CN208621282U - A kind of impact test cohesion device - Google Patents
A kind of impact test cohesion device Download PDFInfo
- Publication number
- CN208621282U CN208621282U CN201821119900.8U CN201821119900U CN208621282U CN 208621282 U CN208621282 U CN 208621282U CN 201821119900 U CN201821119900 U CN 201821119900U CN 208621282 U CN208621282 U CN 208621282U
- Authority
- CN
- China
- Prior art keywords
- buckle
- lock
- fixing seat
- face
- testpieces
- 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
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A kind of impact test cohesion device including the fuselage connector being used cooperatively and returns lock.When testpieces is to buffer direction high-speed motion and collides, bayonet ramp in fuselage connector is contacted with lock bevel edge is returned, under the action of perpendicular to lock inclined edge surfaces downward force and two buckle middle springs are returned, buckle does circular motion clockwise by axle center of rear end, two buckle front end distances are reduced, Hui Suozhong is put in.Under the action of recoil of spring power, buckle moment returns to original state and is stuck in go back to lock seaming edge, and " holding " for completing testpieces and buffer acts.It is zero that final testpieces slows down under the action of buffer.The utility model is in the test of Mr. Yu's type inertial load, guarantee the connection that the type testpieces can be solid and reliable with buffer in inertial load simulation test, the direction of motion of Control experiment part avoids testpieces from being rebounded when big load impacts buffer by counter-force and testpieces is caused to damage.
Description
Technical field
It is specifically a kind of to be carried with Mr. Yu's type fuselage inertia the present invention relates to airframe inertial load experimental technique field
The collision cohesion device of lotus test.
Background technique
In certain type inertia test, due to making testpieces and buffer in big load impact without reliable and effective device
Contact both held tightly, testpieces after being contacted with buffer due to bounce cause testpieces towards load opposite direction move so that
Testpieces moves uncontrolled and damage test part.To need a kind of device can by certain type and buffer in big load,
Solid and reliable connection is integral under high speed impact, and in view of fuselage testpieces simulates in test practical shape as far as possible
Condition can carry out counterweight to the forward and backward position of testpieces, reach the actual state of complete machine.So, it is desirable that the apparatus structure is simple, weight
It measures small, is easily installed and adjusts.
Application No. is a kind of coupler and draft gear is disclosed in 201120244959.1 innovation and creation, it to be used for rolling stock
Between connection, predominantly obtain biggish bearings free misalignment, so enable locomotive smoothly, smoothly through curve circuit.
Due to using the limitation of object, the type coupler and draft gear is caused, joint freedom degree is big, and weight is high, and hitch is up to 1370mm
And structure is complicated, manufacturing cost is high, is not able to satisfy inertial load test requirements document.
Application No. is disclosing a kind of eye-splice in 00232707.4 innovation and creation, the connection being chiefly used between rope band, material
Material is mostly plastics or metal foil wall pieces, and bearing capacity is weak, and small in size, shape is mostly rectangle, is not easy to the installation and adjustment in later period.Institute
With the limitation of the structural strength and use scope of eye-splice is not able to satisfy inertial load test requirements document.
Summary of the invention
For overcome it is existing in the prior art structure is complicated, manufacturing cost is high, and be not able to satisfy inertial load test and want
The deficiency asked, the invention proposes a kind of impact test cohesion devices.
The present invention includes the fuselage connector being used cooperatively and time lock.The fuselage connector includes closed plate, buckles admittedly
Reservation, spring and buckle, wherein closed plate is located in the inner hole of described buckle fixing seat one end, one end difference of two buckles
It is mounted in the cross bath of the buckle fixing seat the other end face, and makes the positional symmetry of this two buckles；Two spring peaces
Be placed between described two buckles, held out against this two buckles by two springs, make it is each buckle with buckle fixing seat ten
Font groove inner surface is adjacent to.Symmetrically there are two adjusting screws for installation on the excircle of the buckle fixing seat, and respectively adjust
The central axis of screw is saved in the center line of the buckle fixing seat.
The inner hole of described time lock is divided into guide section, changeover portion and returns lock cooperation section；Wherein, it is located at the Hui Suoyu fuselage
Connector cooperates the inner surface of the guide section of one end to be the containing conical surface, the fixture block outer end on the taper of the conical surface and the bayonet
The taper in face is identical；The internal diameter of the described time lock other end is maximum, to return lock cooperation section, the internal diameter and described two of this time lock cooperation section
The spacing between each fixture block protrusion surface after a bayonet assembly is identical.The changeover portion is isometrical section, is located at guide section
Cooperate between section with lock is returned；Changeover portion from return lock cooperation the internal diameter of section it is different, formation step difference, the end face of the step difference with it is described
Positioning surface cooperation on bayonet.External peripheral surface described time lock cooperation section end face has the flange of joint test part.
