CN111964856A - Special pin shaft for vibration test of aviation launcher and use method thereof - Google Patents
Special pin shaft for vibration test of aviation launcher and use method thereof Download PDFInfo
- Publication number
- CN111964856A CN111964856A CN202010685819.1A CN202010685819A CN111964856A CN 111964856 A CN111964856 A CN 111964856A CN 202010685819 A CN202010685819 A CN 202010685819A CN 111964856 A CN111964856 A CN 111964856A
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- pin shaft
- shaft sleeve
- aviation
- vibration test
- core rod
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000009471 action Effects 0.000 claims abstract description 4
- 230000008569 process Effects 0.000 claims description 4
- 238000004088 simulation Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 9
- 238000002474 experimental method Methods 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 abstract description 3
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to the field of aviation special tools, in particular to a special pin shaft for a vibration test of an aviation launcher and a using method thereof, the special pin shaft comprises a special pin shaft for mounting the aviation launcher for hanging simulated bombs on a vibration test bed, the special pin shaft comprises a pin shaft sleeve with a central hole, a core rod matched with the central hole of the pin shaft sleeve, a cone nut for supporting the pin shaft sleeve under the combined action of the core rod, and a clamp arranged on the end part of the cone nut for safety, and the special pin shaft comprises the following specific steps: s1; the surfaces of the matching holes are aligned; s2; assembling a special pin shaft; s3; assembling a core rod; s4; disassembling the lock nut; s5; assembling the whole; s6; assembling a clamp; through improving the fit clearance precision between aviation emitter and the vibration test platform with the round pin axle for the installation between the three is simple, very big improvement vibration test's efficiency, the three takes place the back that wears because of the vibration simultaneously, and the installation accuracy is high, and the experiment can go on smoothly.
Description
Technical Field
The invention relates to the field of aviation special tools, in particular to a special pin shaft for a vibration test of an aviation launcher and a use method thereof.
Background
After the military aviation launcher is repaired, a vibration environment test in simulated flight is required to be carried out, in the test process, the safety of the device and equipment is guaranteed, abnormal impact caused by installation gaps among clamps is prevented, and therefore when the aviation launcher is installed on a test bed, the gaps among hanging points of the aviation launcher, lifting lugs of the test bed and connecting pins are reduced as much as possible; when the gap between the three parts is too small, the mounting of the hanging point of the aviation launcher, the lifting lug of the test bed and the connecting pin shaft is difficult to carry out. The special pin shaft for the aviation launcher vibration test greatly improves the problems, so that the aviation launcher is simple and convenient to operate when being hung on a vibration test bed, and meanwhile, the mounting gaps of the hanging point of the aviation launcher, the lifting lug of the test bed and the connecting pin shaft are reduced to the utmost extent.
Because the aerial launcher suspending the simulated bomb has larger mass, the mass of the aerial launcher is generally over 200 Kg; meanwhile, the precision of the fit clearance between the special pin shaft and the aviation launching device and between the special pin shaft and the vibration test bed is high; therefore, the three of the hanging point of the aviation launcher, the lifting lug of the test bed and the connecting pin shaft are extremely difficult to mount and fix, the efficiency of the vibration test is greatly influenced, and meanwhile, after the three are abraded due to vibration, the three are very easy to pause due to low mounting precision, and the test cannot be carried out.
The clearance control during normal matching is ensured by the dimensional tolerance between the pin bolt and the hanging point of the aviation launcher and between the pin bolt and the lifting lug of the test bed, and when the requirement on the matching precision is higher, a smaller clearance can be achieved only by matching the dimensional tolerance with higher precision; when the hole surface between the hanging point of the aviation launcher and the lifting lug of the test bed is kept in alignment, the pin shaft can be smoothly inserted, otherwise, the pin shaft needs to be repeatedly adjusted or knocked by a hammer to enter. Meanwhile, the aviation launcher has heavier mass, and the installation is difficult because the hole surfaces between the hanging point of the aviation launcher and the test bed lifting lug can not be kept aligned basically during installation.
Disclosure of Invention
In order to solve the problems, the invention provides a special pin shaft for a vibration test of an aviation launcher and a using method thereof.
The special pin shaft comprises a pin shaft sleeve with a central hole, a core rod matched with the central hole of the pin shaft sleeve, a cone nut for supporting the pin shaft sleeve under the combined action of the core rod, and a clamp arranged at the end part of the cone nut and used for insurance.
And the aviation launching device and the vibration test bed are both provided with matching hole surfaces for mounting the pin shaft sleeves.
The two ends of the pin shaft sleeve are both provided with conical surfaces matched with the core rod and the conical nut.
