CN105889280A - Non-disengagement fastening device and method - Google Patents
Non-disengagement fastening device and method Download PDFInfo
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- CN105889280A CN105889280A CN201510035881.5A CN201510035881A CN105889280A CN 105889280 A CN105889280 A CN 105889280A CN 201510035881 A CN201510035881 A CN 201510035881A CN 105889280 A CN105889280 A CN 105889280A
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- trip bolt
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Abstract
The invention provides a non-disengagement fastening device and method which are used for integrating an anti-loose function with an anti-disengagement function to execute fastening assembling of equipment on a spacecraft structural airframe. The non-disengagement fastening device comprises a fastening screw, an anti-loose spring and a limiting gasket, wherein the upper end of the head of the fastening screw is provided with an everted flange, and the fastening screw is used for fastening the equipment on the structural airframe, so that a basic connecting function is achieved; the anti-loose spring is a compression spring and continuously supplies the spring force which is transmitted to a thread connection pair through the fastening screw, and the anti-loose function is achieved; and the limiting gasket is in screw connection to an equipment lug piece, and the anti-disengagement function is achieved. Therefore, the anti-loose advantage and the anti-disengagement advantage are combined by the non-disengagement fastening device and method, no extra anti-loose measure is needed, extra objects are not produced, and the fastening device does not need to be controlled by additional objects; the weight cost is small, operation for an astronaut is convenient, and an operating instruction function is achieved; and the requirement for disassembling maintenance equipment of the astronaut under the microgravity state is met, the universality characteristic is achieved, and thus the equipment fastening assembly technology under the microgravity state is further improved.
Description
Technical field
The invention belongs to space station maintainable technology on-orbit technical field, relate to improvement with Anti-extrusion principle locking to tradition, be specifically related to
One does not deviate from clamp device and method, performs the equipment structure body at spacecraft for integrated locking and anti-fall function
Fastening assembling.
Background technology
Equipment is securedly mounted to all kinds of spacecraft various ways and means, along with space station proposes due to long-lived requirement
Maintenance of equipment demand improves constantly, and spacecraft equipment fastening is installed and first should be needed to overcome transmitter section load, i.e. needs possess anti-loosening property.
After entering the orbit, under microgravity environment, it is contemplated that spacefarer's extravehicular activity in cabin is not convenient, spacefarer detaching equipment demanding party just and
Screw under Chai Xie does not allow own floating.
Currently, the equipment fastening means that spacecraft is applied to is mainly regular screw threads and connects, and regular screw threads connect with screw and steel wire
Swivel nut, screw are main with the connection of the forms such as nut, and this structure is only capable of realizing general connection, locking need to apply other measure,
The commonly used locking measure of spacecraft is for using spring washer or gluing, and special thread structure such as Spiralock nuts, self-locking type spiral shell
Follow closely and cannot be widely applied in spacecraft equipment fastening installation application owing to technique limits.Meanwhile, regular screw threads are connected to release spiral shell
After stricture of vagina connects, screw i.e. departs from body, is own floating state under microgravity state, can produce space trash even to boat
The life of it member causes danger.
Although using the fastening of special Quick Release quick-release mechanism to install be capable of locking and anti-fall function, but due to mechanism's design complexity,
Weight cost is big, and this kind of design is only applicable to special main equipment fastening and installs use.
In order to realize spacecraft equipment fastening, locking Anti-extrusion is installed, reduces weight cost, increase the versatility of device, be badly in need of one
Plant and combine locking and Anti-extrusion technology Novel threaded fastening schemes.
Summary of the invention
In order to solve problems of the prior art, the present invention proposes one and takes into account locking and Anti-extrusion, and volume is little, weight
Gently, compact conformation is simple, easy to operate fastening schemes.
One aspect of the present invention provides one and does not deviate from clamp device, performs equipment for integrated locking and anti-fall function
Fastening assembling on the structure body of spacecraft.The clamp device of not deviating from of the present invention includes: trip bolt, its ailhead upper end
It is provided with the flange that turns up, and for equipment being fastened on structure body, thus play the effect of basis connection；Locking spring,
For compression spring, and its spring force persistently provided is passed on threaded connection pair by trip bolt, thus rises locking
Effect；And spacing shim, it is screwed onto on the auricle of equipment, plays the effect of Anti-extrusion.
Specifically, locking spring is between trip bolt and spacing shim, and spacing shim contacts with the bottom of trip bolt, with
And trip bolt is spirally connected with structure body via locking spring and spacing shim successively.
In trip bolt, the flange that turns up transmits at the axial direction of trip bolt for the locking pretightning force produced by locking spring
To spacing shim, thus pass to structure body.Spacing shim is deviate from for limiting screw with the effect realizing screw Anti-extrusion.
