CN110926931B - Torsion-tension relation measuring device and method for airplane hinge structure - Google Patents
Torsion-tension relation measuring device and method for airplane hinge structure Download PDFInfo
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- CN110926931B CN110926931B CN201911362776.7A CN201911362776A CN110926931B CN 110926931 B CN110926931 B CN 110926931B CN 201911362776 A CN201911362776 A CN 201911362776A CN 110926931 B CN110926931 B CN 110926931B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/22—Investigating strength properties of solid materials by application of mechanical stress by applying steady torsional forces
Abstract
The embodiment of the invention discloses a torsion-tension relation measuring device and a torsion-tension relation measuring method of an airplane hinge structure, which comprise the following steps: the hinge structure and the torsion-tension relation measuring module; in the hinge structure, a bolt penetrates through the double-lug structure and the bearing, and a threaded end of the bolt is screwed in and fixed through a nut; in the torsional-tensile relation measuring module, a through hole for a bolt to pass through is formed in the locking chuck and the force bearing baffle plate, one end of the rotating shaft is fixedly connected with the motor, the other end of the rotating shaft is fixedly connected with the nut sleeve, a port of the nut sleeve is clamped on a nut of the hinge structure, and the input torque sensor is arranged on the rotating shaft; the bolt also passes through the stop chuck and the bearing baffle, the bolt head is fixed through the stop chuck, the bearing baffle is contacted with one side of the double-lug structure close to the bolt head, and the bearing baffle and the stop chuck are respectively connected with the torque and tension sensor. The embodiment of the invention solves the problem of measuring the torsion-tension relationship of the typical hinge structure, and can effectively measure the torsion-tension relationship of the typical hinge structure.
Description
Technical Field
The present application relates to, but not limited to, the technical field of measurement of torque and tension of hinge structures, and in particular, to a device and a method for measuring a torsional-tensile relationship of an aircraft hinge structure.
Background
The typical hinge structure is generally used for connecting a movable wing surface of an airplane with a fixed arm and is an important connection of the airplane. The bolts in the hinge structure have proper pretightening force, so that the connection reliability can be ensured, and the fatigue performance of the hinge structure can be improved. Therefore, measuring the torsional-tensile relationship of a typical hinge structure is the core technology of fastening axial force control.
At present, a measuring device and a measuring method for the twist-pull relationship of a thread structure have been proposed. However, the existing measuring device and measuring method are only designed for improving a shorter bolt or thread structure, and the torsion-tension relationship between a bolt nut and a sandwich structure is mainly measured.
Disclosure of Invention
In order to solve the above technical problems, embodiments of the present invention provide a device and a method for measuring a torsional-tensile relationship of an aircraft hinge structure, so as to solve the problem of measuring the torsional-tensile relationship of a typical hinge structure, and effectively measure the torsional-tensile relationship of the typical hinge structure.
The embodiment of the invention provides a torsion-tension relation measuring device of an airplane hinge structure, which comprises: the hinge structure and the torsion-tension relation measuring module;
the hinge structure comprises a double-lug structure provided with a through hole, a bearing, a bolt and a nut, the bearing is arranged between double lugs of the double-lug structure, the bolt penetrates through the double-lug structure and the bearing, and a threaded end of the bolt is screwed in and fixed through the nut;
the torsion-tension relation measuring module comprises a motor, a rotating shaft, a nut sleeve, a force bearing baffle plate, a stopping chuck, an input torque sensor and a torque and tension sensor, wherein the stopping chuck and the force bearing baffle plate are provided with through holes for bolts to pass through; one end of the rotating shaft is fixedly connected with the motor, the other end of the rotating shaft is fixedly connected with the nut sleeve, a port of the nut sleeve is clamped on a nut of the hinge structure, and the input torque sensor is arranged on the rotating shaft;
the bolt further penetrates through the stop chuck and the force bearing baffle, the bolt head is fixed through the stop chuck, the force bearing baffle is in contact with one side, close to the bolt head, of the double-lug structure, and the force bearing baffle and the stop chuck are connected with the torque and tension sensor respectively.
Optionally, in the torsion-tension relationship measuring apparatus for an aircraft hinge structure as described above, the torsion-tension relationship measuring module is configured to drive the rotating shaft, the nut sleeve and the nut to rotate by rotation of the motor, so as to apply an input torque to the hinge structure.
Alternatively, in the torsion relation measuring apparatus of the hinge structure of an aircraft as described above,
the input torque sensor is configured to measure an input torque applied to the hinge structure by the torsional-tensile relationship measurement module.