The pin shaft sleeve is a circular sleeve which axially divides the pin shaft sleeve into three equal sections, and the diameter of the cylindrical surface of the pin shaft sleeve is 1mm smaller than the diameter of the hole surface matched with the cylindrical surface.
The outer surface of one end of the pin shaft sleeve is provided with a locking nut which is used for preventing the pin shaft sleeve from automatically scattering when the pin shaft sleeve is inserted into the matching hole surfaces of an aviation launching device and a vibration test bed.
A use method of a special pin shaft for a vibration test of an aviation launcher comprises the following specific steps:
s1: the matching hole faces are aligned: keeping the matching hole surfaces of the aviation launching device 1 and the vibration test bed aligned;
s2: assembling a special pin shaft: after the pin shaft sleeve, the core rod and the lock nut are assembled together, an integral pin shaft is formed and inserted into the matching hole surfaces of the aviation emission device and the vibration test bed;
s3: assembling a core rod: assembling a cone nut to the tail part of the core rod and screwing the cone nut to the bottom by hands;
s4: dismantling a lock nut: removing the lock nut from the pin sleeve;
s5: assembling the whole body: two wrenches are used for applying force to the core rod and the hexagon head of the conical nut until the pin shaft sleeve is separated and completely contacted with a hanging point of the aviation launching device and a hole surface of a lifting lug of the test bed, and the clearance between the core rod and the hexagon head of the conical nut is minimum;
s6: assembling a hoop: after the pin shaft sleeve, the core rod and the conical nut are installed in place, the clamp is inserted into safety holes of the core rod and the conical nut, and the core rod and the conical nut are prevented from being matched and loosened in the vibration test process.
In step S3, force is applied by hands without using a wrench.
The invention has the beneficial effects that: through improving the fit clearance precision between aviation emitter and the vibration test platform with the round pin axle for the installation between the three is simple, very big improvement vibration test's efficiency, the three takes place the back that wears because of the vibration simultaneously, and the installation accuracy is high, and the experiment can go on smoothly.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic structural diagram of an aviation launcher, a simulated bomb, a vibration test bed and a special pin shaft of the invention;
FIG. 2 is a schematic view of a local structure of an aviation launcher, a vibration test stand and a special pin shaft of the present invention;
FIG. 3 is a schematic view of the structure of a dedicated pin according to the present invention;
FIG. 4 is a schematic side view of the special pin of the present invention;
FIG. 5 is a schematic view of the pin boss configuration of the present invention;
FIG. 6 is a schematic structural view of a core rod of the present invention;
FIG. 7 is a first schematic view of a cone nut according to the present invention;
FIG. 8 is a second schematic structural view of a cone nut of the present invention;
FIG. 9 is a first schematic view of a lock nut of the present invention;
FIG. 10 is a second schematic view of a cage nut of the present invention;
fig. 11 is a schematic view of a connecting pin structure according to the background art.
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.
As shown in fig. 1 to 11, the special pin shaft for the vibration test of the aircraft launcher comprises a special pin shaft 4 for mounting the aircraft launcher 1 for hanging the simulated bomb 2 on a vibration test bed 3, wherein the special pin shaft 4 comprises a pin shaft sleeve 4-1 with a central hole, a core rod 4-2 matched with the central hole of the pin shaft sleeve 4-1, a cone nut 4-4 for supporting the pin shaft sleeve 4-1 under the combined action of the core rod 4-2, and a clamp 4-5 arranged on the end part of the cone nut 4-4 for safety.
The aviation launcher 1 and the vibration test bed 3 are both provided with matching hole surfaces for mounting the pin shaft sleeves 4-1, and the pin shaft sleeves and the vibration test bed can be easily inserted into the matching holes during matching.
Two ends of the pin shaft sleeve 4-1 are respectively provided with a conical surface matched with the core rod 4-2 and the conical nut 4-4.
The pin shaft sleeve 4-1 is a circular sleeve which axially divides the pin shaft sleeve into three equal sections, and the diameter of the cylindrical surface of the pin shaft sleeve 4-1 is 1mm smaller than the diameter of the hole surface matched with the cylindrical surface.
The outer surface of one end of the pin shaft sleeve 4-1 is provided with a threaded groove matched with a lock nut 4-3 for preventing the pin shaft sleeve 4-1 from automatically scattering when the pin shaft sleeve 4-1 is inserted into the matched hole surfaces of the aviation launcher 1 and the vibration test bed 3.
