CN116659720B - Aircraft harness pulling-out force calculation method - Google Patents
Aircraft harness pulling-out force calculation method Download PDFInfo
- Publication number
- CN116659720B CN116659720B CN202310380784.4A CN202310380784A CN116659720B CN 116659720 B CN116659720 B CN 116659720B CN 202310380784 A CN202310380784 A CN 202310380784A CN 116659720 B CN116659720 B CN 116659720B
- Authority
- CN
- China
- Prior art keywords
- clamp
- wire harness
- out force
- pulling
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000004364 calculation method Methods 0.000 title claims abstract description 24
- 238000000034 method Methods 0.000 claims abstract description 32
- 238000012545 processing Methods 0.000 claims description 24
- 230000005540 biological transmission Effects 0.000 claims description 16
- 230000010354 integration Effects 0.000 claims description 11
- 238000006243 chemical reaction Methods 0.000 claims description 6
- 230000003321 amplification Effects 0.000 claims 1
- 238000003199 nucleic acid amplification method Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 9
- 238000002474 experimental method Methods 0.000 abstract description 4
- 239000002184 metal Substances 0.000 description 5
- 229920001971 elastomer Polymers 0.000 description 4
- 238000004088 simulation Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000003405 preventing effect Effects 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 229920000181 Ethylene propylene rubber Polymers 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- -1 polytetrafluoroethylene Polymers 0.000 description 1
- 229920001343 polytetrafluoroethylene Polymers 0.000 description 1
- 239000004810 polytetrafluoroethylene Substances 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0033—Force sensors associated with force applying means applying a pulling force
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a method for calculating pulling-out force of an aircraft wire harness, which belongs to the technical field of aircraft wire harness experiments and comprises the following steps: a. measuring the axial pressure of the bolt applied to the screw by a pressure collecting screw blade; b. programming is carried out, and the input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database; c. calculating stress between the clamp and the wire harness; d. calculating the stressed area of the clamp; e. calculating the pulling-out force of the clamp on the wire harness by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness; f. and e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, and judging to be qualified if the calculated value is in a range of 1-1.5 times of the standard value. The invention can simulate and calculate the wire Shu Latuo force, conveniently and accurately predict the wire harness pulling-out force and ensure the wire harness fastening effect.
Description
Technical Field
The invention relates to the technical field of aircraft wire harness experiments, in particular to a method for calculating pulling-out force of an aircraft wire harness.
Background
When the aircraft pencil is installed on the aircraft, need use the clamp to fix, the clamp divide into rubber layer and metal level, the rubber layer cover outside the metal level and with pencil direct contact, the used bolt and the nut of clamp and fixed clamp are installed on the angle piece, the angle piece passes through the rivet and directly rivets on the structure. The clamp is applied with tightening force through the tool rotating bolt, and the clamp is clamped with the wire harness when being stressed and contracted inwards, so that the wire harness is prevented from loosening in the clamp.
The aircraft receives the influence of aerial air current and engine in the flight, can take place great vibration, pencil and clamp in the vibration process, if the clamp is too little to the clamp force of pencil, the pencil can take place to loosen, the clamp can't play fixed pencil, prevent the effect of pencil swing by a wide margin, the pencil can produce the friction with the structure on every side this moment, can lead to pencil skin card cloth Long Butao or metal wave-proof cover to produce wearing and tearing, lead to the wire to expose and structural contact, can produce the ablation of short circuit or pencil, influence aircraft flight safety. If the clamping force of the clamp to the wire harness is too large, the wire harness is deformed too much due to severe extrusion, and the wire harness rubber layer or the metal wire is also extruded to deform.
The conventional measuring wire harness pulling-out force is that pulling force is applied to the wire harness through a tension meter on a special test bench until the wire harness is loosened from the clamp, and the test equipment is large in size, so that the method is only used for obtaining standard pulling-out force in a laboratory and cannot be popularized to the machine for measuring the pulling-out preventing effect which can be achieved by the clamp after the installation is completed in real time.