Alternatively, in the torsion relation measuring apparatus of the hinge structure of an aircraft as described above,
the torque and tension sensor is configured to measure a bolt tension transmitted to the bolt head through the locking collet by a tension of the input torque to the hinge structure.
Alternatively, in the torsion relation measuring apparatus of the hinge structure of an aircraft as described above,
the torque and tension sensor is further configured to measure the output torque transmitted by the force bearing baffle plate through the tension of the input torque on the hinge structure.
The embodiment of the invention also provides a torsion-tension relationship measuring method of the aircraft hinge structure, which adopts the torsion-tension relationship measuring device of the aircraft hinge structure to measure the torsion-tension relationship, and the torsion-tension relationship measuring method comprises the following steps:
applying input torque to a nut of the hinge structure from zero through the rotation of the motor until a bolt of the hinge structure is broken;
measuring an input torque with an input torque sensor during application of the input torque;
based on the tension of the input torque to the hinge structure, measuring the bolt tension transmitted to the bolt head through the stopping chuck by adopting a torque and tension sensor;
and drawing a torsion-tension relation curve graph of the hinge structure according to the input torque and the bolt tension.
Optionally, in the method for measuring a torsional relationship of an aircraft hinge structure as described above, the applying an input torque to a nut of the hinge structure from zero until a bolt of the hinge structure is broken includes:
continuously applying input torque to the nut of the hinge structure from zero until the bolt of the hinge structure is broken; alternatively, the first and second liquid crystal display panels may be,
and continuously applying the input torque to the nut of the hinge structure from zero, and restarting continuously applying the input torque from the input torque value at the previous stop after the break-pulling force is allowed to stop every 10% of the bolts until the bolts of the hinge structure are broken.
Optionally, in the method for measuring a torsional relationship of an aircraft hinge structure, the method further includes:
applying an input torque to a nut of the hinge structure from zero through the rotation of the motor until the input torque reaches the allowable breaking tension of the bolt;
and taking down the nut, screwing the nut into the fixed bolt again, and applying an input torque to the nut of the hinge structure from zero through the rotation of the motor again until the input torque reaches the allowable breaking tension of the bolt.
Optionally, in the method for measuring a torsional relationship of an aircraft hinge structure, the method further includes:
measuring the output torque transmitted by the bearing baffle by adopting a torque and tension sensor based on the tension of the input torque to the hinge structure;
and calculating a torque coefficient of the hinge structure and an end surface friction coefficient of the nut close to the double-lug structure according to the input torque, the output torque, the bolt tension and the structural parameters of the bolt and the nut.
The embodiment of the invention provides a device and a method for measuring the torsion-tension relationship of an aircraft hinge structure, wherein the device comprises the following steps: the hinge structure and the torsion-tension relation measuring module; in the hinge structure, a bolt penetrates through the double-lug structure and the bearing, and a threaded end of the bolt is screwed in and fixed through a nut; in the torsional-tensile relation measuring module, a through hole for a bolt to pass through is formed in the locking chuck and the force bearing baffle plate, one end of the rotating shaft is fixedly connected with the motor, the other end of the rotating shaft is fixedly connected with the nut sleeve, a port of the nut sleeve is clamped on a nut of the hinge structure, and the input torque sensor is arranged on the rotating shaft; the bolt also passes through the stop chuck and the bearing baffle, the bolt head is fixed through the stop chuck, the bearing baffle is contacted with one side of the double-lug structure close to the bolt head, and the bearing baffle and the stop chuck are respectively connected with the torque and tension sensor. The torsion-tension relation measuring device is designed for a typical hinge structure, the influence of a lug structure, bearing friction torque and the like in the hinge on the torsion-tension relation is simulated through the torsion-tension relation measuring device, and the torsion-tension relation measuring problem of the typical hinge structure can be solved; in addition, the torsion-pull relation measuring device is simple in structure, clear in principle of measuring the torsion-pull relation, and capable of effectively and accurately measuring the torsion-pull relation of various typical hinge structures.
Drawings
The accompanying drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and are not intended to limit the invention.
