CN202964525U - Missile bay section connection auxiliary tool - Google Patents
Missile bay section connection auxiliary tool Download PDFInfo
- Publication number
- CN202964525U CN202964525U CN 201220635080 CN201220635080U CN202964525U CN 202964525 U CN202964525 U CN 202964525U CN 201220635080 CN201220635080 CN 201220635080 CN 201220635080 U CN201220635080 U CN 201220635080U CN 202964525 U CN202964525 U CN 202964525U
- Authority
- CN
- China
- Prior art keywords
- clip
- spacer pin
- missile cabin
- hole
- missile
- 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.)
- Expired - Lifetime
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- Connection Of Plates (AREA)
Abstract
The utility model discloses a missile bay section connection auxiliary tool. The missile bay section connection auxiliary tool comprises a clamp hoop which is clamped and fixed on the peripheral surface of a missile bay section in the use process, wherein two ends of the clamp hoop are two connection ends, a locking mechanism used for forcing the two ends of the clamp hoop to get close to fix the clamp hoop on the missile bay section is arranged between the two connection ends of the clamp hoop, the clamp hoop is fixedly provided with a limiting protruding block used for being correspondingly inserted in a limiting groove in the peripheral surface of the missile bay section in a positioning and matched mode to circumferentially position the clamp hoop, a screwing push rod corresponding to a limiting pin at the connection position of the missile bay section is screwed on the clamp hoop in a threaded mode, and when screwed in, the screwing push rod applies acting force for pressing the limiting pin into a limiting pin installation groove to an ejection-in end of the limiting pin, or applies acting force for ejecting the limiting pin out of the limiting pin installation groove to an ejection-out end of the limiting pin. The clamp hoop is fixed on the missile bay section, so that the screw push rod applies ejection force to the ejection-in end or the ejection-out end of the limiting pin conveniently, and the problem of inaccurate installation or deformation of the limiting pin is avoided when the limiting pin is installed in a knocked mode or detached.
Description
Technical field
The utility model relates to a kind of missile cabin and connects auxiliary mould.
Background technology
Existing missile cabin outer peripheral face is provided with the spacer pin mounting groove, spacer pin need to be packed in the spacer pin mounting groove when missile cabin connects or the spacer pin that is provided with in the spacer pin mounting groove is pulled down, traditional installation and dismounting mode are pounded heading into end or ejecting end of spacer pin for machinery strikes, the installation and removal mode of this mechanical impact formula firmly differs, easily cause spacer pin install not in place or during dismounting spacer pin or limit mounting groove distortion appears, affect the normal use of spacer pin and the connection of missile cabin.
The utility model content
The purpose of this utility model is to provide a kind of missile cabin to connect auxiliary mould, strikes and easily causes when pounding the installation or removal spacer pin spacer pin that not in place or limit mounting groove is installed the technical problem of being out of shape easily to occur to solve machinery in prior art.
for achieving the above object, the technical approach that missile cabin provided by the utility model connects auxiliary mould is: missile cabin connects auxiliary mould, comprise and clamp the clip that is fixed on the missile cabin outer peripheral face when using, the clip two ends are two links, be furnished with between two links of clip be used to forcing clip two ends mutually to draw close clip to be fixed on the retaining mechanism on missile cabin, be installed with on clip for location inserting corresponding to stopper slot on the missile cabin outer peripheral face clip is carried out the circumferentially spacing block set of location, the end that heads into to spacer pin when screw thread is installed with the precession of corresponding missile cabin junction spacer pin on clip applies and spacer pin is pressed into the active force of spacer pin mounting groove or to end applies the active force that spacer pin is ejected from the spacer pin mounting groove the spiral handspike that ejects of spacer pin.
Described clip is provided with for the guiding installing hole corresponding with the stopper slot on the missile cabin outer peripheral face, described spacing block set is inserted in the guiding installing hole, spacing block set by being located in the guiding installing hole hole wall and the steady pin on spacing block set is removable is installed on clip.
On described clip with the missile cabin outer peripheral face on spacer pin mounting groove corresponding position be provided with the installation through hole, offer tapped through hole on the hole wall of this installation through hole, the corresponding spinning of described spiral handspike is in described tapped through hole.
Described tapped through hole has been arranged symmetrically with two about the center line that through hole is installed on circumferential along clip.
Being used for of described spiral handspike and heading into end or ejecting the corresponding removable jacking block that is fixed with in end of end of spacer pin.
Described clip comprises by the hinged upper and lower connecting plate of bearing pin, the end away from described bearing pin of the two corresponding upper and lower connecting plates of links difference of described clip.
Described two links are respectively the first link and the second link, retaining mechanism comprises the connecting axle that is hinged on the first link, the end away from the first link of connecting axle is provided with external thread section, be provided with on the second link for the through hole of connecting axle inserting, retaining mechanism also comprises the locking nut of spinning on the external thread section of connecting axle.
the beneficial effects of the utility model are: when using auxiliary mould mounting limit pin provided by the utility model, hoop sleeve is contained on the outer peripheral face of missile cabin, and make the spacing block set on clip insert in stopper slot corresponding on the missile cabin outer peripheral face with the positioning lathe dog that makes progress in guided missile week, by retaining mechanism, clip is fixed on missile cabin, at this moment, the spacer pin of the corresponding missile cabin of the spiral handspike that is installed with on clip junction head into end, the precession spiral handspike is with in the spacer pin mounting groove that the slow jacking of spacer pin is corresponding, until complete the installation of spacer pin.But when using auxiliary mould provided by the utility model dismounting spacer pin, equally hoop sleeve is contained on the outer peripheral face of missile cabin, and make the spacing block set on clip insert in stopper slot corresponding on the missile cabin outer peripheral face with the positioning lathe dog that makes progress in guided missile week, by retaining mechanism, clip is fixed on missile cabin, at this moment, the spacer pin of the corresponding missile cabin of the spiral handspike that is installed with on clip junction eject end, the precession spiral handspike is to eject spacer pin slowly in corresponding spacer pin mounting groove, until complete the dismounting of spacer pin.During auxiliary mould work provided by the utility model, clip is fixed on missile cabin, be convenient to spiral handspike heading into end or ejecting end and apply pressure on top surface to spacer pin, avoid striking the problem that when pounding the installation or removal spacer pin, the spacer pin installation is not in place or appearance is out of shape, guarantee normal mounting and the dismounting of spacer pin, realize Fast Installation or the dismounting of spacer pin.
Description of drawings
Fig. 1 is the structural representation that missile cabin provided by the utility model connects auxiliary mould embodiment 1;
Fig. 2 is the left side view of Fig. 1;
Fig. 3 is the structural representation that missile cabin provided by the utility model connects auxiliary mould embodiment 2;
Fig. 4 is the left side view of Fig. 3.
The specific embodiment
Embodiment 1:
as Fig. 1, shown in Figure 2, a kind of missile cabin connects the embodiment of auxiliary mould, auxiliary mould in this embodiment clamps the clip 100 that is fixed on the missile cabin outer peripheral face when comprising use, this clip 100 by by bearing pin hinged tighten sheet 3 and lower connecting plate 1 consists of, the two ends of clip 100 are two links, on two links difference correspondences of clip, an end away from described bearing pin of lower connecting plate, two links of clip 100 are respectively the first link 11 and the second link 12, first, being furnished with between the second link for applying to two links forces two links mutually to draw close clip to be fixed on the retaining mechanism on missile cabin, this retaining mechanism comprises the connecting axle 13 that is hinged on the first link 11, the end away from the first link of connecting axle 13 is provided with external thread section, be provided with on the second link 12 for the through hole of connecting axle inserting, retaining mechanism also comprises the locking nut 6 of spinning on the external thread section of connecting axle.Herein, be provided with the guiding installing hole in the stopper slot corresponding position with on the missile cabin outer peripheral face on lower connecting plate 1, be fitted with in installing hole for the spacing block set 2 of the corresponding location inserting of stopper slot clip is carried out circumferentially locate that is provided with the missile cabin outer peripheral face in guiding, spacing block set 2 by being located in the guiding installing hole hole wall and the steady pin on spacing block set 7 is removable is installed on lower connecting plate 1, offer the breach of being convenient to plug-in mounting spacing block set on the clip on the hole wall of the guiding installing hole on lower connecting plate 1 herein.In the present embodiment, two described guiding installing holes have been arranged symmetrically with around lower connecting plate bearing of trend on lower connecting plate 1, during use, can be inserted in the guiding installing hole to realize the circumferential location of clip 100 on the missile cabin junction with spacing block set 2 and spacing block set 8 are corresponding respectively.Tighten on sheet 2 with the missile cabin outer peripheral face on spacer pin mounting groove corresponding position be provided with through hole 9 be installed, offer tapped through hole 10 on the hole wall of installation through hole 9, the end that heads into to spacer pin when in this tapped through hole 10, corresponding screw thread is installed with corresponding missile cabin junction spacer pin and precession applies the active force spiral handspike 4 that spacer pin is pressed into the spacer pin mounting groove, spiral handspike 4 be used for spacer pin head into the corresponding removable jacking block 5. that is fixed with in end of end
In the present embodiment, described tapped through hole 10 is being arranged symmetrically with two about the center line that through hole 9 is installed along tightening sheet 3 on circumferentially.Two spiral handspikes can be installed at the same time, can install two spacer pins of missile cabin junction like this, improve the installation effectiveness of spacer pin.
when the auxiliary mould mounting limit pin that provides in the present embodiment is provided, to tighten sheet 3 and lower connecting plate 1 correspondence is sleeved on the missile cabin outer peripheral face, guiding installing hole on lower connecting plate 1 is corresponding with the stopper slot of missile cabin junction, spacing block set 2 be inserted in the installing hole of lower connecting plate and make the corresponding location inserting of stopper slot corresponding on spacing block set and missile cabin outer peripheral face to realize the circumferential location to clip 100, and with steady pin 7, spacing block set 2 is fixed on lower connecting plate 1, clip 100 is fixed on the outer peripheral face of missile cabin by retaining mechanism again, then, rotate spinning at the spiral handspike 4 that tightens on sheet 3, usually adopt torque wrench to rotate spiral handspike, driving jacking block 5 by spiral handspike 4 contacts and spacer pin is pressed in the spacer pin mounting groove slowly with the end that heads into of spacer pin, namely complete installation until reach default moment of torsion.
In above-described embodiment, tapped through hole has been arranged symmetrically with two about the center line that through hole is installed on circumferential along clip, in other embodiments, also a tapped through hole can only be set.
In above-described embodiment, be provided with two guiding installing holes on lower connecting plate, like this, can choose one of them guiding installing hole mounting limit projection wantonly, also can be in two guiding installing holes equal mounting limit projections.
In the above-described embodiments, in the guiding installing hole that is provided with on connecting plate under removable being inserted into of spacing block set, in other embodiments, spacing block set is also directly under being installed in of one or split on connecting plate.
In above-described embodiment, the structure that retaining mechanism adopts connecting axle and locking nut to match, in other embodiments, the structure that retaining mechanism also can match for clamping screw and locking nut, at this moment, need to bolt mounting holes be set respectively at two links of clip, the bolt that clamping screw is installed on two links is installed in the air, then screws locking nut and gets final product.
In above-described embodiment, the connecting plate of clip is connected by the bearing pin split by upper and lower connecting plate and consists of, and is convenient to so upper and lower connecting plate is being processed respectively, also is convenient to install on missile cabin.In other embodiments, the connecting plate of clip also can adopt overall structure.
Embodiment 2:
As shown in Figure 3, Figure 4, its difference with embodiment 1 mainly is: the end that ejects to spacer pin when screw thread is installed with corresponding missile cabin junction spacer pin and precession on this clip 100 applies the spiral handspike 24 of the active force that spacer pin is ejected from the spacer pin mounting groove, this spiral handspike 24 be used for spacer pin eject the corresponding removable jacking block 25 that is fixed with in end of end.
when the auxiliary mould dismounting spacer pin that provides in the present embodiment is provided, to tighten sheet 3 and lower connecting plate 1 correspondence is sleeved on the missile cabin outer peripheral face, guiding installing hole on lower connecting plate 1 is corresponding with the stopper slot of missile cabin junction, spacing block set 2 be inserted in the installing hole of lower connecting plate and make the corresponding location inserting of stopper slot corresponding on spacing block set and missile cabin outer peripheral face to realize the circumferential location to clip 100, and with steady pin 7, spacing block set 2 is fixed on lower connecting plate 1, clip 100 is fixed on the outer peripheral face of missile cabin by retaining mechanism again, then, rotate spinning at the spiral handspike 24 that tightens on sheet 3, usually adopt torque wrench to rotate spiral handspike, driving jacking block 25 by spiral handspike 24 contacts and slowly spacer pin is extruded from the spacer pin mounting groove with the end that ejects of spacer pin, namely complete dismounting until reach default moment of torsion.
Claims (7)
1. missile cabin connects auxiliary mould, it is characterized in that: comprise clamping the clip that is fixed on the missile cabin outer peripheral face when using, the clip two ends are two links, be furnished with between two links of clip be used to forcing clip two ends mutually to draw close clip to be fixed on the retaining mechanism on missile cabin, be installed with on clip for location inserting corresponding to stopper slot on the missile cabin outer peripheral face clip is carried out the circumferentially spacing block set of location, the end that heads into to spacer pin when screw thread is installed with the precession of corresponding missile cabin junction spacer pin on clip applies and spacer pin is pressed into the active force of spacer pin mounting groove or to end applies the active force that spacer pin is ejected from the spacer pin mounting groove the spiral handspike that ejects of spacer pin.
2. missile cabin according to claim 1 connects auxiliary mould, it is characterized in that: described clip is provided with for the guiding installing hole corresponding with the stopper slot on the missile cabin outer peripheral face, described spacing block set is inserted in the guiding installing hole, spacing block set by being located in the guiding installing hole hole wall and the steady pin on spacing block set is removable is installed on clip.
3. missile cabin according to claim 1 and 2 connects auxiliary mould, it is characterized in that: on described clip with the missile cabin outer peripheral face on spacer pin mounting groove corresponding position be provided with the installation through hole, offer tapped through hole on the hole wall of this installation through hole, the corresponding spinning of described spiral handspike is in described tapped through hole.
4. missile cabin according to claim 3 connects auxiliary mould, it is characterized in that: described tapped through hole has been arranged symmetrically with two about the center line that through hole is installed on circumferential along clip.
5. missile cabin according to claim 1 and 2 connects auxiliary mould, it is characterized in that: being used for of described spiral handspike and heading into end or ejecting the corresponding removable jacking block that is fixed with in end of end of spacer pin.
6. missile cabin according to claim 1 and 2 connects auxiliary mould, it is characterized in that: described clip comprises by the hinged upper and lower connecting plate of bearing pin, the end away from described bearing pin of the two corresponding upper and lower connecting plates of links difference of described clip.
7. missile cabin according to claim 6 connects auxiliary mould, it is characterized in that: described two links are respectively the first link and the second link, retaining mechanism comprises the connecting axle that is hinged on the first link, the end away from the first link of connecting axle is provided with external thread section, be provided with on the second link for the through hole of connecting axle inserting, retaining mechanism also comprises the locking nut of spinning on the external thread section of connecting axle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220635080 CN202964525U (en) | 2012-11-27 | 2012-11-27 | Missile bay section connection auxiliary tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220635080 CN202964525U (en) | 2012-11-27 | 2012-11-27 | Missile bay section connection auxiliary tool |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202964525U true CN202964525U (en) | 2013-06-05 |
Family
ID=48505653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220635080 Expired - Lifetime CN202964525U (en) | 2012-11-27 | 2012-11-27 | Missile bay section connection auxiliary tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202964525U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103759597A (en) * | 2014-01-14 | 2014-04-30 | 北京航空航天大学 | Missile cabin radial monoclinic bushing bolt connection structure |
| CN104260041A (en) * | 2014-09-15 | 2015-01-07 | 北京航天新风机械设备有限责任公司 | Special fixture for disassembling and assembling wedge-shaped ring |
| CN104314930A (en) * | 2014-10-13 | 2015-01-28 | 凯迈（洛阳）测控有限公司 | Adjustable clamp hoop and guide head fixing device using clamp hoop |
| CN104406468A (en) * | 2014-11-21 | 2015-03-11 | 中国空空导弹研究院 | Guided missile and engine cabin segment missile body thereof |
| CN104567561A (en) * | 2013-10-28 | 2015-04-29 | 北京临近空间飞行器系统工程研究所 | Special-shape missile bay section connecting structure for sectional fairing deploying |
| CN105129069A (en) * | 2015-08-04 | 2015-12-09 | 江西洪都航空工业集团有限责任公司 | Wedge block cabin connecting device |
| CN110160409A (en) * | 2019-02-25 | 2019-08-23 | 北京机电工程研究所 | A kind of odd-shaped cross section missile body joint structure |
-
2012
- 2012-11-27 CN CN 201220635080 patent/CN202964525U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104567561A (en) * | 2013-10-28 | 2015-04-29 | 北京临近空间飞行器系统工程研究所 | Special-shape missile bay section connecting structure for sectional fairing deploying |
| CN104567561B (en) * | 2013-10-28 | 2015-12-02 | 北京临近空间飞行器系统工程研究所 | A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering |
| CN103759597A (en) * | 2014-01-14 | 2014-04-30 | 北京航空航天大学 | Missile cabin radial monoclinic bushing bolt connection structure |
| CN103759597B (en) * | 2014-01-14 | 2015-06-17 | 北京航空航天大学 | Missile cabin radial monoclinic bushing bolt connection structure |
| CN104260041A (en) * | 2014-09-15 | 2015-01-07 | 北京航天新风机械设备有限责任公司 | Special fixture for disassembling and assembling wedge-shaped ring |
| CN104314930A (en) * | 2014-10-13 | 2015-01-28 | 凯迈（洛阳）测控有限公司 | Adjustable clamp hoop and guide head fixing device using clamp hoop |
| CN104406468A (en) * | 2014-11-21 | 2015-03-11 | 中国空空导弹研究院 | Guided missile and engine cabin segment missile body thereof |
| CN105129069A (en) * | 2015-08-04 | 2015-12-09 | 江西洪都航空工业集团有限责任公司 | Wedge block cabin connecting device |
| CN110160409A (en) * | 2019-02-25 | 2019-08-23 | 北京机电工程研究所 | A kind of odd-shaped cross section missile body joint structure |
| CN110160409B (en) * | 2019-02-25 | 2022-02-08 | 北京机电工程研究所 | Special-shaped section projectile body butt-joint structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130605 |