Through improving the fit clearance precision between aviation emitter 1 and vibration test platform 3 with round pin axle 4 for installation between the three is simple, very big improvement vibration test's efficiency, and the three takes place the back of wearing and tearing because of the vibration simultaneously, and the installation accuracy is high, and the experiment can go on smoothly.
The lock nut 4-3 has the following functions: 1. when the pin shaft sleeve 4-1 is inserted into the matching hole surfaces of the aviation emission device 1 and the vibration test bed 3, the pin shaft sleeve 4-1 is prevented from automatically scattering and is not easy to install; 2. when the pin shaft sleeve 4-1 is inserted into the matching hole surfaces of the aviation launcher 1 and the vibration test bed 3, the pin shaft sleeve 4-1, the core rod 4-2 and the lock nut 4-3 form an integral pin shaft, so that the pin shaft sleeve 4-1 is prevented from being not cylindrical due to uneven stress.
A use method of a special pin shaft for a vibration test of an aviation launcher comprises the following specific steps:
s1: the matching hole faces are aligned: keeping the matching hole surfaces of the aviation launching device 1 and the vibration test bed 3 aligned;
s2: assembling the special pin shaft 4: assembling a pin shaft sleeve 4-1, a core rod 4-2 and a lock nut 4-3 together to form an integral pin shaft which is inserted into the matching hole surfaces of the aviation launcher 1 and the vibration test bed 3;
s3: assembling a core rod 4-2: assembling a cone nut 4-4 to the tail part of the core rod 4-2 and screwing the cone nut to the bottom by hands;
s4: and (4) disassembling the lock nut 4-3: the lock nut 4-3 is removed from the pin shaft sleeve 4-1;
s5: assembling the whole body: two wrenches are used for applying force to the core rod 4-2 and the hexagon head of the conical nut 4-4 until the pin shaft sleeve 4-1 is separated from the aircraft launching device 1 and is completely contacted with the hole surface of the lifting lug of the test bed 3, and the clearance between the core rod 4-2 and the hexagon head of the conical nut 4-4 is minimum;
s6: assembling a hoop 4-5: after the pin shaft sleeve 4-1, the core rod 4-2 and the cone nut 4-4 are installed in place, the clamp 4-5 is inserted into safety holes of the core rod 4-2 and the cone nut 4-4, and the core rod 4-2 and the cone nut 4-4 are prevented from being matched and loosened in the vibration test process.
In step S3, force is applied by hands without using a wrench.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides a special round pin axle for aeronautical launcher vibration test which characterized in that: the device comprises a special pin shaft (4) for installing an aviation launching device (1) for hanging a simulation bomb (2) on a vibration test bed (3), wherein the special pin shaft (4) comprises a pin shaft sleeve (4-1) with a central hole, a core rod (4-2) matched with the central hole of the pin shaft sleeve (4-1), a conical nut (4-4) for supporting the pin shaft sleeve (4-1) under the combined action of the core rod (4-2), and a clamp (4-5) arranged at the end part of the conical nut (4-4) and used for safety.
2. The special pin for the vibration test of the aviation launcher according to claim 1, wherein: and the aviation launching device (1) and the vibration test bed (3) are respectively provided with a matching hole surface for mounting the pin shaft sleeve (4-1).
3. The special pin for the vibration test of the aviation launcher according to claim 1, wherein: two ends of the pin shaft sleeve (4-1) are respectively provided with a conical surface matched with the core rod (4-2) and the conical nut (4-4).
4. The special pin for the vibration test of the aviation launcher according to claim 1, wherein: the pin shaft sleeve (4-1) is a circular sleeve which axially divides the pin shaft sleeve into three equal sections, and the diameter of the cylindrical surface of the pin shaft sleeve (4-1) is 1mm smaller than the diameter of the hole surface matched with the cylindrical surface.
5. The special pin for the vibration test of the aviation launcher according to claim 2, wherein: the outer surface of one end of the pin shaft sleeve (4-1) is provided with a threaded groove matched with a lock nut (4-3) used for preventing the pin shaft sleeve (4-1) from automatically dispersing when the pin shaft sleeve (4-1) is inserted into the matching hole surfaces of the aviation launching device (1) and the vibration test bed (3).
6. Use of a special pin for vibration tests of aircraft launching devices according to any of claims 1 to 5, characterized in that: the method comprises the following specific steps:
s1: the matching hole faces are aligned: keeping the matching hole surfaces of the aviation launching device (1) and the vibration test bed (3) aligned;
s2: assembling the special pin shaft (4): assembling a pin shaft sleeve (4-1), a core rod (4-2) and a lock nut (4-3) together to form an integral pin shaft to be inserted into the matching hole surfaces of the aviation emission device (1) and the vibration test bed (3);
s3: assembling core bar (4-2): assembling a cone nut (4-4) to the tail part of the core rod (4-2) and screwing the cone nut to the bottom by hands;
s4: removing the lock nut (4-3): the lock nut (4-3) is detached from the pin shaft sleeve (4-1);
s5: assembling the whole body: two wrenches are used for applying force to the core rod (4-2) and the hexagonal head of the conical nut (4-4) until the pin shaft sleeve (4-1) is separated and is completely contacted with a hanging point of the aviation launching device (1) and a hole surface of a lifting lug of the test bed (3), and the clearance between the core rod (4-2) and the hexagonal head of the conical nut (4-4) is minimum;
s6: assembling the clamp (4-5): after the pin shaft sleeve (4-1), the core rod (4-2) and the cone nut (4-4) are installed in place, the clamp (4-5) is inserted into safety holes of the core rod (4-2) and the cone nut (4-4), and the core rod (4-2) and the cone nut (4-4) are prevented from being matched and loosened in the vibration test process.
7. The use method of the special pin for the vibration test of the aircraft launcher according to claim 6, characterized in that: in step S3, force is applied by hands without using a wrench.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010685819.1A CN111964856A (en) | 2020-07-16 | 2020-07-16 | Special pin shaft for vibration test of aviation launcher and use method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010685819.1A CN111964856A (en) | 2020-07-16 | 2020-07-16 | Special pin shaft for vibration test of aviation launcher and use method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111964856A true CN111964856A (en) | 2020-11-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010685819.1A Pending CN111964856A (en) | 2020-07-16 | 2020-07-16 | Special pin shaft for vibration test of aviation launcher and use method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111964856A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3762881A (en) * | 1971-06-14 | 1973-10-02 | Federal Mogul Corp | Composite high strength machine element and method of making the same |
| US5362185A (en) * | 1991-03-23 | 1994-11-08 | Connex Ag | Device for positioning components |
| CN2907863Y (en) * | 2006-04-04 | 2007-06-06 | 郑州人造金刚石及制品工程技术研究中心 | Radial movable location pin shaft |
| CN102537006A (en) * | 2012-02-27 | 2012-07-04 | 湖南山河科技股份有限公司 | Positioning connection pin |
| CN104110426A (en) * | 2014-07-04 | 2014-10-22 | 大连渤海金加机器有限公司 | Non-clearance-fit hinge pin |
| CN204980783U (en) * | 2015-07-27 | 2016-01-20 | 天津中际装备制造有限公司 | Inflation round pin axle of usefulness is assembled to ocean module rig structure sled piece |
| CN105782195A (en) * | 2016-05-19 | 2016-07-20 | 辽宁辽鞍机械制造有限公司 | Expansion cylindrical pin for location |
| CN207058400U (en) * | 2017-07-19 | 2018-03-02 | 天津飞悦航空工业股份有限公司 | A kind of three-pawl type alignment pin |
| CN109989976A (en) * | 2019-03-26 | 2019-07-09 | 石家庄铁道大学 | A kind of steel pin for eliminating hole |
-
2020
- 2020-07-16 CN CN202010685819.1A patent/CN111964856A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3762881A (en) * | 1971-06-14 | 1973-10-02 | Federal Mogul Corp | Composite high strength machine element and method of making the same |
| US5362185A (en) * | 1991-03-23 | 1994-11-08 | Connex Ag | Device for positioning components |
| CN2907863Y (en) * | 2006-04-04 | 2007-06-06 | 郑州人造金刚石及制品工程技术研究中心 | Radial movable location pin shaft |
| CN102537006A (en) * | 2012-02-27 | 2012-07-04 | 湖南山河科技股份有限公司 | Positioning connection pin |
| CN104110426A (en) * | 2014-07-04 | 2014-10-22 | 大连渤海金加机器有限公司 | Non-clearance-fit hinge pin |
| CN204980783U (en) * | 2015-07-27 | 2016-01-20 | 天津中际装备制造有限公司 | Inflation round pin axle of usefulness is assembled to ocean module rig structure sled piece |
| CN105782195A (en) * | 2016-05-19 | 2016-07-20 | 辽宁辽鞍机械制造有限公司 | Expansion cylindrical pin for location |
| CN207058400U (en) * | 2017-07-19 | 2018-03-02 | 天津飞悦航空工业股份有限公司 | A kind of three-pawl type alignment pin |
| CN109989976A (en) * | 2019-03-26 | 2019-07-09 | 石家庄铁道大学 | A kind of steel pin for eliminating hole |
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Application publication date: 20201120 |