The Chinese patent literature with the publication number of CN112033844A and the publication date of 2020, 12 and 04 discloses multi-station simulation aircraft wire harness abrasion test equipment and an experiment method.
The multi-station simulated aircraft harness wear experimental equipment and the experimental method disclosed by the patent document can collect stress conditions of the aircraft harness under different working conditions and provide data support for an aircraft harness wear prevention process. But can not comparatively swiftly and accurate prediction pencil pull-out force, can not effectively ensure pencil fastening effect.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the aircraft wire harness pulling-out force calculation method, which can simulate and calculate the wire Shu Latuo force, conveniently and accurately predict the wire harness pulling-out force and ensure the wire harness fastening effect.
The invention is realized by the following technical scheme:
The aircraft wire harness pulling-out force calculating method is characterized by comprising the following steps of:
a. measuring the axial pressure of the bolt applied to the screw by a pressure collecting screw blade;
b. Performing program design, wherein an input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database, the bolt axial pressure measured by a pressure acquisition screw blade is transmitted to an upper computer in a wireless manner, and the friction coefficient of the wire harness surface is obtained from the friction coefficient database;
c. calculating stress between the clamp and the wire harness through the method 1;
1 (1)
Wherein,For stress between the clip and the wire harness,/>Is the axial pressure/>The radius of the clamp after deformation is h, and the width of the clamp is h;
d. calculating the stressed area of the clamp through the method 2;
2, 2
Wherein S is the stress area of the clamp,The radius of the clamp after deformation is h, and the width of the clamp is h;
e. The pulling-out force of the clamp on the wire harness is calculated through a 3 method by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness;
3
Wherein,For the pulling-out force of the clamp to the wire harness,/>Is the coefficient of friction of the wire harness surface,/>Is the axial pressure of the bolt;
f. And e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, and judging to be qualified if the calculated value is in a range of 1-1.5 times of the standard value.
In the step a, the pressure acquisition screwdriver comprises a shell and a screwdriver rotating rod arranged on the shell, wherein a pressure sensor, a signal integration processing module, a power module and a wireless module are arranged in the shell, and the signal integration processing module is respectively and electrically connected with the pressure sensor, the power module and the wireless module.
Step a specifically means that the screw blade rotating rod transmits torque to the pressure sensor, the pressure sensor converts a force signal into a voltage signal, the voltage signal is processed through the signal integration processing module, then data are transmitted to the upper computer through wireless transmission, the upper computer obtains a digital signal, and the upper computer software processes the data to obtain a torque value applied to the screw by the screw blade.
The signal integrated processing module processes the voltage signal, specifically, removes ripple, adjusts zero point, amplifies and analog-to-digital conversion process.
The data transmission to the upper computer through wireless transmission specifically means transmission through Bluetooth.
The pressure sensor is used for detecting a force signal and converting the force signal into a voltage signal.
The power module is used for providing electric energy for the signal integrated processing module.
The wireless module is used for wireless transmission of data.
The harness of the present invention refers to a connector assembly of a plurality of wires, cables and their terminations that are arranged, bundled, and can be installed or removed as a unit.
The clamping force refers to force generated by the wire harness in the contraction process of the clamp when the lug of the clamp is subjected to external force.
The pulling force refers to the application of a pulling force to the wire harness, and the pulling force just pulls the wire harness out of the clamp or releases the wire harness.
The basic principle of the invention is as follows:
The clamp mounting screw is screwed down to the pressure acquisition screw sword, and the pressure acquisition screw sword changes moment into voltage signal, handles voltage signal through signal integration processing module, changes analog signal into digital signal to give the host computer through wireless transmission, host computer software gathers communication interface and obtains transmission data, obtains the bolt axial pressure that the pressure acquisition screw sword received in the aircraft operating personnel's hand in real time.
