the first clamp (4) is used for clamping the control surface, and the first clamp (4) is slidably arranged on the longitudinal sliding rail (3);
the first linear displacement sensor (5) is arranged on the longitudinal sliding rail (3);
and the second linear displacement sensor (6) is arranged on the first clamp (4).
2. The aircraft control surface measurement device of claim 1, wherein: the device further comprises a data processing unit (10) and a terminal display unit (11), wherein the first linear displacement sensor (5) and the second linear displacement sensor (6) are electrically connected with the data processing unit (10), and the terminal display unit (11) is electrically connected with the data processing unit (10).
3. The aircraft control surface measurement device according to claim 1 or 2, characterized in that: the bottom of the transverse sliding rail (2) is provided with a second support (7), and the transverse sliding rail (2) is rotationally connected with the second support (7) so that the transverse sliding rail (2) can rotate around the second support (7) in a transverse plane.
4. The aircraft control surface measurement device of claim 3, wherein: the support is provided with a plurality of adjusting column bases (9), and the adjusting column bases (9) are connected with the support through threads.
5. An aircraft control surface measurement device, comprising:
a transverse slide rail (2);
the longitudinal sliding rail (3) is slidably arranged on the transverse sliding rail (2);
the second clamp (13) is used for clamping the control surface;
the force application mechanism (12) is used for applying a pushing force or a pulling force to the second clamp (13) in the longitudinal direction, and the force application mechanism (12) is slidably arranged on the longitudinal sliding rail (3);
a force sensor (14) connected between the second clamp (13) and the force application mechanism (12);
the first linear displacement sensor (5) is arranged on the longitudinal sliding rail (3);
and a second linear displacement sensor (6) provided on the force application mechanism (12).
6. The aircraft control surface measurement device of claim 5, wherein: the device further comprises a data processing unit (10) and a terminal display unit (11), wherein the first linear displacement sensor (5), the second linear displacement sensor (6) and the force sensor (14) are electrically connected with the data processing unit (10), and the terminal display unit (11) is electrically connected with the data processing unit (10).
7. The aircraft control surface measurement device of claim 5, wherein: the force application mechanism (12) comprises a push rod (1201), a screw nut linear pair (1202), a first support (1203) and a motor, wherein the first support (1203) is slidably arranged on the longitudinal sliding rail (3), the motor is arranged on the first support (1203) and connected with a screw of the screw nut pair, the push rod (1201) is connected with a nut of the screw nut linear pair (1202), and the force sensor (14) is connected between the push rod (1201) and the second clamp (13).
8. The aircraft control surface measurement device of claim 5, 6 or 7, wherein: the bottom of the transverse sliding rail (2) is provided with a second support (7), and the transverse sliding rail (2) is rotationally connected with the second support (7) so that the transverse sliding rail (2) can rotate around the second support (7) in a transverse plane.
9. An aircraft control surface measuring method based on an aircraft control surface measuring device according to any one of claims 1-4, characterized in that the method comprises the steps of:
s1, giving a control command to control the control surface (16) of the aircraft to deflect upwards or downwards;
s2, according to the data measured by the first linear displacement sensor (5), obtaining the transverse displacement X of the outer end of the aircraft control surface (16), and according to the data measured by the second linear displacement sensor (6), obtaining the longitudinal displacement Y of the outer end of the aircraft control surface (16);
and S3, obtaining a deflection angle A=2 arctan (X/Y) of the aircraft control surface (16) according to a triangle principle.
10. An aircraft control surface measuring method based on an aircraft control surface measuring device according to any one of claims 5-8, characterized in that the method comprises the steps of:
s1, applying a pushing force or a pulling force to a second clamp (13) in the longitudinal direction through a force application mechanism (12), and measuring the pulling force or the pushing force F through a force sensor (14);
s2, according to the data measured by the first linear displacement sensor (5), obtaining the transverse displacement X of the outer end of the aircraft control surface (16) under the action of the pulling force or the pushing force F, and according to the data measured by the second linear displacement sensor (6), obtaining the longitudinal displacement Y of the outer end of the aircraft control surface (16) under the action of the pulling force or the pushing force F;
and S3, obtaining a clearance angle A' =2 arctan (X/Y) of the aircraft control surface (16) under the action of the pulling force or the pushing force F according to a triangle principle.
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