Fig. 1 is a schematic structural diagram of a torsion-tension relationship measuring device of an aircraft hinge structure according to an embodiment of the present invention;
fig. 2 is a flowchart of a torsion-tension relationship measuring method of an aircraft hinge structure according to an embodiment of the present invention;
FIG. 3 is a graph illustrating a torsional-tensile relationship obtained by a conventional loading method according to an embodiment of the present invention;
FIG. 4 is a graph of a torsional-tensile relationship obtained by using an intermittent loading manner in an embodiment of the present invention;
FIG. 5 is a graph showing the torsion-pull relationship obtained by the loading method of the present invention with two screwing operations.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic structural diagram of a torsion-tension relationship measuring device of an aircraft hinge structure according to an embodiment of the present invention. The torsion-pull relationship measuring device of the aircraft hinge structure provided by the embodiment can comprise: the hinge structure and the torsion-tension relation measuring module;
the hinge structure comprises a double-lug structure 7 provided with a through hole, a bearing 11, a bolt 10 and a nut 4, wherein the bearing 11 is arranged between double lugs of the double-lug structure 7, the bolt 10 penetrates through the double-lug structure 7 and the bearing 11, and the threaded end of the bolt 10 is screwed in and fixed through the nut 4;
the torsion-tension relation measuring module comprises a motor 1, a rotating shaft 2, a nut sleeve 3, a force-bearing baffle plate 8, a stopping chuck 5, an input torque sensor 6 and a torque and tension sensor 9, wherein the stopping chuck 5 and the force-bearing baffle plate 8 are provided with through holes for bolts 10 to pass through; one end of the rotating shaft 2 is fixedly connected with the motor 1, the other end of the rotating shaft is fixedly connected with the nut sleeve 3, a port of the nut sleeve 3 is clamped on the nut 4 of the hinge structure, and the input torque sensor 6 is arranged on the rotating shaft 2;
the bolt 10 also penetrates through the stop chuck 5 and the force bearing baffle plate 8, the bolt head is fixed through the stop chuck 5, the force bearing baffle plate 8 is in contact with one side, close to the bolt head, of the double-lug structure 7, and the force bearing baffle plate 8 and the stop chuck 5 are respectively connected with the torque and tension sensor 9.
In the embodiment of the invention, the torsion-tension relation measuring module has the following functions: through the rotation of motor 1, drive pivot 2, nut sleeve 3 and nut 4 and rotate, exert input torque to the hinge structure.
In the embodiment of the present invention, the input torque sensor 6 may function as: the measurement of the torsional-tensile relationship measures the input torque applied by the module to the hinge structure.
In the embodiment of the present invention, the torque and tension sensor 9 may function as: the bolt tension transmitted to the bolt head through the locking collet 5 is measured by the tension of the input torque to the hinge structure.
In the embodiment of the present invention, the torque and tension sensor 9 may also function as: the output torque transmitted by the bearing baffle 8 is measured by the pulling force of the input torque to the hinge structure.
The torsion-tension relation measuring device of the aircraft hinge structure provided by the embodiment of the invention is designed for the torsion-tension relation of bolts and nuts in a typical hinge structure of an aircraft; the torsion-tension relationship testing device simplifies a typical hinge structure and is equivalent to a combined structure of a double-lug structure 7, a bearing 11, a bolt 10 and a nut 4; the bolt head of a typical hinge bolt is fixed by a stop chuck 5, one side of a double-lug structure 7 close to the bolt head is in contact with a bearing baffle plate 8, and the bearing baffle plate 8 is connected with a torque and tension sensor 9; and a nut sleeve 3 connected with a motor 6 is adopted at one torque loading side to drive a nut at one side to apply torque. In practical application, the torque can be loaded from zero, the torque is measured, the tension in the bolt is measured, a torsion-tension relation curve is drawn, and finally the measurement of the torsion-tension relation of the typical hinge structure is completed.
Based on the torsion-tension relationship measuring device of the aircraft hinge structure provided by the embodiment of the invention, the embodiment of the invention also provides a torsion-tension relationship measuring method of the aircraft hinge structure, the torsion-tension relationship measuring method adopts the torsion-tension relationship measuring device of the aircraft hinge structure provided by any one of the embodiments of the invention to measure the torsion-tension relationship, as shown in fig. 2, the torsion-tension relationship measuring method of the aircraft hinge structure provided by the embodiment of the invention comprises the following steps:
and 4, drawing a torsion-tension relation curve graph of the hinge structure according to the input torque and the bolt tension.
Optionally, in step 1 of the embodiment of the present invention, the implementation manner of applying the input torque to the nut of the hinge structure from zero to the bolt of the hinge structure being pulled apart may include the following several cases:
first, the conventional loading mode: continuously applying input torque to the nut of the hinge structure from zero until the bolt of the hinge structure is broken; in the mode, the nut end continuously loads torque from zero until the bolt is broken, the input torque is measured through multi-point recording, the torque and the pulling force transmitted by the hinge structure are correspondingly measured, and finally a torsion-pulling relation curve is drawn.