In locking spring, the spring force of locking spring is passed on threaded connection pair via the flange that turns up and is threaded connection
Sub-quilt be converted to pretightning force and and then be converted to locking moment, thus play locking effect.
Alternatively, in described spacing shim, spacing screw thread can be used to ensure that trip bolt the most individually comes off.Correspondingly, anti-
The locking effect of threaded pre-tightening under vibration environment of pine spring.
Another aspect of the present invention additionally provides one and does not deviate from fastening method, comprises the following steps: step one, is sent not by meal
Abjection clamp device is arranged on the auricle of equipment, thus passes through Torque Control so that it is be fixedly secured on the auricle of equipment；
Step 2, trip bolt is threadeded with the screwed hole on structure body, with during pretension, makes locking spring constantly compress
And compression stress constantly increases；And step 3, when the compression stress of locking spring reaches maximum, its pretightning force provided rises locking
Effect, it is achieved thereby that the effect of thread connection anti-loose, wherein, the operation of pretension is: when the ailhead of trip bolt is with spacing
Pad contact and when reaching predetermined screw-down torque, trip bolt completes pretension.
Extraly, also include according to the fastening method of not deviating from of the present invention: when dismantling trip bolt, trip bolt completely with
Under structure body non-threaded connection status, trip bolt is limited in spacing shim and cannot exit；Trip bolt is lifted, from
And spacefarer obtains, by the distance of raising observing trip bolt, the information whether trip bolt is removed.
Visible, the clamp device of the present invention mainly includes trip bolt, locking spring, spacing shim.Wherein, trip bolt leads to
Crossing the locking pretightning force that locking spring produces by the flange that turns up to be delivered in structure by spacing shim, now spacing shim plays pad
Sheet effect, the elastic force in conjunction with screw pretightning force Yu locking spring realizes locking effect.Spacing shim is threadedly secured on equipment,
Threadeding under state with structure disengaging at trip bolt, spacing shim plays position-limiting action, makes screw cannot depart from spacing shim
And finally keep being connected with equipment, trip bolt cannot individually come off.Due to this device, space equipment can ensure that installation
Reliability is conducive to again spacefarer's maintainable technology on-orbit so that this kind of technology can fully be applied to space maintenance field.
Therefore, with common threaded compared with, the present invention based on spring locking do not deviate from fastening schemes take into account locking with
Two advantages of Anti-extrusion, under the screw thread pair of identical screw-down torque connects, it is not necessary to unnecessary locking measure, do not produce fifth wheel,
Without fifth wheel control, weight cost is little, and spacefarer is easy to operate, spacefarer's screw can be pointed out the most to disassemble, have
Operation instruction effect.
It addition, compared with threaded with existing and locking measure, due to the fact that and have employed new locking principle, it is integrated with anti-
Pine and anti-fall function, solve the demand of spacefarer's detachable maintaining equipment under microgravity state, have versatility feature, thus
Further increase the equipment fastening mounting technology under microgravity state.
Accompanying drawing explanation
Fig. 1 is the structural representation not deviating from clamp device of the specific embodiment of the invention；
Fig. 2 is the schematic diagram of the non-installment state not deviating from clamp device of the specific embodiment of the invention；And
Fig. 3 is that the equipment of the specific embodiment of the invention can not pass through the state signal that clamp device is arranged on structure body
Figure.
Detailed description of the invention
It will be appreciated that the clamp device of not deviating from of the present invention is made up of trip bolt, locking spring and spacing shim three part.Wherein,
Trip bolt secures the equipment on structure body by threadeding with structure body, plays basis interconnection function.Locking spring is
Compression spring, plays locking effect.Spacing shim is fixed with equipment auricle by screw thread pair, plays spiral shell in equipment fastening is installed
Nail pad effect, and limit screw depart from equipment come off.
In the present invention, trip bolt in ailhead upper end design turn up flange, in screw axial direction, spring force is delivered to
The spacing shim of contact bottom head of screw, and then be delivered on structure body.
The spring force of locking spring is converted to locking moment, reaches locking effect.
Spacing shim inner chamber arranges stopping means, plays screw Anti-extrusion effect.
The present invention is described in detail for 1-3 and detailed description of the invention below in conjunction with the accompanying drawings.
As it is shown in figure 1, do not deviate from clamp device 4 to specifically include that trip bolt 1, locking spring 2 and spacing shim 3.
Do not deviate from clamp device 4 to be fastened on structure body by equipment by trip bolt 1, locking spring 2 and spacing shim 3
Between screw 1 and equipment auricle, locking spring 2 is by providing lasting spring force by the method for turning up of the ailhead of trip bolt 1
Orchid is delivered on screw thread pair.Spacing shim 3 is screwed onto on equipment auricle, prevents screw 1 from swimming under microgravity environment.
As in figure 2 it is shown, the trip bolt 1 not deviating from clamp device is under Pre strained state, when there is loosening trend, locking
Spring 2 provides lasting elastic force and then is converted to lasting locking moment, owing to device only exists loosening trend, and the compression of spring
Amount keeps constant, so the locking moment that locking spring 2 provides keeps constant, lasting locking moment to ensure that screw 1 is difficult to pine
De-.
As it is shown on figure 3, describe the detailed mistake being securedly mounted to structure body 6 of the equipment 5 using not deviate from clamp device 4
Journey, specifically comprises the following steps that
The first step, is arranged on not deviating from clamp device 4 on the auricle of equipment 5, by Torque Control, does not deviate from clamp device
On 4 auricles being fastened on equipment 5 reliably；
Second step, the trip bolt 1 of device 4 is threadeded with the screwed hole on structure body, during pretension, locking spring
2 are compressed continuously, and the compression stress of spring 2 constantly increases, and produced pretightning force constantly increases, wherein, when trip bolt is followed closely
After 1 contacts with spacing shim 3, and reaching anticipated screw-down torque, screw 1 completes pretension.The compression stress of locking spring 2
Reaching maximum, its pretightning force provided can reach locking effect, it is achieved thereby that the effect of thread connection anti-loose；And
3rd step, when knockout screw 1, when screw 1 is completely and under structure body non-threaded connection status, being limited of screw 1
System is at spacing shim 3 intracavity, and screw 1 cannot exit from spacing shim intracavity, simultaneously as the effect of locking spring 2 elastic force,
Screw 1 can be lifted certain altitude, and spacefarer raises distance by observation screw 1 can obtain whether screw 1 is removed
Information.
Described on end, use technical scheme, take into account locking and two advantages of Anti-extrusion, at identical screw-down torque
Screw thread pair connect under, it is not necessary to unnecessary locking measure, do not produce fifth wheel, it is not necessary to fifth wheel control, weight cost is little, space flight
Member is easy to operate, spacefarer's screw can be pointed out the most to disassemble, have operation instruction effect, and new owing to have employed
Locking principle, is integrated with locking and anti-fall function, solves the demand of spacefarer's detachable maintaining equipment under microgravity state, tool
There is versatility feature, thus the equipment under further increasing microgravity state fastens mounting technology.
Undeclared in the present invention partly belong to techniques known.
Claims (9)
1. do not deviate from a clamp device, perform the equipment structure body at spacecraft for integrated locking and anti-fall function
On fastening assembling, it is characterised in that including:
Trip bolt, its ailhead upper end is provided with the flange that turns up, and for described equipment being fastened on described structure body,
Thus play the effect of basis connection；
Locking spring, for compression spring, and its spring force persistently provided is passed to screw thread even by described trip bolt
Connect in pair, thus play locking effect；And
Spacing shim, is screwed onto on the auricle of described equipment, plays the effect of Anti-extrusion.
The most according to claim 1 do not deviate from clamp device, it is characterised in that
Described locking spring between described trip bolt and described spacing shim,
Described spacing shim contacts with the bottom of described trip bolt, and
Described trip bolt is spirally connected with described structure body via described locking spring and described spacing shim successively.
The most according to claim 2 do not deviate from clamp device, it is characterised in that in described trip bolt,
The described flange that turns up passes at the axial direction of described trip bolt for the locking pretightning force produced by described locking spring
It is delivered to described spacing shim, thus passes to described structure body.
The most according to claim 3 do not deviate from clamp device, it is characterised in that described spacing shim is used for: limit institute
State trip bolt abjection, to realize the effect of the Anti-extrusion of described trip bolt.
The most according to claim 2 do not deviate from clamp device, it is characterised in that in described locking spring,
The spring force of described locking spring is passed on described threaded connection pair via the described flange that turns up and by described spiral shell
Stricture of vagina auxiliary connection be converted into pretightning force and and then be converted to locking moment, thus play described locking effect.
The most according to claim 2 do not deviate from clamp device, it is characterised in that in described spacing shim, described limit
Position screw thread is used for, it is ensured that described trip bolt the most individually comes off.
The most according to claim 6 do not deviate from clamp device, it is characterised in that described locking spring is used for:
The locking effect of described trip bolt threaded pre-tightening under vibration environment.
8. do not deviate from a fastening method, for using the clamp device of not deviating from described in any of the above-described claim to perform
Equipment fastening assembling on the structure body of spacecraft, it is characterised in that comprise the following steps:
Step one, send to deviate from clamp device to be arranged on the auricle of described equipment described meal, thus by Torque Control,
It is made to be fixedly secured on the auricle of described equipment；
Step 2, trip bolt is threadeded with the screwed hole on structure body, with during pretension, makes locking spring not
Disconnected compression and compression stress constantly increase；And
Step 3, when the compression stress of described locking spring reaches maximum, its pretightning force provided plays locking effect, thus
Achieve the effect of thread connection anti-loose,
Wherein, the operation of described pretension is: when the ailhead of described trip bolt contacts with spacing shim and reaches predetermined tightening
During moment, described trip bolt completes pretension.
The most according to claim 8 do not deviate from fastening method, it is characterised in that also include:
When dismantling described trip bolt, described trip bolt completely with under described structure body non-threaded connection status, institute
State trip bolt to be limited in described spacing shim and cannot exit；And
Described trip bolt is lifted, thus spacefarer obtains described fastening spiral shell by the distance of raising observing described trip bolt
The information whether nail is removed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510035881.5A CN105889280A (en) | 2015-01-23 | 2015-01-23 | Non-disengagement fastening device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510035881.5A CN105889280A (en) | 2015-01-23 | 2015-01-23 | Non-disengagement fastening device and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105889280A true CN105889280A (en) | 2016-08-24 |
Family
ID=56999573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510035881.5A Pending CN105889280A (en) | 2015-01-23 | 2015-01-23 | Non-disengagement fastening device and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105889280A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106309134A (en) * | 2016-08-31 | 2017-01-11 | 上海涵欧制药设备有限公司 | Adjustable fluidized bed coating cylinder structure |
| CN106523505A (en) * | 2016-12-30 | 2017-03-22 | 东方蓝天钛金科技有限公司 | Automatic limiting and looseness-resisting fastening assembly |
| CN112855735A (en) * | 2021-01-26 | 2021-05-28 | 四川航天***工程研究所 | Anti-floating screw for space station |
| CN114180106A (en) * | 2021-11-16 | 2022-03-15 | 北京卫星制造厂有限公司 | Ventilation device |
Citations (7)
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|---|---|---|---|---|
| US3343581A (en) * | 1966-07-01 | 1967-09-26 | Northrop Corp | Captive screw fastener |
| US4915557A (en) * | 1988-09-13 | 1990-04-10 | Rexnord Holdings Inc. | Captive screw assembly |
| JPH10115013A (en) * | 1996-10-08 | 1998-05-06 | Akagi:Kk | Insert for constructing scalfold |
| US6682282B2 (en) * | 2001-09-28 | 2004-01-27 | Hewlett-Packard Development Company, L.P. | Rack mount panel fastener with interchangeable thread size |
| JP2005282020A (en) * | 2004-03-29 | 2005-10-13 | Rebuilt Enterprise:Kk | Screwing auxiliary tool for building structure material |
| CN203322016U (en) * | 2013-05-16 | 2013-12-04 | 贵州航天林泉电机有限公司 | Anti-looseness self-locking screw connecting structure |
| CN103697041A (en) * | 2013-12-27 | 2014-04-02 | 中国第一汽车股份有限公司 | Fastening bolt assembly with spring |
-
2015
- 2015-01-23 CN CN201510035881.5A patent/CN105889280A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3343581A (en) * | 1966-07-01 | 1967-09-26 | Northrop Corp | Captive screw fastener |
| US4915557A (en) * | 1988-09-13 | 1990-04-10 | Rexnord Holdings Inc. | Captive screw assembly |
| JPH10115013A (en) * | 1996-10-08 | 1998-05-06 | Akagi:Kk | Insert for constructing scalfold |
| US6682282B2 (en) * | 2001-09-28 | 2004-01-27 | Hewlett-Packard Development Company, L.P. | Rack mount panel fastener with interchangeable thread size |
| JP2005282020A (en) * | 2004-03-29 | 2005-10-13 | Rebuilt Enterprise:Kk | Screwing auxiliary tool for building structure material |
| CN203322016U (en) * | 2013-05-16 | 2013-12-04 | 贵州航天林泉电机有限公司 | Anti-looseness self-locking screw connecting structure |
| CN103697041A (en) * | 2013-12-27 | 2014-04-02 | 中国第一汽车股份有限公司 | Fastening bolt assembly with spring |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106309134A (en) * | 2016-08-31 | 2017-01-11 | 上海涵欧制药设备有限公司 | Adjustable fluidized bed coating cylinder structure |
| CN106523505A (en) * | 2016-12-30 | 2017-03-22 | 东方蓝天钛金科技有限公司 | Automatic limiting and looseness-resisting fastening assembly |
| CN112855735A (en) * | 2021-01-26 | 2021-05-28 | 四川航天***工程研究所 | Anti-floating screw for space station |
| CN112855735B (en) * | 2021-01-26 | 2022-11-18 | 四川航天***工程研究所 | Anti-floating screw for space station |
| CN114180106A (en) * | 2021-11-16 | 2022-03-15 | 北京卫星制造厂有限公司 | Ventilation device |
| CN114180106B (en) * | 2021-11-16 | 2023-08-11 | 北京卫星制造厂有限公司 | Ventilating device |
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Application publication date: 20160824 |