And the software calls the friction coefficient in the database and the axial pressure of the bolt, and the pulling-out force of the clamp on the wire harness is obtained through the function call type 3 and displayed on a software interface. Comparing the calculated clamp with a standard value in a standard drawing force database of the wire harness through software, and judging that the wire harness is qualified if the calculated value is in a range of 1-1.5 times of the standard value; if the calculated value is smaller than 1 time of the standard value, the actual pulling-out force is smaller, which means that the screw of an operator is not screwed down, and the wire harness is likely to be loosened under the condition of vibration or external force of the aircraft; if the calculated value is greater than 1.5 times of the standard value, the wiring harness is stressed too much, the wire core or the rubber inside the wiring harness is in cold risk, and an operator has to loosen the screws, so that the stress between the clamp and the wiring harness is reduced.
The beneficial effects of the invention are mainly shown in the following aspects:
1. The method comprises the steps of a, measuring the axial pressure of a bolt applied to the bolt through a pressure collecting screwdriver; b. performing program design, wherein an input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database, the bolt axial pressure measured by a pressure acquisition screw blade is transmitted to an upper computer in a wireless manner, and the friction coefficient of the wire harness surface is obtained from the friction coefficient database; c. calculating stress between the clamp and the wire harness; d. calculating the stressed area of the clamp; e. calculating the pulling-out force of the clamp on the wire harness by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness; f. and e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, judging to be qualified if the calculated value is within a range of 1-1.5 times of the standard value, and compared with the prior art, the clamp can simulate and calculate the force of Shu Latuo, so that the pulling-out force of the wire harness can be conveniently and accurately predicted, and the fastening effect of the wire harness is ensured.
2. According to the invention, the wire harness pulling-out force is predicted by carrying out simulation calculation on the wire harness pulling-out force, the calculation is simple and convenient, the device is beneficial to being popularized on a machine to measure the pulling-out prevention effect achieved by the clamp after the installation is completed in real time, and the applicability is good.
3. The clamping device can effectively evaluate the clamping effect of the clamp on the wire harness and improve the safety problem of the wire harness caused by the fact that the wire harness is not fastened in place.
Drawings
The invention will be further specifically described with reference to the drawings and detailed description below:
FIG. 1 is a schematic diagram of a clamp force analysis in accordance with the present invention;
FIG. 2 is a schematic view of a pressure acquisition screw;
FIG. 3 is a flow chart of signal acquisition according to the present invention;
the marks in the figure: 1. the device comprises a shell, a screw cutter rotating rod, a pressure sensor, a signal integrated processing module, a power module, a wireless module and a signal integrated processing module, wherein the shell is provided with the screw cutter rotating rod, the screw cutter rotating rod is provided with the screw cutter rotating rod, the signal integrated processing module is provided with the screw cutter rotating rod, and the signal integrated processing module is provided with the screw cutter rotating rod;
Variation of collar radius,/> Variable of clip tab distance,/>Radius of clamp before deformation,/>Radius of clamp after deformation,/>Axial pressure of bolt,/>And the reaction resultant force is A, the clamp A point, B, the clamp B point, C, the clamp C point, D and the clamp D point.
Detailed Description
Example 1
The aircraft harness pulling-out force calculating method comprises the following steps of:
a. measuring the axial pressure of the bolt applied to the screw by a pressure collecting screw blade;
b. Performing program design, wherein an input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database, the bolt axial pressure measured by a pressure acquisition screw blade is transmitted to an upper computer in a wireless manner, and the friction coefficient of the wire harness surface is obtained from the friction coefficient database;
c. calculating stress between the clamp and the wire harness through the method 1;
1 (1)
Wherein,For stress between the clip and the wire harness,/>Is the axial pressure/>The radius of the clamp after deformation is h, and the width of the clamp is h;
d. calculating the stressed area of the clamp through the method 2;
2, 2
Wherein S is the stress area of the clamp,The radius of the clamp after deformation is h, and the width of the clamp is h;
e. The pulling-out force of the clamp on the wire harness is calculated through a 3 method by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness;
3
Wherein,For the pulling-out force of the clamp to the wire harness,/>Is the coefficient of friction of the wire harness surface,/>Is the axial pressure of the bolt;
f. And e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, and judging to be qualified if the calculated value is in a range of 1-1.5 times of the standard value.
The embodiment is the most basic implementation mode, can carry out simulation calculation to the line Shu Latuo force, and the wire harness pulling-out force is predicted conveniently and accurately, and the wire harness fastening effect is guaranteed.
Example 2
The aircraft harness pulling-out force calculating method comprises the following steps of:
a. measuring the axial pressure of the bolt applied to the screw by a pressure collecting screw blade;
b. Performing program design, wherein an input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database, the bolt axial pressure measured by a pressure acquisition screw blade is transmitted to an upper computer in a wireless manner, and the friction coefficient of the wire harness surface is obtained from the friction coefficient database;
c. calculating stress between the clamp and the wire harness through the method 1;
1 (1)
Wherein,For stress between the clip and the wire harness,/>Is the axial pressure/>The radius of the clamp after deformation is h, and the width of the clamp is h;
d. calculating the stressed area of the clamp through the method 2;
2, 2
Wherein S is the stress area of the clamp,The radius of the clamp after deformation is h, and the width of the clamp is h;
e. The pulling-out force of the clamp on the wire harness is calculated through a 3 method by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness;
3
Wherein,For the pulling-out force of the clamp to the wire harness,/>Is the coefficient of friction of the wire harness surface,/>Is the axial pressure of the bolt;
f. And e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, and judging to be qualified if the calculated value is in a range of 1-1.5 times of the standard value.
Further, in the step a, the pressure collecting screwdriver comprises a casing 1 and a screwdriver rotating rod 2 arranged on the casing 1, wherein a pressure sensor 3, a signal integrated processing module 4, a power module 5 and a wireless module 6 are arranged in the casing 1, and the signal integrated processing module 4 is electrically connected with the pressure sensor 3, the power module 5 and the wireless module 6 respectively.
Step a specifically means that the screw blade rotating rod 2 transmits torque to the pressure sensor 3, the pressure sensor 3 converts a force signal into a voltage signal, the voltage signal is processed through the signal integration processing module 4, then data are transmitted to the upper computer through wireless transmission, the upper computer obtains a digital signal, and the upper computer software processes the data to obtain a torque value applied to the screw by the screw blade.
The embodiment is a preferred embodiment, the wire harness pulling-out force is predicted by carrying out simulation calculation on the wire harness pulling-out force, the calculation is simple and convenient, the device is beneficial to being popularized to the machine to measure the pulling-out preventing effect achieved by the clamp after the installation is completed in real time, and the applicability is good.
Example 3
Referring to fig. 1-3, an aircraft harness pull-out force calculation method includes the steps of:
a. measuring the axial pressure of the bolt applied to the screw by a pressure collecting screw blade;
b. Performing program design, wherein an input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database, the bolt axial pressure measured by a pressure acquisition screw blade is transmitted to an upper computer in a wireless manner, and the friction coefficient of the wire harness surface is obtained from the friction coefficient database;
c. calculating stress between the clamp and the wire harness through the method 1;
1 (1)
Wherein,For stress between the clip and the wire harness,/>Is the axial pressure/>The radius of the clamp after deformation is h, and the width of the clamp is h;
d. calculating the stressed area of the clamp through the method 2;
2, 2
Wherein S is the stress area of the clamp,The radius of the clamp after deformation is h, and the width of the clamp is h;
e. The pulling-out force of the clamp on the wire harness is calculated through a 3 method by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness;
3
Wherein,For the pulling-out force of the clamp to the wire harness,/>Is the coefficient of friction of the wire harness surface,/>Is the axial pressure of the bolt;
f. And e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, and judging to be qualified if the calculated value is in a range of 1-1.5 times of the standard value.