As shown in fig. 3, which is a torsion-tension relationship curve obtained by a conventional loading manner in the embodiment of the present invention, and is a conventional loading torsion-tension relationship curve 12 illustrated in fig. 3, it can be seen that, in an initial stage, a structural clearance is eliminated, an axial force does not occur in the bolt, and the axial force in the bolt is continuously increased along with an increase in the loading torque.
Second, the intermediate interrupt loading mode: continuously applying input torque to a nut of the hinge structure from zero, and restarting continuously applying the input torque from the input torque value of the previous stop after stopping every 10% of bolts by using breaking tension until the bolts of the hinge structure are broken; in the method, the torque of the nut end is loaded, the allowable breaking tension of the bolt is stopped every 10 percent until the bolt is broken, and the loaded torque and the tension transmitted by the hinge structure are respectively recorded; and finally drawing a torque tension curve.
As shown in fig. 4, which is a torsion-tension relationship curve obtained by using an intermittent loading manner in the embodiment of the present invention, it can be seen that, compared with a conventional intermittent loading manner, the intermittent loading manner needs to overcome the static friction force of re-tightening, the intermittent loading manner is illustrated as a torsion-tension relationship curve 13 in fig. 4. The second loading mode can measure the effect of intermittent tightening on the twist-pull relationship.
Optionally, the torsion-tension relationship measuring method provided in the embodiment of the present invention may further include the following loading manner:
and the third is that: two-time screwing loading mode: applying an input torque to a nut of the hinge structure from zero through the rotation of the motor until the input torque reaches the allowable breaking tension of the bolt;
and taking down the nut, screwing the nut into the fixed bolt again, and applying an input torque to the nut of the hinge structure from zero through the rotation of the motor again until the input torque reaches the allowable breaking tension of the bolt.
In this manner, the nut end is loaded with torque from zero continuously until the allowable bolt strength value is reached. And after the nut is withdrawn, the torque is continuously loaded from zero to the allowable bolt strength value again. The values of the shaft force and the torque force are recorded for two screws. As shown in fig. 5, which is a graph of the torsion-tension relationship obtained by using the two-time screwing-in loading manner in the embodiment of the present invention, the two-time screwing-in loading illustrated in fig. 5 includes a first-time loading torsion-tension relationship curve 14 and a second-time loading torsion-tension relationship curve 15. Since the first screwing in causes wear of the thread crests, plating, etc., the torque that generates the same bolt axial force becomes small.
Optionally, the torsion-tension relationship measuring method provided in the embodiment of the present invention may further include the following steps:
based on the tension of the input torque to the hinge structure, measuring the output torque transmitted by the bearing baffle by using a torque and tension sensor;
and calculating the torque coefficient of the hinge structure and the end surface friction coefficient of the nut close to the double-lug structure according to the input torque, the output torque, the bolt tension and the structural parameters of the bolt and the nut.
It should be noted that, in the embodiment of the present invention, in the three loading manners, the loaded input torque and the tensile force transmitted by the hinge structure are recorded, and the plotted relationship curve is a variation curve of the tensile force along with the input torque; the recorded data can be used for calculating a torque coefficient, a thread friction coefficient and an end face friction coefficient, and the data can be used for guiding anti-clamping design of the hinge structure.