One end of the buckle fixing seat is connect with fuselage, and the geometric center of the other end face through slot cruciferous should
The length of through slot vertical direction must meet after two buckles are mounted in the through slot, the outer end face of the fixture block on this two buckle tops
Height respectively than described time lock isometrical section internal diameter it is 2.5mm big；The length of the through slot horizontal direction should meet described in installation
Each buckle.It is symmetrical there are two the mounting hole for adjusting screw in the circumferential surface of the buckle fixing seat, and make the adjusting spiral shell
Nail mounting hole is located at the both ends of the through slot vertical direction.
The outer diameter of the closed plate is identical as the buckle fixing seat fuselage connecting pin internal diameter, and matches gap between the two
It closes.The connecting hole for connecting fuselage tooling is evenly equipped on the surface of the closed plate.
There are two the buckles, is made of respectively blend stop and time lock connecting plate, and between the blend stop and time lock connecting plate
It is mutually perpendicular to, keeps the shape of buckle in T shape.There is the card for protruding this go back to lock connecting plate outer surface in the end of this time lock connecting plate
Block；The fixture block and the step difference returned between lock connecting plate outer surface are formed by the positioning surface that inner face is the buckle；The card
The outer end face of block is inclined-plane.In each time lock connecting plate inner surface, there are two spring installing blinds.
When assembly, the blend stop is located in the inner hole of buckle fixing seat, returns lock connecting plate and is located in cross through slot, Hui Suo
The fixture block of connecting plate outer end is located at except buckle fixing seat.
The present invention guarantees type testpieces energy in inertial load simulation test in the test of Mr. Yu's type inertial load
Enough and solid and reliable buffer connections, the direction of motion of Control experiment part avoid testpieces from impacting buffer in big load
When rebounded by counter-force testpieces caused to damage.
When testpieces drives preceding part to buffer direction high-speed motion and with rear local collision, bayonet ramp is locked with returning
Bevel edge contact, the closed plate axial position that buckle rear end part is fixed on buffer end face limit, perpendicular to time lock bevel edge
Towards under the action of exerting oneself and under the effect of two buckle middle springs, and buckle front end recoil of spring power is less than rear end spring
Screen resilience, buckle does circular motion clockwise as axle center using rear end and two buckle front end distances reduce, and puts in Hui Suozhong.?
Under the action of recoil of spring power, buckle moment returns to original state, and buckle is stuck in go back to lock seaming edge, i.e. completion testpieces and buffer
" holding " movement.It is zero that final testpieces slows down under the action of buffer.After completing a collision and holding the period tightly, adjust
It adjusts screw and is pressed downward front is buckled, until buckle topmost edge is lower than go back to lock bevel edge bottom, then in the effect of external force
Under, buckle exits back lock.
The present invention by collision cohesion device by inertia test fuselage testpieces and the simple and reliable connection of buffer
Together, it is convenient for later period installation and adjustment.The part used in the present invention is mostly revolving parts, convenient processing and manufacture.At certain
In the inertia test of kind of type, problem is collided and held tightly to effective solution between testpieces and buffer, avoids testpieces,
Big load, which is rebounded when impacting buffer by counter-force, causes testpieces to damage, and improves the safety of test, tries in airplane inertial
Work is offered reference and referred to for problems in testing, assists smoothly completing for aircraft inertial load test.
Detailed description of the invention
Fig. 1 is the right view three dimensional structure diagram of the present invention；
Fig. 2 is left view schematic three dimensional views of the present invention；
Fig. 3 is structural schematic diagram of the invention；
Fig. 4 is back the structural schematic diagram of lock；
Fig. 5 is the side view of Fig. 4；
Fig. 6 is the structural schematic diagram of buckle；
Fig. 7 is the top view of Fig. 6；
Fig. 8 is the structural schematic diagram for buckling fixing seat；
Fig. 9 is the B-B direction view in Fig. 8；
Figure 10 is the structural schematic diagram of closed plate；
Figure 11 is the C-C direction view in Figure 10.
In figure: 1. times locks；2. buckle；3. spring；4. adjusting screw；5. buckling fixing seat；6. closed plate.
Specific embodiment
The present embodiment is a kind of inertial load test collision cohesion device, including fuselage connector and returns lock, therein time
Lock is used cooperatively with fuselage connector.