In the step a, the pressure acquisition screwdriver comprises a shell 1 and a screwdriver rotating rod 2 arranged on the shell 1, wherein a pressure sensor 3, a signal integration processing module 4, a power module 5 and a wireless module 6 are arranged in the shell 1, and the signal integration processing module 4 is electrically connected with the pressure sensor 3, the power module 5 and the wireless module 6 respectively.
Step a specifically means that the screw blade rotating rod 2 transmits torque to the pressure sensor 3, the pressure sensor 3 converts a force signal into a voltage signal, the voltage signal is processed through the signal integration processing module 4, then data are transmitted to the upper computer through wireless transmission, the upper computer obtains a digital signal, and the upper computer software processes the data to obtain a torque value applied to the screw by the screw blade.
Further, the signal integrated processing module 4 processes the voltage signal specifically means that the voltage signal is processed by removing ripple, adjusting zero point, amplifying and analog-to-digital conversion.
Further, the transmitting the data to the upper computer through wireless transmission specifically means transmitting through bluetooth.
The pressure sensor 3 is configured to detect a force signal and convert the force signal into a voltage signal.
The power module 5 is used for providing electric energy for the signal integrated processing module 4.
The wireless module 6 is used for wireless transmission of data.
The embodiment is the best mode, can effectively evaluate the clamping effect of clamp to the pencil, improve the pencil because the security problem that the fastening is not in place produced.
Stress between clip and harnessThe derivation process is as follows:
After the wiring harness is laid on the aircraft, the wiring harness can be fixed by using the clamp, and the upper lug of the clamp is axially pressed by the bolt Under the action of the clamp lug distance variation is/>. Meanwhile, the BC section of the clamp deforms towards the center of a circle, extrusion force is generated on the wire harness in the clamp, and the radius of the clamp is equal to the radius/>, before deformationReducing to the radius/>The variation of the radius of the clamp is/>The left and right direction force direction of the clamp is opposite, and the CD section is connected and fixed on the structure, which is regarded as fixed constraint, and no deformation is generated. When the clamp generates extrusion force to the wire harness along the circumferential direction, the wire harness generates reaction force to the circumferential direction of the clamp, and the resultant force/>And the vertical direction is opposite to the force direction of the screw to the lug and the deformation of the clamp.
Assuming a clamp width of h, the clamp radius after deformation isThe area of the 3/4 circle clamp is:
Reaction resultant force:
the work done by the screw on the lug and the work done by the clamp on the wire harness are both The wire harness overcomes the defect that the clamp does/>Then:
Thus, there are:
namely, the stress between the clamp and the wire harness is as follows: 。
The calculation principle of the clamp bearing area S is as follows:
Assuming that the band is extruded with a change in surface area which is small relative to the overall surface area, and negligible, the surface area is the circumferential length multiplied by the width of the band, i.e The main stress area is A-C section, then clamp stress area is:。
The invention is illustrated below by way of specific examples:
The surface material of the wire harness is polytetrafluoroethylene, the surface material of the clamp is ethylene propylene rubber, and the surface friction coefficient of the wire harness 0.25, Bolt axial pressure exerted on the screw/>12.5N, carry-in 3, calculate the pulling-out force of the clamp to the wire harness17.87N, a standard value range is 15.5-23.25N, and when the force of the clamp to the wire harness is smaller than 15.5N, the wire harness is at risk of loosening; if the number of the wire harness is larger than 23.25N, the wire harness is subjected to a large clamping force, and the wire core is deformed so as to influence the strength of the metal wire core. 17.87N is between 15.5N and 23.25N, meets the safety requirement of the wire harness, and is qualified.