The torsion-pull relation measuring device of the airplane hinge structure provided by the embodiment of the invention has a simple structure, has a clear principle of measuring the torsion-pull relation, and can effectively and accurately measure the torsion-pull relation of various typical hinge structures.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (6)
1. A torsion-pull relationship measuring device of an aircraft hinge structure, comprising: the hinge structure and the torsion-tension relation measuring module;
the hinge structure comprises a double-lug structure provided with a through hole, a bearing, a bolt and a nut, the bearing is arranged between double lugs of the double-lug structure, the bolt penetrates through the double-lug structure and the bearing, and a threaded end of the bolt is screwed in and fixed through the nut;
the torsion-tension relation measuring module comprises a motor, a rotating shaft, a nut sleeve, a force bearing baffle plate, a stopping chuck, an input torque sensor and a torque and tension sensor, wherein the stopping chuck and the force bearing baffle plate are provided with through holes for bolts to pass through; one end of the rotating shaft is fixedly connected with the motor, the other end of the rotating shaft is fixedly connected with the nut sleeve, a port of the nut sleeve is clamped on a nut of the hinge structure, and the input torque sensor is arranged on the rotating shaft;
the bolt also penetrates through the stop chuck and the force bearing baffle, the bolt head is fixed through the stop chuck, the force bearing baffle is in contact with one side of the double-lug structure close to the bolt head, and the force bearing baffle and the stop chuck are respectively connected with the torque and tension sensor;
the torsion-tension relation measuring device of the airplane hinge structure equivalently simulates a typical airplane hinge structure through a combined structure of a double-lug structure, a bearing, a bolt and a nut; the bolt head of a bolt in a typical hinge structure of the airplane is fixed by a stop chuck, one side of a double-lug structure close to the bolt head is in contact with a bearing baffle plate, and the bearing baffle plate is connected with a torque and tension sensor; a nut sleeve connected with a motor is adopted at one torque loading side to drive a nut at one side to apply torque;
the input torque sensor is used for measuring the input torque applied to the hinge structure by the torsion-tension relation measuring module;
the torque and tension sensor is used for measuring the bolt tension transmitted to the bolt head through the locking chuck through the tension of the input torque to the hinge structure, and is also used for measuring the output torque transmitted through the bearing baffle plate through the tension of the input torque to the hinge structure;
the input torque and the bolt tension are used for drawing a torsion-tension relation curve chart of the hinge structure; the input torque, the output torque, the bolt tension and the structural parameters of the bolt and the nut are used for calculating the torque coefficient of the hinge structure and the end surface friction coefficient of the nut close to the double-lug structure.
2. The apparatus of claim 1, wherein the torsional relationship measuring module is configured to apply an input torque to the hinge structure by rotating the shaft, the nut sleeve and the nut via rotation of the motor.
3. A torsion-pulling relationship measurement method of an aircraft hinge structure, characterized in that a torsion-pulling relationship measurement is performed using the torsion-pulling relationship measurement apparatus of an aircraft hinge structure according to claim 1 or 2, the torsion-pulling relationship measurement method comprising:
applying input torque to a nut of the hinge structure from zero through the rotation of the motor until a bolt of the hinge structure is broken;
measuring an input torque with an input torque sensor during application of the input torque;
based on the tension of the input torque to the hinge structure, measuring the bolt tension transmitted to the bolt head through the stopping chuck by using a torque and tension sensor;
and drawing a torsion-tension relation curve graph of the hinge structure according to the input torque and the bolt tension.
4. The method of measuring a torsional relationship of an aircraft hinge structure according to claim 3, wherein the applying an input torque to a nut of the hinge structure from zero until a bolt of the hinge structure is broken comprises:
continuously applying input torque to the nut of the hinge structure from zero until the bolt of the hinge structure is broken; alternatively, the first and second electrodes may be,
and continuously applying the input torque to the nut of the hinge structure from zero, and restarting continuously applying the input torque from the input torque value at the previous stop after the break-pulling force is allowed to stop every 10% of the bolts until the bolts of the hinge structure are broken.
5. The method of measuring a torsional relationship of an aircraft hinge structure according to claim 3, further comprising:
applying an input torque to a nut of the hinge structure from zero through the rotation of the motor until the input torque reaches the allowable breaking tension of the bolt;
and taking off the nut, screwing the nut into the fixed bolt again, and applying the input torque to the nut of the hinge structure from zero through the rotation of the motor again until the input torque reaches the allowable breaking tension of the bolt.
6. The method of measuring a torsional relationship of an aircraft hinge structure according to claim 3, further comprising:
measuring the output torque transmitted by the bearing baffle by adopting a torque and tension sensor based on the tension of the input torque to the hinge structure;
and calculating a torque coefficient of the hinge structure and an end surface friction coefficient of the nut close to the double-lug structure according to the input torque, the output torque, the bolt tension and the structural parameters of the bolt and the nut.
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| CN112556915B (en) * | 2020-11-26 | 2022-09-30 | 济南纳克试验设备有限公司 | Bolt and nut connection pair comprehensive performance test device |
| CN114184378A (en) * | 2021-12-02 | 2022-03-15 | 江苏心源航空科技有限公司 | Declination axis static torsion test bed |
| CN114776159A (en) * | 2022-04-26 | 2022-07-22 | 爱驰汽车有限公司 | Vehicle door hinge mounting method |
| CN116818306B (en) * | 2023-07-11 | 2024-03-15 | 长春仟邦测试设备有限公司 | Pipe joint torsion-pull relation and friction coefficient measuring method |
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