阅读说明：本技术 一种飞机舵面测量装置及测量方法 (Airplane control surface measuring device and measuring method ) 是由 熊皑 付克昌 李杨 任晓坜 于 2021-08-25 设计创作，主要内容包括：本发明提供了一种飞机舵面测量装置及测量方法,测量装置包括横向滑轨；纵向滑轨,可滑动地设于所述横向滑轨上；用于夹持舵面的第一夹具,第一夹具可滑动地设于所述纵向滑轨上；第一直线位移传感器,设于所述纵向滑轨上；第二直线位移传感器,设于所述第一夹具上；基于该装置的测量方法包括如下步骤：S1、给出控制命令,控制飞机舵面往上或往下进行偏转；S2、根据第一直线位移传感器测得的数据,得出飞机舵面外端的横向位移X,根据第二直线位移传感器测得的数据,得出飞机舵面外端的纵向位移Y；S3、根据三角原理得出飞机舵面的偏转角A＝2arctan(X/Y)。本发明大大提高了安全性,操作更加简单,测量精度高,无需现场校准。(The invention provides a measuring device and a measuring method for an airplane control surface, wherein the measuring device comprises a transverse slide rail; the longitudinal slide rail is slidably arranged on the transverse slide rail; the first clamp is used for clamping the control surface and can be arranged on the longitudinal slide rail in a sliding manner; the first linear displacement sensor is arranged on the longitudinal slide 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 airplane to deflect upwards or downwards; s2, obtaining the transverse displacement X of the outer end of the control surface of the airplane according to the data measured by the first linear displacement sensor, and obtaining the longitudinal displacement Y of the outer end of the control surface of the airplane according to the data measured by the second linear displacement sensor; and S3, obtaining the deflection angle A of the airplane control surface by the triangle principle to be 2arctan (X/Y). The invention greatly improves the safety, has simpler operation and high measurement precision, and does not need field calibration.)

1. An aircraft control surface measurement device, comprising:

a transverse slide rail (2);

the longitudinal slide rail (3) is slidably arranged on the transverse slide rail (2);

the first clamp (4) is used for clamping the control surface, and the first clamp (4) is slidably arranged on the longitudinal slide rail (3);

the first linear displacement sensor (5) is arranged on the longitudinal slide rail (3);

and the second linear displacement sensor (6) is arranged on the first clamp (4).

2. Aircraft control surface measuring device according to claim 1, characterized in that: the sensor is characterized by further comprising 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. Aircraft control surface measuring 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 rotatably 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. An aircraft control surface measurement device according to claim 3, wherein: the support is provided with a plurality of adjusting column feet (9), and the adjusting column feet (9) are connected with the support through threads.

5. An aircraft control surface measurement device, comprising:

a transverse slide rail (2);

the longitudinal slide rail (3) is slidably arranged on the transverse slide rail (2);

a second clamp (13) for clamping the control surface;

the force application mechanism (12) is used for applying pushing force or pulling force in the longitudinal direction to the second clamp (13), and the force application mechanism (12) is slidably arranged on the longitudinal slide 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 slide rail (3);

and the second linear displacement sensor (6) is arranged on the force application mechanism (12).

6. Aircraft control surface measuring device according to claim 5, characterized in that: the sensor is characterized by further comprising 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. Aircraft control surface measuring device according to claim 5, characterized in that: 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 sliding rail (3), the motor is installed on the first support (1203) and connected with a screw of the screw-nut linear 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. Aircraft control surface measuring device according to claim 5, 6 or 7, 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 rotatably 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 the aircraft control surface measuring device of any one of claims 1-4, characterized by comprising the following steps:

s1, giving a control command to control the airplane control surface (16) to deflect upwards or downwards;

s2, obtaining the transverse displacement X of the outer end of the airplane control surface (16) according to the data measured by the first linear displacement sensor (5), and obtaining the longitudinal displacement Y of the outer end of the airplane control surface (16) according to the data measured by the second linear displacement sensor (6);

and S3, obtaining the deflection angle A of the airplane control surface (16) by 2arctan (X/Y) according to the triangle principle.