Claims (8)
1. The aircraft wire harness pulling-out force calculating method is characterized by comprising the following steps of:
a. measuring the axial pressure of the bolt applied to the screw by a pressure collecting screw blade;
b. Performing program design, wherein an input layer comprises a bolt axial pressure database, a friction coefficient database and a pull-out force database, the bolt axial pressure measured by a pressure acquisition screw blade is transmitted to an upper computer in a wireless manner, and the friction coefficient of the wire harness surface is obtained from the friction coefficient database;
c. calculating stress between the clamp and the wire harness through the method 1;
1 (1)
Wherein,For stress between the clip and the wire harness,/>Is the axial pressure/>The radius of the clamp after deformation is h, and the width of the clamp is h;
d. calculating the stressed area of the clamp through the method 2;
2, 2
Wherein S is the stress area of the clamp,The radius of the clamp after deformation is h, and the width of the clamp is h;
e. The pulling-out force of the clamp on the wire harness is calculated through a 3 method by combining the surface friction coefficient of the wire harness, the stress area of the clamp and the stress between the clamp and the wire harness;
3
Wherein,For the pulling-out force of the clamp to the wire harness,/>Is the coefficient of friction of the wire harness surface,/>Is the axial pressure of the bolt;
f. And e, comparing the pulling-out force value of the wire harness with a standard value in a pulling-out force standard database by the clamp obtained by calculation in the step e, and judging to be qualified if the calculated value is in a range of 1-1.5 times of the standard value.
2. The aircraft harness pull-out force calculation method according to claim 1, characterized in that: in the step a, the pressure acquisition screwdriver comprises a shell (1) and a screwdriver rotating rod (2) arranged on the shell (1), wherein a pressure sensor (3), a signal integration processing module (4), a power module (5) and a wireless module (6) are arranged in the shell (1), and the signal integration processing module (4) is electrically connected with the pressure sensor (3), the power module (5) and the wireless module (6) respectively.
3. The aircraft harness pull-out force calculation method according to claim 2, characterized in that: step a specifically means that the screw knife rotating rod (2) transmits torque to the pressure sensor (3), the pressure sensor (3) converts a force signal into a voltage signal, the voltage signal is processed through the signal integration processing module (4), then data are transmitted to the upper computer through wireless transmission, the upper computer acquires a digital signal, and the upper computer software processes the data to obtain a torque value applied to the screw by the screw knife.
4. The aircraft harness pull-out force calculation method according to claim 3, characterized in that: the signal integrated processing module (4) processes the voltage signal specifically to perform ripple removal, zero adjustment, amplification and analog-to-digital conversion processing on the voltage signal.
5. The aircraft harness pull-out force calculation method according to claim 3, characterized in that: the data transmission to the upper computer through wireless transmission specifically means transmission through Bluetooth.
6. The aircraft harness pull-out force calculation method according to claim 2, characterized in that: the pressure sensor (3) is used for detecting a force signal and converting the force signal into a voltage signal.
7. The aircraft harness pull-out force calculation method according to claim 2, characterized in that: the power module (5) is used for providing electric energy for the signal integrated processing module (4).
8. The aircraft harness pull-out force calculation method according to claim 2, characterized in that: the wireless module (6) is used for wireless transmission of data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310380784.4A CN116659720B (en) | 2023-04-11 | 2023-04-11 | Aircraft harness pulling-out force calculation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310380784.4A CN116659720B (en) | 2023-04-11 | 2023-04-11 | Aircraft harness pulling-out force calculation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116659720A CN116659720A (en) | 2023-08-29 |
| CN116659720B true CN116659720B (en) | 2024-06-11 |
Family
ID=87708644
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310380784.4A Active CN116659720B (en) | 2023-04-11 | 2023-04-11 | Aircraft harness pulling-out force calculation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116659720B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1560595A (en) * | 2004-02-19 | 2005-01-05 | 上海交通大学 | Friction coefficient measuring system |
| CN104732005A (en) * | 2014-12-27 | 2015-06-24 | 长城汽车股份有限公司 | Terminal pulling-out force detecting method |
| CN111523211A (en) * | 2020-04-13 | 2020-08-11 | 中车青岛四方机车车辆股份有限公司 | Cable pull-out force processing method and device, storage medium and processor |
| CN112033844A (en) * | 2020-07-28 | 2020-12-04 | 成都飞机工业（集团）有限责任公司 | Multi-working-condition simulated aircraft wire harness abrasion experimental equipment and experimental method |
| CN114876783A (en) * | 2022-05-24 | 2022-08-09 | 浙江大学高端装备研究院 | Embedded pull-out force measuring device for plunger piston shoe structure |
-
2023
- 2023-04-11 CN CN202310380784.4A patent/CN116659720B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1560595A (en) * | 2004-02-19 | 2005-01-05 | 上海交通大学 | Friction coefficient measuring system |
| CN104732005A (en) * | 2014-12-27 | 2015-06-24 | 长城汽车股份有限公司 | Terminal pulling-out force detecting method |
| CN111523211A (en) * | 2020-04-13 | 2020-08-11 | 中车青岛四方机车车辆股份有限公司 | Cable pull-out force processing method and device, storage medium and processor |
| CN112033844A (en) * | 2020-07-28 | 2020-12-04 | 成都飞机工业（集团）有限责任公司 | Multi-working-condition simulated aircraft wire harness abrasion experimental equipment and experimental method |
| CN114876783A (en) * | 2022-05-24 | 2022-08-09 | 浙江大学高端装备研究院 | Embedded pull-out force measuring device for plunger piston shoe structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116659720A (en) | 2023-08-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108709724B (en) | Online bolt state monitoring system and method for wind generating set | |
| CN101718582B (en) | Tone testing method of wind power generator set | |
| EP3538757A1 (en) | Wind turbine noise analysis and control | |
| CN116659720B (en) | Aircraft harness pulling-out force calculation method | |
| CN207888246U (en) | It is a kind of can online acquisition Tool in Cutting force signal fixture | |
| CN113390591A (en) | On-load tap-changer mechanical vibration detection system and method based on 5G network | |
| US20040083009A1 (en) | Control embedded machine condition monitor | |
| KR101749646B1 (en) | Apparatus and nethod for measuring acoustic and vibration spectrum of high maneuvering vehicle system | |
| CN107240559A (en) | A kind of system and method for real-time monitoring etching cavity metals content impurity | |
| JP6709551B2 (en) | Abnormal lightning strike determination system and method of attaching abnormal lightning strike determination system to wind power generation facility | |
| CN211783846U (en) | Portable engine abnormal sound identification and positioning system | |
| CN201628754U (en) | Wideband partial discharge detection device for power equipment | |
| CN219200613U (en) | Vibration measuring device for driving chain slip ring of wind generating set | |
| CN113008539B (en) | Wireless transmission rotary encoder acquisition card and application | |
| CN113984392B (en) | Online testing and evaluating method for vibration quality of electric drive assembly system | |
| CN213397008U (en) | Automatic on-line monitoring device and system for cable clamp slippage | |
| CN210165887U (en) | Generator magnetic pole connecting wire and excitation lead deformation monitoring device | |
| CN104972423B (en) | Bolt screwing detection method, device and system | |
| CN209698220U (en) | A kind of high speed to-and-fro thread electrode wire of wire-cutting machine tools tension detecting apparatus | |
| CN203551104U (en) | Fixing clamp for hand-held vibration measurer | |
| CN202329804U (en) | Online monitoring system for vibration of auxiliary engine of generator | |
| CN112578218A (en) | Method and device for identifying broken strands of overhead conductors | |
| CN213147752U (en) | Aeroengine bearing clearance detection device based on vibration principle | |
| CN111158297A (en) | Bridge template data acquisition and control system | |
| CN207195296U (en) | A kind of instrument for being used to install draught fan impeller counterweight |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |