CN113443168A - Device for fixedly detecting clearance of control surface of airplane - Google Patents
Device for fixedly detecting clearance of control surface of airplane Download PDFInfo
- Publication number
- CN113443168A CN113443168A CN202110652010.3A CN202110652010A CN113443168A CN 113443168 A CN113443168 A CN 113443168A CN 202110652010 A CN202110652010 A CN 202110652010A CN 113443168 A CN113443168 A CN 113443168A
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- control surface
- module
- adjusting rod
- clearance
- control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/14—Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
A device for fixedly detecting the clearance of a control surface of an airplane comprises a pressure loading mechanism and an automatic test system loaded with a test program, wherein a control surface clamp in the pressure loading mechanism is of a U-shaped structure, a clamping disc is arranged on the inner side surface of the U-shaped structure, and a rotating handle is arranged on the control surface clamp; the control surface clamp is fixed at the top of the height adjusting rod, the bottom of the height adjusting rod is installed on the support body, a force sensor fixing clamp for installing a force sensor, a motor fixing clamp for installing a servo motor, a laser ranging sensor installing support for installing a laser ranging sensor and an adjusting disc for controlling the height adjusting rod to move up and down are arranged on the height adjusting rod, and the force sensor, the servo motor and the laser ranging sensor are respectively connected with the automatic testing system; the measurement operation is simple and convenient, the applied force can be freely controlled, the continuous change is realized, and the flexibility test requirement can be met.
Description
Technical Field
The invention relates to the technical field of airplane control surface detection, in particular to a device for fixedly detecting the clearance of an airplane control surface.
Background
The control surface is the control surface of the airplane and is responsible for controlling the flight direction of the airplane, and because the parts of the airplane control surface are easy to generate errors in the processing process, the manual assembly process, the fixing process and the like, gaps with different degrees are generated on the airplane control surface. The size of the control surface clearance directly influences the flight performance of the airplane; if the clearance of the control surface of the airplane is out of tolerance, the flight safety of the airplane is seriously influenced.
At present, after the airplane control surface is assembled on the airplane in the assembly and final assembly stages, different forces are exerted on the control surface mainly in an old mode of adding weights, and several corresponding specific acting forces can be exerted on the control surface only according to the fixed weight of the weights.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a device for fixedly detecting the clearance of the control surface of an aircraft, so as to solve the problems in the background art.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a device for fixedly detecting the clearance of an airplane control surface comprises a pressure loading mechanism and an automatic test system loaded with a test program, wherein the pressure loading mechanism comprises a control surface clamp, a force sensor fixing clamp, a motor fixing clamp, a laser ranging sensor mounting bracket, a height adjusting rod and a support body, the control surface clamp is of a U-shaped structure, a clamping disc used for protecting the control surface from being damaged is arranged on the inner side surface of the U-shaped structure, and a rotary handle used for adjusting the clamping state of the control surface and the clamping disc is arranged on the control surface clamp; the control surface fixture is fixed at the top of the height adjusting rod, the bottom of the height adjusting rod is installed on the supporting body, a force sensor fixing clamp used for installing a force sensor, a motor fixing clamp used for installing a servo motor, a laser ranging sensor installing support used for installing a laser ranging sensor and an adjusting disc used for controlling the vertical displacement of the height adjusting rod are arranged on the height adjusting rod, and the force sensor, the servo motor and the laser ranging sensor are respectively connected with an automatic testing system.
In the invention, the clamping disc comprises an upper clamping disc and a lower clamping disc, the upper clamping disc is arranged on the upper surface of the inner side of the control surface clamp, the lower clamping disc is arranged on the lower surface of the inner side of the control surface clamp, and the upper clamping disc and the lower clamping disc are made of flexible materials.
In the invention, the laser ranging sensor mounting bracket is mounted on the height adjusting rod through the ranging adjusting rod, the laser ranging sensor mounting bracket is mounted at the top of the ranging adjusting rod, the adjusting handle is mounted at the bottom of the ranging adjusting rod, the laser ranging sensor collects position information of a control surface in real time, the position of a target point of the tested control surface is obtained in a laser ranging mode, after the control surface deflects, the position of the target point in space changes, and the laser ranging sensor transmits the position change information of the control surface to the automatic testing system for corresponding processing to obtain a stroke result.
The support body comprises an upper support plate, a support rod, a lower support plate, universal wheels and an adjustable support, wherein the height adjusting rod is arranged in the middle of the upper support plate, the height adjusting rod is adjusted in a vertically telescopic mode through an adjusting disc, so that the overall position of a control surface clamp and a detected control surface is adjusted and fixed, the upper support plate and the lower support plate are fixed through the support rod to bear the weight of the whole set of pressure loading mechanism, the stability is good, the three universal wheels are arranged at the bottom of the lower support plate, so that the detection device can move on site conveniently, the adjustable support is further arranged at the bottom of the lower support plate, fixing clamping pieces are arranged on the universal wheels, and the detection device is fixed in a horizontal state when in use through adjusting the adjustable support and the fixing clamping pieces.
In the invention, the automatic test system comprises a state selection module, a data transmission module, a data acquisition module, a data monitoring module, a motor control module, a data processing module and a data display module, the test program is loaded on the data processing module, the state selection module, the data transmission module, the data acquisition module, the data monitoring module, the motor control module and the data display module are respectively connected with the data processing module, the servo motor, the force sensor and the laser ranging sensor are respectively connected with the data acquisition module, the motor control module is connected with the servo motor, the test program automatically monitors and judges the magnitude of a force value through the force sensor so as to control the rotation of the servo motor and the displacement of a screw rod, then the magnitude of the applied force of a rudder surface is adjusted, and the laser ranging sensor acquires the position change of the rudder surface after being stressed in real time, and then the data processing module is combined with the data model to generate the stroke change of the target point, and then the force and displacement curve is generated by combining the pulling force or the pressure value acquired by the force sensor, and finally the clearance value of the tested control surface is calculated.
Has the advantages that:
1) the height adjusting rod is controlled by the adjusting disc to move up and down so as to measure the control surfaces of different types of airplanes, and the control surfaces of the airplanes can be installed and fixed in the control surface clamp according to the actual height, so that the application range is wide;
2) the automatic test system can automatically control the servo motor to rotate according to the magnitude of applied target tension/pressure, and convert the rotation into linear displacement of the internal screw rod, the laser ranging sensor collects position information of the control surface in real time, and when the space position of the control surface changes, the laser ranging sensor transmits the position change information of the control surface to the automatic test system for corresponding processing, so that the clearance value of the control surface of the airplane is calculated, the measurement operation is simple and convenient, the applied force can be freely controlled, the continuous change is realized, and the flexibility test requirement can be met.
Drawings
Fig. 1 is a schematic structural diagram of a pressure loading mechanism in a preferred embodiment of the invention.
FIG. 2 is a flow chart of an automatic test system according to a preferred embodiment of the invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Referring to fig. 1-2, a device for fixedly detecting a gap between control surfaces of an aircraft comprises a pressure loading mechanism and an automatic test system loaded with a test program, wherein the pressure loading mechanism comprises a control surface clamp 1, an upper clamping disc 2, a lower clamping disc 3, a rotary handle 4, a force sensor fixing clamp 5, a motor fixing clamp 6, a laser ranging sensor mounting bracket 7, a ranging adjusting rod 8, an adjusting handle 9, a height adjusting rod 10, an adjusting disc 11, an upper supporting plate 12, a supporting rod 13, a lower supporting plate 14, a universal wheel 15 and an adjustable bracket 16, wherein the control surface clamp is of a U-shaped structure and is suitable for mounting and adjusting control surfaces of different shapes and different depths, the upper clamping disc 2 is mounted on the upper surface of the inner side of the control surface clamp 1, the lower clamping disc 3 is mounted on the lower surface of the inner side of the control surface clamp 1, and the upper clamping disc 2 and the lower clamping disc 3 are designed by adopting flexible materials, the control surface is protected from being damaged when being clamped; the upper surface of the control surface clamp 1 is provided with a rotary handle 4 for adjusting the clamping state of the control surface and the upper clamping disc 2 and the lower clamping disc 3; the control surface clamp 1 is fixed on the top of the height adjusting rod 10, the height adjusting rod 10 is controlled to move up and down through the adjusting disc 11, the overall height of the control surface clamp 1 is adjusted by adjusting the telescopic length of the height adjusting rod 10, so that the control surface can be properly installed in the control surface clamp 1, the control surface clamp 1 is adjusted, a tested control surface is placed on the upper clamping disc 2 and the lower clamping disc 3, and then the rotary handle 4 is adjusted to enable the two clamping discs to be clamped on the proper positions of the control surface;
the height adjusting rod 10 is arranged in the middle of the upper supporting plate 12, the height adjusting rod 10 can be adjusted in a vertically telescopic mode through the adjusting disc 11, so that the overall positions of the control surface clamp 1 and a tested control surface can be adjusted and fixed, the upper supporting plate 12 and the lower supporting plate 14 are fixed through the supporting rod 13 to bear the weight of the whole set of pressure loading mechanism, the stability is good, the bottom of the lower supporting plate 14 is provided with three universal wheels 15, the detection device can move on site conveniently, the bottom of the lower supporting plate 14 is also provided with an adjustable support 16, the universal wheels 15 are provided with fixing clamping pieces, and the detection device can be fixed in a horizontal state when in use through adjusting the adjustable support 16 and the fixing clamping pieces;
the motor fixing clamp 6 is used for installing a servo motor, a screw rod is installed in an electric cylinder of the servo motor, when an automatic test system inputs a target force, a test program controls the motor to rotate so as to convert kinetic energy into vertical linear displacement of the screw rod in the electric cylinder and generate an upward or downward control force on the control surface clamp 1, and therefore the purpose that a tensile force or a pressure with adjustable magnitude is applied to a tested control surface is achieved;
the force sensor fixing clamp 5 is used for installing a force sensor, monitoring the change of a force value in real time, and when the linear motion of the electric cylinder screw rod extrudes or pulls the force sensor, the force sensor transmits the detected pulling force or pressure value to an automatic testing system for processing;
the device comprises a distance measuring adjusting rod 8, a laser distance measuring sensor mounting bracket 7, a regulating handle 9, a laser distance measuring sensor, an automatic testing system and a laser distance measuring sensor, wherein the distance measuring adjusting rod 8 is mounted on a height adjusting rod 10, the laser distance measuring sensor mounting bracket 7 is mounted at the top of the distance measuring adjusting rod 8, the regulating handle 9 is mounted at the bottom of the distance measuring adjusting rod 8, the laser distance measuring sensor collects position information of a control surface in real time, the position of a target point of the tested control surface is obtained in a laser distance measuring mode, after the control surface deflects, the position of the target point in the space changes, and the laser distance measuring sensor transmits the position change information of the control surface to the automatic testing system for corresponding processing to obtain a stroke result;
the servo motor, the force sensor and the laser ranging sensor are respectively connected with the automatic testing system;
the automatic test system comprises a state selection module, a data transmission module, a data acquisition module, a data monitoring module, a motor control module, a data processing module and a data display module, wherein a test program is loaded on the data processing module, the state selection module, the data transmission module, the data acquisition module, the data monitoring module, the motor control module and the data display module are respectively connected with the data processing module, a servo motor, a force sensor and a laser ranging sensor are respectively connected with the data acquisition module, the motor control module is connected with the servo motor, the test program automatically monitors and judges the magnitude of a force value through the force sensor so as to control the rotation of the servo motor and the displacement of a screw rod, then the magnitude of the applied force of a rudder surface is adjusted, the laser ranging sensor acquires the position change of the rudder surface after being stressed in real time, and then the data processing module is combined with the data model to generate the stroke change of a target point, and then generating a force and displacement curve by combining the tension or pressure value acquired by the force sensor, and finally calculating the clearance value of the control surface to be tested, wherein the method comprises the following specific steps:
1) starting a test program, and preparing control surface clearance measurement;
2) inputting a target pull/pressure of the pressure loading;
3) the test program controls the motor to rotate through the motor control module, and a screw rod of the servo motor generates displacement, so that pulling/pressure is applied to the control surface;
4) the force sensor automatically monitors the pulling/pressure change of the control surface, the laser ranging sensor collects the position change of the control surface after being stressed in real time, when the condition is met, a force and displacement curve is generated, and after the gap data of the control surface at this time is calculated, the next gap measurement is carried out;
5) the data acquisition module starts to acquire the motion of the control surface;
6) the data processing module processes the acquired data;
7) the data processing module outputs the position coordinates of the characteristic points of the servo motor, the stroke coordinates of the characteristic points of the screw rod and the stroke coordinates of the real-time characteristic points of the control surface, compares the position coordinates with the input target pull/pressure, generates a force and displacement curve when the conditions are met, and enters the next gap measurement after the gap data of the control surface is calculated until the gap measurement is completed.
Claims (8)
1. A device for fixedly detecting the clearance of an airplane control surface comprises a pressure loading mechanism and an automatic test system loaded with a test program, and is characterized in that a control surface clamp in the pressure loading mechanism is of a U-shaped structure, a clamping disc for protecting the control surface from being damaged is arranged on the inner side surface of the U-shaped structure, and a rotary handle for adjusting the clamping state of the control surface and the clamping disc is arranged on the control surface clamp; the control surface fixture is fixed at the top of the height adjusting rod, the bottom of the height adjusting rod is installed on the supporting body, a force sensor fixing clamp used for installing a force sensor, a motor fixing clamp used for installing a servo motor, a laser ranging sensor installing support used for installing a laser ranging sensor and an adjusting disc used for controlling the vertical displacement of the height adjusting rod are arranged on the height adjusting rod, and the force sensor, the servo motor and the laser ranging sensor are respectively connected with an automatic testing system.
2. The device for fixedly detecting the clearance between the control surfaces of the aircraft as claimed in claim 1, wherein the clamping disks comprise an upper clamping disk and a lower clamping disk, the upper clamping disk is mounted on the upper inner surface of the control surface fixture, and the lower clamping disk is mounted on the lower inner surface of the control surface fixture.
3. The device for fixedly detecting the control surface clearance of the aircraft as claimed in claim 2, wherein the upper clamping disk and the lower clamping disk are made of flexible materials.
4. The device for fixedly detecting the clearance between the control surfaces of the airplane as claimed in claim 1, wherein the laser ranging sensor mounting bracket is mounted on the height adjusting rod through a ranging adjusting rod, the laser ranging sensor mounting bracket is mounted at the top of the ranging adjusting rod, and an adjusting handle is mounted at the bottom of the ranging adjusting rod.
5. The device for fixedly detecting the clearance between the control surfaces of the aircraft as claimed in claim 1, wherein the supporting body comprises an upper supporting plate, a supporting rod and a lower supporting plate, the height adjusting rod is installed in the middle of the upper supporting plate, and the upper supporting plate and the lower supporting plate are fixed through the supporting rod.
6. The device for fixedly detecting the control surface clearance of the airplane as claimed in claim 5, wherein the bottom of the lower support plate is provided with three universal wheels, and fixing cards are mounted on the universal wheels.
7. The device for fixedly detecting the control surface clearance of the aircraft as claimed in claim 6, wherein an adjustable bracket is further arranged at the bottom of the lower support plate.
8. The device for fixedly detecting the clearance between the control surfaces of the airplane as claimed in claim 1, wherein the automatic test system comprises a state selection module, a data transmission module, a data acquisition module, a data monitoring module, a motor control module, a data processing module and a data display module, the test program is loaded in the data processing module, the state selection module, the data transmission module, the data acquisition module, the data monitoring module, the motor control module and the data display module are respectively connected with the data processing module, the servo motor, the force sensor and the laser ranging sensor are respectively connected with the data acquisition module, and the motor control module is connected with the servo motor; the testing program automatically monitors and judges the magnitude of the force value through the force sensor so as to control the rotation of the servo motor and the displacement of the screw rod, then the magnitude of the force applied by the control surface is adjusted, the laser distance measuring sensor collects the position change of the control surface after being stressed in real time, then the data processing module is combined with the data model to generate the stroke change of a target point, then the force and displacement curve is generated by combining the pulling force or the pressure value collected by the force sensor, and finally the clearance value of the tested control surface is calculated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110652010.3A CN113443168A (en) | 2021-06-11 | 2021-06-11 | Device for fixedly detecting clearance of control surface of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110652010.3A CN113443168A (en) | 2021-06-11 | 2021-06-11 | Device for fixedly detecting clearance of control surface of airplane |
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| Publication Number | Publication Date |
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| CN113443168A true CN113443168A (en) | 2021-09-28 |
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| CN202110652010.3A Pending CN113443168A (en) | 2021-06-11 | 2021-06-11 | Device for fixedly detecting clearance of control surface of airplane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114906256A (en) * | 2022-04-04 | 2022-08-16 | 中国第一汽车股份有限公司 | Device for quickly adjusting back door gap by using limiting block and assembly method |
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
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2021
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114906256A (en) * | 2022-04-04 | 2022-08-16 | 中国第一汽车股份有限公司 | Device for quickly adjusting back door gap by using limiting block and assembly method |
| CN114906256B (en) * | 2022-04-04 | 2023-11-14 | 中国第一汽车股份有限公司 | Device for quickly adjusting back door gap by utilizing limiting block and assembly method |
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
| CN116986015B (en) * | 2023-09-28 | 2023-12-12 | 航天江南集团有限公司 | Steering engine detection device |
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Application publication date: 20210928 |