10. An aircraft control surface measuring method based on the aircraft control surface measuring device of any one of claims 5-8, characterized by comprising the following steps:

s1, applying a pushing force or a pulling force in the longitudinal direction to the second clamp (13) through the force application mechanism (12), and measuring the pulling force or the pushing force F through the force sensor (14);

s2, obtaining the transverse displacement X of the outer end of the airplane control surface (16) under the action of the pulling force or the pushing force F according to the data measured by the first linear displacement sensor (5), and obtaining the longitudinal displacement Y of the outer end of the airplane control surface (16) under the action of the pulling force or the pushing force F according to the data measured by the second linear displacement sensor (6);

and S3, obtaining the clearance angle A 'of the airplane control surface (16) under the action of the pulling force or the pushing force F according to the triangle principle, wherein the clearance angle A' is 2arctan (X/Y).

Technical Field

The invention relates to the technical field of angle measurement, in particular to a device and a method for measuring an airplane control surface.

Background

Aircraft include a number of control surfaces such as horizontal tails, ailerons, flaps, front wings, and the like. The control surface is the control surface of the airplane, and the deflection angle of the control surface of the airplane needs to be continuously adjusted in the flying process to control the attitude and the flying track of the airplane; in the debugging process of the aircraft control system, not only the deflection angles and the strokes of the input mechanisms in all directions of the control system need to be accurately debugged and measured, but also the deflection angles of all corresponding control surfaces need to be debugged and measured, and if the working angles of the deflected control surfaces are not within the specified numerical range, the corresponding adjusting mechanisms need to be readjusted to meet the specified values.

The traditional control surface measurement usually adopts a chord length method or a heavy hammer method; the chord length method has the disadvantages of complicated calibration process, large positioning reference error, low calibration precision, and unsafe condition because workers need to work in the high altitude for a long time; the weight-drop method is also complicated in calibration process, low in calibration precision, safe in operation at high altitude and the like.

In view of this, some new methods have been proposed to measure the control surface of the aircraft, for example, patent publication No. CN112729221A discloses a method for measuring the deflection angle of the control surface of the aircraft, and as shown in the book of mastership academic papers, which is included in the university of western medicine in 2006 month 2 and is written by heson and entitled "research on calibration techniques of elevator, aileron and flap corner), a method for measuring the control surface of the aircraft is also disclosed. Therefore, a device and a method for measuring a control surface with simpler measurement are urgently needed to be provided.

Disclosure of Invention

The invention aims to provide a measuring device and a measuring method for an airplane control surface, which greatly improve the safety, are simpler to operate and high in measuring precision and do not need field calibration.

The embodiment of the invention is realized by the following technical scheme:

the invention provides two airplane control surface measuring devices:

the invention provides a first airplane control surface measuring device, which comprises a transverse slide rail; the longitudinal slide rail is slidably arranged on the transverse slide rail; the first clamp is used for clamping the control surface and can be arranged on the longitudinal slide rail in a sliding manner; the first linear displacement sensor is arranged on the longitudinal slide rail; and the second linear displacement sensor is arranged on the first clamp.

Furthermore, 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.

Furthermore, a second support is arranged at the bottom of the transverse sliding rail, and the transverse sliding rail is rotatably connected with the second support, so that the transverse sliding rail can rotate around the second support in a transverse plane.

Furthermore, a plurality of adjusting column feet are arranged on the support, and the adjusting column feet are connected with the support through threads.

The invention provides a second airplane control surface measuring device, which comprises a transverse slide rail; the longitudinal slide rail is slidably arranged on the transverse slide rail; the second clamp is used for clamping the control surface; the force application mechanism is used for applying pushing force or pulling force in the longitudinal direction to the second clamp, and can be arranged on the longitudinal slide rail in a sliding mode; the force sensor is connected between the second clamp and the force application mechanism; the first linear displacement sensor is arranged on the longitudinal slide rail; and the second linear displacement sensor is arranged on the force application mechanism.

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, the first support is slidably arranged on the longitudinal slide rail, the motor is installed on the first support and connected with a screw of the screw-nut linear 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.

Furthermore, a second support is arranged at the bottom of the transverse sliding rail, and the transverse sliding rail is rotatably 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 airplane control surface measuring method, which is based on the first airplane control surface measuring device and comprises the following steps:

s1, giving a control command to control the control surface of the airplane to deflect upwards or downwards;

s2, obtaining the transverse displacement X of the outer end of the control surface of the airplane according to the data measured by the first linear displacement sensor, and obtaining the longitudinal displacement Y of the outer end of the control surface of the airplane according to the data measured by the second linear displacement sensor;

and S3, obtaining the deflection angle A of the airplane control surface by the triangle principle to be 2arctan (X/Y).

The invention also provides a second aircraft control surface measuring method, which is based on the second aircraft control surface measuring device and comprises the following steps:

s1, applying a pushing force or a pulling force in the longitudinal direction to the second clamp through the force application mechanism, and measuring the pulling force or the pushing force F through the force sensor;

s2, obtaining the transverse displacement X of the outer end of the control surface of the airplane under the action of the pulling force or the pushing force F according to the data measured by the first linear displacement sensor, and obtaining the longitudinal displacement Y of the outer end of the control surface of the airplane under the action of the pulling force or the pushing force F according to the data measured by the second linear displacement sensor;

and S3, obtaining the clearance angle A 'of the airplane control surface under the action of the pulling force or the pushing force F according to the triangle principle, wherein the clearance angle A' is 2arctan (X/Y).

The invention has at least the following advantages and beneficial effects:

1. the two airplane measuring devices provided by the invention have simple structures, do not need measuring personnel to work high above the ground, and greatly improve the measuring safety;

2. the first airplane control surface measuring method provided by the invention can measure the deflection angle of the airplane control surface, the second airplane control surface measuring method can measure the clearance angle of the airplane control surface, the transverse displacement X of the outer end of the airplane control surface and the longitudinal displacement Y of the outer end of the airplane control surface are obtained according to the first linear displacement sensor and the second linear displacement sensor during measurement, and the deflection angle (clearance angle) A (A') is 2arctan (X/Y) by combining the trigonometric principle, so that the measuring method is simple, the measuring precision is high, and the field calibration is not needed.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic structural diagram of an aircraft control surface measuring device according to an embodiment;

FIG. 2 is an enlarged view of FIG. 1 at D;

FIG. 3 is a schematic view of a connection structure of the first support and the turntable;

FIG. 4 is a sectional view of a coupling structure of a first holder and a turntable;

FIG. 5 is a schematic view of the measurement principle;

FIG. 6 is a control schematic diagram according to a first embodiment;

FIG. 7 is a schematic structural diagram of an aircraft control surface measuring device according to a second embodiment;

FIG. 8 is an enlarged view at E in FIG. 7;

FIG. 9 is a schematic structural view of a second fixture;

FIG. 10 is a control schematic diagram of the second embodiment;

icon: 1-a supporting platform, 2-a transverse sliding rail, 3-a longitudinal sliding rail, 4-a first clamp, 401-a first connecting block, 402-a first clamping block, 403-a first adjusting rod, 404-a first pressing block, 5-a first linear displacement sensor, 6-a second linear displacement sensor, 7-a second support, 8-a rotary table, 9-an adjusting column base, 10-a data processing unit, 101-a first acquisition module, 102-a second acquisition module, 103-a third acquisition module, 104-an AC/DC power supply module, 105-a PLC control module, 11-a terminal display unit, 12-a force application mechanism, 1201-a push rod, 1202-a lead screw nut linear pair, 1203-a first support, 13-a second clamp and 1301-a second clamping block, 1302-a second adjusting rod, 1303-a second press block, 14-a force sensor, 15-a second connecting block and 16-an aircraft control surface.

Detailed Description

Example one

The embodiment provides an aircraft control surface 16 measuring device, including transverse slide rail 2, transverse slide rail 2's bottom is equipped with second support 7, and second support 7 bottom sets up supporting platform 1, and supporting platform 1 plays and raises the whole height to and play the effect of supporting whole measuring device, and supporting platform 1's height is designed according to actual demand.

The transverse sliding rail 2 is rotatably connected with the second support 7, so that the transverse sliding rail 2 can rotate around the second support 7 in a transverse plane, concretely, the top of the second support 7 is connected with a turntable 8 through a bearing, the transverse sliding rail 2 is installed on the top surface of the turntable 8, the bearing adopts a pair of high-precision angle contact ball bearings, the bearing can eliminate measurement errors caused by gaps by eliminating the gaps, because the rolling bodies of the bearing are balls, the friction torque is very small, the measurement errors are also reduced, the turntable 8 and the supports are manufactured by adopting 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 bases 9 on the support, adjust column base 9 and support and pass through threaded connection, adjust different regulation column base 9 through rotating, can reach the effect of leveling, avoid leading to supporting platform 1 to have slight slope and then lead to wholly not steady because of the ground is uneven, be equipped with two nuts in support bottom position on adjusting column base 9, play the locking effect, improve the security.

Be equipped with slidable vertical slide rail 3 on the horizontal slide rail 2, be equipped with the first anchor clamps 4 of slidable on vertical slide rail 3 for the centre gripping control surface, concretely, first anchor clamps 4 include first splice 401 and have the first splice 402 of centre gripping groove, first splice 402 and first splice 401 fixed connection, there is first regulation pole 403 a lateral wall in centre gripping groove through threaded connection, the one end of first regulation pole 403 in the centre gripping inslot is equipped with first briquetting 404, during the use, one side of aircraft control surface 16 and a lateral wall butt in centre gripping groove, the opposite side compresses tightly through first briquetting 404.

The longitudinal slide 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 on one side of the bottom end of the longitudinal slide rail 3 and moves along the transverse slide rail 2 along with the longitudinal slide rail 3 to measure transverse displacement; the second linear displacement is arranged on the first connecting block 401 of the first clamp 4, slides along the longitudinal slide rail 3 along with the first connecting block 401, and measures the longitudinal displacement.

In this implementation, the sensor further comprises a data processing unit 10 and a terminal display unit 11, the first linear displacement sensor 5 and the second linear displacement sensor 6 are both 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, an AC/DC power module 104 and a PLC control module 105, wherein the AC/DC power module 104 is used for supplying 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, the data acquired by the first acquisition module 101 and the second acquisition module 102 are processed and a result is generated, the result is sent to the terminal display unit 11 through a USB or an Ethernet, the terminal display unit 11 can be an industrial personal computer with display equipment, the industrial personal computer can control a rudder face and process measurement signals in real time, and the data are displayed, stored and output according to user requirements.

The embodiment also provides an aircraft control surface 16 measuring method based on the measuring device, and 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 airplane control surface 16 to deflect upwards or downwards;

s2, when the airplane control surface 16 deflects, the first clamp 4 is driven to move upwards or downwards along the longitudinal slide block, and meanwhile, the longitudinal slide block is driven to move leftwards or rightwards along the transverse slide rail 2, so that the transverse displacement X of the outer end of the airplane control surface 16 is obtained according to the data measured by the first linear displacement sensor 5, and the longitudinal displacement Y of the outer end of the airplane control surface 16 is obtained according to the data measured by the second linear displacement sensor 6;

s3, referring to fig. 5, there is tan (X/Y) according to the trigonometric function;

according to the angle relation of the right-angled triangle, easily obtaining that < a + < B > is 90 DEG ═ A + < B- < a, and then obtaining that 2 < a ═ A;

the angle of deflection a of the aircraft control surface 16 can be found to be 2arctan (X/Y) from the arctan function.

Example two

The embodiment provides another kind of aircraft control surface 16 measuring device, including transverse slide rail 2, the bottom of transverse slide rail 2 is equipped with second support 7, and second support 7 bottom sets up supporting platform 1, and supporting platform 1 plays and raises the overall height to and play the effect of supporting whole measuring device, and supporting platform 1's height designs according to actual demand.

The transverse sliding rail 2 is rotatably connected with the second support 7, so that the transverse sliding rail 2 can rotate around the second support 7 in a transverse plane, concretely, the top of the second support 7 is connected with a turntable 8 through a bearing, the transverse sliding rail 2 is installed on the top surface of the turntable 8, the bearing adopts a pair of high-precision angle contact ball bearings, the bearing can eliminate measurement errors caused by gaps by eliminating the gaps, because the rolling bodies of the bearing are balls, the friction torque is very small, the measurement errors are also reduced, the turntable 8 and the supports are manufactured by adopting 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 bases 9 on the support, adjust column base 9 and support and pass through threaded connection, adjust different regulation column base 9 through rotating, can reach the effect of leveling, avoid leading to supporting platform 1 to have slight slope and then lead to wholly not steady because of the ground is uneven, be equipped with two nuts in support bottom position on adjusting column base 9, play the locking effect, improve the security.

The transverse 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 disposed 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 disposed on the longitudinal slide rail 3, the motor is mounted on the first support 1203 and connected with a screw of the screw nut linear pair, in order to save space, the motor is arranged inside the ground first support 1203, the push rod 1201 is connected with the 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 the force sensor is used, the push rod 1201 can be driven by a motor to move along a lead screw of the lead screw nut linear pair 1202, so that thrust or tension 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, in the clamping groove, of the second adjusting rod 1302, and when the aircraft rudder face adjusting device is used, one side of the aircraft rudder face 16 is abutted to one side wall of the clamping groove, and the other side of the aircraft rudder face adjusting device is pressed tightly through the second pressing block 1303.

The longitudinal slide 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, and specifically, the first linear displacement sensor 5 is arranged on one side of the bottom end of the longitudinal slide rail 3 and moves along the transverse slide rail 2 along with the longitudinal slide rail 3 to measure transverse displacement; the second linear displacement is arranged on the second connecting block 15 and slides along the longitudinal sliding rail 3 along with the second connecting block 15, and the longitudinal displacement is measured.

In this implementation, the sensor further comprises a data processing unit 10 and a terminal display unit 11, the first linear displacement sensor 5 and the second linear displacement sensor 6 are both 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 supply module 104 and a PLC control module 105.

The AC/DC power module 104 is used for supplying power to the first acquisition module 101, the second acquisition module 102, the third acquisition module 103, the servo driver and the PLC control module 105, the PLC control module 105 is respectively connected with the first acquisition module 101, the second acquisition module 102, the third acquisition module 103 and the servo driver, the data acquired by the first acquisition module 101 and the second acquisition module 102 are processed and a result is generated, the result is sent to the terminal display unit 11 through a USB or an Ethernet, meanwhile, closed-loop calculation is carried out on signals acquired by the third acquisition module 103, a guide quantity is generated to control the servo motor, and closed-loop driving is completed to realize required thrust or tension F for a control surface.

The terminal display unit 11 may be an industrial personal computer with a display device, and can control a control plane, process a measurement signal in real time, and display, store and output data according to user requirements.

The embodiment also provides an aircraft control surface 16 measuring method based on the measuring device, and specifically, the method can measure the clearance angle a' of the aircraft control surface 16, and the method comprises the following steps:

s1, applying a pushing force or a pulling force in the longitudinal direction to the second clamp 13 through the force applying mechanism 12, wherein the pushing force or the pulling force acts on the aircraft control surface 16 through the second clamp 13, and the pulling force or the pushing force F is measured through the force sensor 14;

s2, when the airplane control surface 16 is subjected to thrust or tension, due to the existence of the gap of the airplane control surface 16, the airplane control surface 16 deflects to drive the second clamp 13 to move upwards or downwards along the longitudinal slide block and simultaneously drive the longitudinal slide block to move leftwards or rightwards along the transverse slide rail 2, so that the transverse displacement X of the outer end of the airplane control surface 16 is obtained according to the data measured by the first linear displacement sensor 5, and the longitudinal displacement Y of the outer end of the airplane control surface 16 is obtained according to the data measured by the second linear displacement sensor 6;

s3, obtaining a clearance angle a' of the aircraft control surface 16 under the action of the pulling force or the pushing force F according to a trigonometric principle (the specific principle is described in the first embodiment, which is not described in detail in this embodiment), which is 2arctan (X/Y).

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.