The fuselage connector includes closed plate 6, buckle fixing seat 5, spring 3 and buckle 2, wherein closed plate 6 is located at institute
In the inner hole for stating buckle 5 one end of fixing seat, one end of two buckles 2 is separately mounted to the ten of the buckle fixing seat the other end face
In font groove, and make the positional symmetry of this two buckles；Two springs 3 are placed between described two buckles, pass through two bullets
Spring 3 holds out against this two buckles, is adjacent to cross bath inner surface of each buckle with buckle fixing seat.It is fixed in the buckle
Symmetrically there are two adjusting screws 4 for installation on the excircle of seat 5, and the central axis for respectively adjusting screw is solid in the buckle
The center line of reservation.
Described time lock 1 is hollow revolving body.The inner hole of this time lock is divided into guide section, changeover portion and returns lock cooperation section；
Wherein, the inner surface that the guide section of one end is cooperated positioned at the Hui Suoyu fuselage connector is the containing conical surface, the taper of the conical surface
It is identical as the taper of fixture block outer end face on the bayonet 2；The internal diameter of the described time lock other end is maximum, should to return lock cooperation section
The spacing returned between the internal diameter of lock cooperation section and each fixture block protrusion surface after the assembly of described two bayonets is identical.The mistake
Crossing section is isometrical section, is located at guide section and returns between lock cooperation section；Changeover portion is different from the lock cooperation internal diameter of section is returned, and forms ladder
Positioning surface on difference, the end face of the step difference and the bayonet 2 cooperates.External peripheral surface described time lock cooperation section end face has
The flange of joint test part.
The buckle fixing seat 5 is hollow revolving body.One end of the buckle fixing seat is connect with fuselage, the other end face
Geometric center through slot cruciferous, the length of the through slot vertical direction must meet after two buckles are mounted in the through slot, should
The internal diameter that the height of the outer end face of the fixture block on two buckle tops locks 1 isometrical section than described time respectively is 2.5mm big.The through slot water
Square to length should meet installation each buckle.It is described buckle fixing seat 5 circumferential surface it is symmetrical there are two adjust
The mounting hole of screw 4 is saved, and the adjusting screw mounting hole is made to be located at the both ends of the through slot vertical direction.
The closed plate 6 is circular slab, the outer diameter of the closed plate and the 5 fuselage connecting pin internal diameter phase of buckle fixing seat
Together, and make clearance fit between the two.The connecting hole for connecting fuselage tooling is evenly equipped on the surface of the closed plate.
There are two the buckles 2, is made of respectively blend stop and time lock connecting plate, and between the blend stop and time lock connecting plate
It is mutually perpendicular to, keeps the shape of buckle in T shape.The cross section of the blend stop is circle.Have in the end of this time lock connecting plate convex
The fixture block of this time lock connecting plate outer surface out；The fixture block and the step difference returned between lock connecting plate outer surface are formed by inner face
For the positioning surface of the buckle；The outer end face of the fixture block is inclined-plane.In each time lock connecting plate inner surface, there are two springs to install
Blind hole.When assembly, the blend stop is located in the inner hole of buckle fixing seat 5, returns lock connecting plate and is located in cross through slot, Hui Suolian
The fixture block of fishplate bar outer end is located at except buckle fixing seat.
In the present embodiment, buckle, buckle fixing seat and time lock material selection 30CrMnSiA, Rockwell hardness reach 28~32.
Buckle should use overall processing, to guarantee part strength.Closed plate material selection is general 45 steel, and closed plate was originally and buckle is solid
Reservation is an entirety, plays limitation buckle and is axially moved.In the actual production process, craftsmanship difference is unfavorable for fabricating,
Closed plate and buckle fixing seat are separated thus, or reserve a boss in advance in the mounting table that repacking is set, plays closing
The effect of plate and the form of closed plate can be single part, or become an entirety, closed plate and buckle with the installation space of a whole page
Contact surface roughness answers≤1.6, guarantees that buckle is accessible and moves in a circle, so by the technique of closed plate and fixing seat point
From improving the processing technology of fixing seat, reduce manufacturing cost.During assembly, first one should be buckled from buckle
Fixing seat, is put into intermediate cross recess, is then pushed up, and then installs another buckle.Two springs are installed to bayonet again
The biggish spring of elastic force, should be attached to buckle rear end by middle position, and the lesser spring of elastic force is installed to buckle front end, spring installation
After should be at compressive state, make its not under the effect of external force can independently will buckle jack up, to complete " to hold " movement tightly.?
It also should ensure that the concentricity of preceding part and rear part when installation, in order to avoid influence the practical effect of the device.
When work, part is to buffer direction high-speed motion before being driven by testpieces, and rear local collision, in this process
Middle bayonet ramp is contacted with lock bevel edge is returned, and the closed plate axial position that buckle rear end part is fixed on buffer end face limits,
Under the action of perpendicular to lock inclined edge surfaces downward force is returned and under two buckle middle springs effects, and buckle front end spring returns
Elastic force is less than rear end recoil of spring power, and buckle does circular motion clockwise and two buckle front end distance contractings by axle center of rear end
It is small, put in Hui Suozhong.Under the action of recoil of spring power, buckle moment returns to original state, and buckle is stuck in go back to lock seaming edge, i.e., complete
It is acted at " holding " of testpieces and buffer.It is zero that final testpieces slows down under the action of buffer.It is touched completing one
It hits after holding the period tightly, adjusts screw and be pressed downward front is buckled, be lower than go back to lock bevel edge bottom until buckling topmost edge,
Then under the effect of external force, buckle exits back lock.Described time lock 1 is sleeve-shaped, and one end is the connection of the energy absorbing buffer
End, the connecting pin are opening, and the external peripheral surface in the connecting pin has connecting flange；The cooperation of the other end and fuselage connector
There is through-hole at end, the center of the abutting end end face, which is made of cone section and isometrical section；The cone angle and the card of the cone section
The cone angle for detaining 2 inclined-planes is identical, and isometrical section of the internal diameter is 5mm smaller than the maximum outer dimension of described two buckles 2；The cooperation
The inner face at end forms the seam allowance of each buckle.When work, under the effect of the pressure, the beveled end of described two buckles is worn
The through-hole for returning 1 abutting end of lock is crossed, into this time lock, and is stuck on the seam allowance.
Claims (6)
1. a kind of impact test cohesion device, which is characterized in that including the fuselage connector being used cooperatively and return lock；The fuselage
Connector includes closed plate, buckle fixing seat, spring and buckle, wherein closed plate is located at the interior of described buckle fixing seat one end
One end of Kong Zhong, two buckles are separately mounted in the cross bath of the buckle fixing seat the other end face, and make this two cards
The positional symmetry of button；Two springs are placed between described two buckles, are held out against this two buckles by two springs, are made each
Cross bath inner surface of the buckle with buckle fixing seat is adjacent to；It is symmetrically equipped on the excircle of the buckle fixing seat
Two adjusting screws, and the central axis of screw is respectively adjusted in the center line of the buckle fixing seat.
2. impact test cohesion device as described in claim 1, which is characterized in that the inner hole of described time lock is divided into guiding
Section, changeover portion and time lock cooperation section；Wherein, the inner surface of the guide section of one end is cooperated to be interior positioned at the Hui Suoyu fuselage connector
The conical surface held back, the taper of the conical surface are identical as the taper of fixture block outer end face on the buckle；The internal diameter of the described time lock other end
Maximum, to return lock cooperation section, the internal diameter of this time lock cooperation section and each fixture block protrusion surface after described two snap-fitteds
Between spacing it is identical；The changeover portion is isometrical section, is located at guide section and returns between lock cooperation section；Changeover portion cooperates with lock is returned
The internal diameter of section is different, forms step difference, and the positioning surface on the end face of the step difference and the buckle cooperates；Cooperate in described time lock
The external peripheral surface of section end face has the flange of joint test part.
3. impact test cohesion device as described in claim 1, which is characterized in that one end of the buckle fixing seat and fuselage connect
It connects, the geometric center of the other end face through slot cruciferous, the length of the through slot vertical direction must meet two buckle installations
After in the through slot, the internal diameter that the height of the outer end face of the fixture block on this two buckle tops locks isometrical section than described time respectively is big
2.5mm；The length of the through slot horizontal direction should meet installation each buckle；In the circumferential surface pair of the buckle fixing seat
Claiming distribution, there are two the mounting holes for adjusting screw, and the adjusting screw mounting hole is made to be located at the two of the through slot vertical direction
End.
4. impact test cohesion device as described in claim 1, which is characterized in that the outer diameter of the closed plate and the buckle are solid
Reservation fuselage connecting pin internal diameter is identical, and makes clearance fit between the two；It is evenly equipped on the surface of the closed plate for connecting machine
The connecting hole of body tooling.
5. impact test cohesion device as described in claim 1, which is characterized in that there are two the buckles, respectively by blend stop and
Lock connecting plate composition is returned, and is mutually perpendicular between the blend stop and time lock connecting plate, keeps the shape of buckle in T shape；In this time
There is the fixture block for protruding this go back to lock connecting plate outer surface in the end of lock connecting plate；Rank between the fixture block and time lock connecting plate outer surface
Terraced difference is formed by the positioning surface that inner face is the buckle；The outer end face of the fixture block is inclined-plane；The table in each time lock connecting plate
There are two spring installing blinds in face.
6. impact test cohesion device as claimed in claim 5, which is characterized in that when assembly, the blend stop, which is located at buckle, to be fixed
It in the inner hole of seat, returns lock connecting plate and is located in cross through slot, the fixture block for going back to lock connecting plate outer end is located at except buckle fixing seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821119900.8U CN208621282U (en) | 2018-07-16 | 2018-07-16 | A kind of impact test cohesion device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821119900.8U CN208621282U (en) | 2018-07-16 | 2018-07-16 | A kind of impact test cohesion device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208621282U true CN208621282U (en) | 2019-03-19 |
Family
ID=65705709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821119900.8U Active CN208621282U (en) | 2018-07-16 | 2018-07-16 | A kind of impact test cohesion device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208621282U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108692906A (en) * | 2018-07-16 | 2018-10-23 | 西安航空制动科技有限公司 | A kind of inertial load experiment collision cohesion device |
| CN112179603A (en) * | 2020-09-15 | 2021-01-05 | 南京怀青小牛体育科技有限公司 | Energy-saving horizontal bar and parallel bar support bar impact test device |
| CN116202900A (en) * | 2023-03-27 | 2023-06-02 | 常州涛惠文化传媒有限公司 | Detection instrument and detection method for detecting hardness of valve based on rebound parameters after impact |
-
2018
- 2018-07-16 CN CN201821119900.8U patent/CN208621282U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108692906A (en) * | 2018-07-16 | 2018-10-23 | 西安航空制动科技有限公司 | A kind of inertial load experiment collision cohesion device |
| CN108692906B (en) * | 2018-07-16 | 2024-02-09 | 西安航空制动科技有限公司 | Collision enclasping device for inertial load test |
| CN112179603A (en) * | 2020-09-15 | 2021-01-05 | 南京怀青小牛体育科技有限公司 | Energy-saving horizontal bar and parallel bar support bar impact test device |
| CN116202900A (en) * | 2023-03-27 | 2023-06-02 | 常州涛惠文化传媒有限公司 | Detection instrument and detection method for detecting hardness of valve based on rebound parameters after impact |
| CN116202900B (en) * | 2023-03-27 | 2024-03-12 | 苏州旭博检测服务有限公司 | Detection instrument and detection method for detecting hardness of valve based on rebound parameters after impact |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN208621282U (en) | A kind of impact test cohesion device | |
| US20140097732A1 (en) | Sliding rail assembly | |
| WO2017121094A1 (en) | Derailing prevention device for sliding rail and furniture sliding rail using same | |
| WO2009011389A1 (en) | Seat for vehicle | |
| CN211396162U (en) | Mounting structure of ultra-thin stone honeycomb panel curtain | |
| CN204250371U (en) | A kind of variable load energy absorption device of helicopter crash proof seat | |
| CN108692906A (en) | A kind of inertial load experiment collision cohesion device | |
| EP2748046A1 (en) | Arrangement and method for installing furniture item in vehicle | |
| CN203924925U (en) | A kind of electronic lock sliding lid construction | |
| CN111845493A (en) | Manual adjustment buffer isolation device of military vehicle lightning protection seat and use method | |
| CN205917589U (en) | Speed locking cantilever stick subtracts isolation bearing | |
| CN103754136B (en) | A kind of sliding rail of automobile seat of bilateral locking | |
| CN109365719B (en) | Guiding positioning top handle for riveting | |
| CN215824582U (en) | A cutting head buffer stop for laser cutting machine | |
| CN115890027A (en) | A cutting head buffer stop for laser cutting machine | |
| CN112790567A (en) | Unlocking shock insulation lock of shock insulation platform | |
| CN206393350U (en) | A kind of assembly tooling of aircraft rib | |
| CN114310243A (en) | Traction pull rod press-fitting device | |
| CN101908401B (en) | Damping device for double-push magnetic apparatus | |
| CN112177193A (en) | Self-resetting viscous damping wall | |
| CN216519956U (en) | Large-specification pipe jacking machine rack buffering and locking device | |
| CN213950268U (en) | Special guide rail device for car type elevator hall door | |
| CN206936149U (en) | A kind of automobile high strength steel plate stringer forming mould | |
| CN105059151A (en) | Impact buffer device for automobile seat | |
| CN109622717A (en) | A kind of horizontal drawing and extending hydraulic machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |