CN202623305U - Bonding device of butt girder and butt frame of satellite fairing body - Google Patents
Bonding device of butt girder and butt frame of satellite fairing body Download PDFInfo
- Publication number
- CN202623305U CN202623305U CN 201120552720 CN201120552720U CN202623305U CN 202623305 U CN202623305 U CN 202623305U CN 201120552720 CN201120552720 CN 201120552720 CN 201120552720 U CN201120552720 U CN 201120552720U CN 202623305 U CN202623305 U CN 202623305U
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- butt
- frame
- seat
- pressing block
- girder
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- Expired - Fee Related
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Abstract
The utility model discloses a bonding device of a butt girder and a butt frame of a satellite fairing body. The bonding device comprises a clamping mechanism I, a clamping mechanism II, a pressing mechanism and a positioning mechanism; a slide groove in the clamping mechanism I is installed on a base seat through screws, a slide block is sleeved in the slide groove in an inlaid mode, a push rod is connected with the slide block in a spherical hinged mode, and a support frame is connected with the push rod in a threaded mode; a movable pressing block in the clamping mechanism II is installed on a tail seat through the screws and connected with a movable pressing block seat through pins, and a waist-shaped hole is arranged in the movable pressing block; one end of a pressing block in the pressing mechanism is tightly attached to the base seat, the other end of the pressing block is tightly attached to the butt girder and the butt frame, and the middle of the pressing block is tightly pressed through the screws; and a positioning block in the positioning mechanism is installed on the tail seat through positioning pins and clamping screws. By changing the clamping mode, the bonding device of the butt girder and the butt frame of the satellite fairing body can effectively control accuracy of bonding and positioning and pressure strength in a bonding process; and structural machining is simple, structural overall quality is light, strength is ensured, and weight is reduced.
Description
Technical field
The utility model relates to a kind of mechanical driving device, is specifically related to a kind of satellite fairing cover body butt joint purlin interface frame, mating frame adhering device.
Background technology
Satellite fairing is used to protect satellite and other payload, receives aerodynamic force to prevent satellite, the influence of hostile environment such as shake of pneumatic heating and sound, and it is the important component part of carrier rocket.At present satellite fairing is generally clampshell (HALF) structure, by termination, inner cone section, cylindrical section, inverted cone segment with vertically reach lateral separation mechanism etc. and form.Head design is an overall structure, adopts the nonmetallic materials moulding by casting; All the other each Duan Junyong stringers are bent into skeleton, rivet covering again and form.This structure processed complex, the structural entity quality is heavy.Existing case adopts integrated poured the forming of composite of lighter weight, does not need skeleton structure, has not only guaranteed intensity but also reduced weight.
For adapting to the integrally-built variation of radome fairing, adopted novel technique for bonding.New technology connects butt joint purlin (vertically separating mechanism carrier), interface frame, mating frame (lateral separation organizational carrier) and the case of radome fairing with bonding way.The processing technology of radome fairing changes, and previously used satellite fairing riveting set no longer is fit to the bonding manufacturing of new satellite fairing.
Summary of the invention
The utility model purpose is to solve the bonding problem of case and butt joint purlin, interface frame, mating frame, provides a kind of cemented in place precision good a kind of satellite fairing cover body butt joint purlin interface frame, mating frame adhering device.
The technical scheme that the utility model solves its technical problem is: a kind of satellite fairing cover body butt joint purlin interface frame, mating frame adhering device is characterized in that comprising clamp mechanism I, clamp mechanism II, hold-down mechanism, detent mechanism; In the said clamp mechanism I chute through screw be installed on the base, slide block is nested in the chute, push rod is connected with the slide block ball pivot, support is threaded with push rod.
The movable holddown seat is installed on the tailstock through screw in the said clamp mechanism II, and movable holddown is connected with the movable holddown seat through pin, has waist-shaped hole on the movable holddown.
Briquetting one end is close to base in the said hold-down mechanism, and an end is close to butt joint purlin, interface frame, mating frame, and screw in compression is passed through in the centre.
Locating piece is installed on the tailstock through alignment pin and pinching screw in the said detent mechanism.
The beneficial effect of the utility model is: through changing clamping mode, control pressure size in cemented in place precision and the bonding process effectively; Structure processing is simple, and the structural entity light weight has not only guaranteed intensity but also reduced weight.
Description of drawings
Fig. 1 is the utility model satellite fairing cover body butt joint purlin interface frame, mating frame adhering device sketch map.
Fig. 2 is the left view of the utility model Fig. 1.
Fig. 3 is the utility model clamp mechanism I sketch map.
Fig. 4 is the utility model clamp mechanism II sketch map.
Fig. 5 is the utility model hold-down mechanism sketch map.
Fig. 6 is the utility model detent mechanism sketch map.
Comprise 1 base, 2 chutes, 3 slide blocks, 4 push rods, 5 supports, 6 briquettings, 7 tailstocks, 8 locating pieces, 9 alignment pins, 10 pinching screws, 11 movable holddown seats, 12 movable holddowns, 13 support members.
The specific embodiment
Shown in Fig. 1-6, the utility model device comprises: base 1, chute 2, slide block 3, push rod 4, support 5, briquetting 6, tailstock 7, locating piece 8, alignment pin 9, pinching screw 10, movable holddown seat 11, movable holddown 12, support member 13.
Chute 2 through screw be installed on the base 1, slide block 3 is nested in the chute 2, push rod 4 is connected with slide block 3 ball pivots, support 5 is threaded with push rod 4, composition clamp mechanism I.
Briquetting 6 one ends are close to base 1, one end and are close to butt joint purlin, interface frame, mating frame, and are middle through screw in compression, form hold-down mechanism.
Locating piece 8 is installed on the tailstock 7 through alignment pin 9 and pinching screw 10, forms detent mechanism.
Before bonding, pull down detent mechanism and the movable holddown 11 of clamp mechanism II is turned up.
At first through hold-down mechanism will dock the purlin, interface frame, mating frame is installed on the butt joint purlin interface frame, mating frame adhering device of radome fairing cover body, again the radome fairing cover body is installed on the interface frame, mating frame adhering device of radome fairing cover body butt joint purlin.Case through the positioning step location, is located through detent mechanism on tailstock 7 on base 1.Detent mechanism is put locating piece 8 earlier, behind the insertion alignment pin 9, tightens location, pinching screw 10 back product.Unclamp hold-down mechanism, make the slide block 3 of clamp mechanism I contact butt joint purlin, interface frame, mating frame and case respectively, make the clamp mechanism II movable holddown 12 contact cases.Tighten the push rod 4 of clamp mechanism I with torque wrench, push rod 4 withstands slide block 3, makes it compress butt joint purlin, interface frame, mating frame and case.Tighten the screw of clamp mechanism II with torque wrench, utilize leverage to compress case.
Claims (1)
1. a satellite fairing cover body butt joint purlin interface frame, mating frame adhering device is characterized in that comprising clamp mechanism I, clamp mechanism II, hold-down mechanism, detent mechanism;
In the said clamp mechanism I chute through screw be installed on the base, slide block is nested in the chute, push rod is connected with the slide block ball pivot, support is threaded with push rod;
The movable holddown seat is installed on the tailstock through screw in the said clamp mechanism II, and movable holddown is connected with the movable holddown seat through pin, has waist-shaped hole on the movable holddown;
Briquetting one end is close to base in the said hold-down mechanism, and an end is close to butt joint purlin, interface frame, mating frame, and screw in compression is passed through in the centre;
Locating piece is installed on the tailstock through alignment pin and pinching screw in the said detent mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120552720 CN202623305U (en) | 2011-12-27 | 2011-12-27 | Bonding device of butt girder and butt frame of satellite fairing body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120552720 CN202623305U (en) | 2011-12-27 | 2011-12-27 | Bonding device of butt girder and butt frame of satellite fairing body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202623305U true CN202623305U (en) | 2012-12-26 |
Family
ID=47376544
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120552720 Expired - Fee Related CN202623305U (en) | 2011-12-27 | 2011-12-27 | Bonding device of butt girder and butt frame of satellite fairing body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202623305U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105540436A (en) * | 2016-01-06 | 2016-05-04 | 天津航天长征火箭制造有限公司 | Locking device and closing method for fairing adopting locking device |
| CN105628352A (en) * | 2014-11-03 | 2016-06-01 | 上海宇航***工程研究所 | Static test method of integrated carrier rocket satellite radome |
| CN105619145A (en) * | 2015-12-28 | 2016-06-01 | 哈尔滨工业大学 | Clamping device and method used for precise machining of outer surface of shape-preserving fairing |
| CN106926006A (en) * | 2017-04-25 | 2017-07-07 | 哈尔滨工业大学 | A kind of clamping device and clamping method for the conformal head-shield Surface Machining of steepness high |
-
2011
- 2011-12-27 CN CN 201120552720 patent/CN202623305U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105628352A (en) * | 2014-11-03 | 2016-06-01 | 上海宇航***工程研究所 | Static test method of integrated carrier rocket satellite radome |
| CN105628352B (en) * | 2014-11-03 | 2018-04-06 | 上海宇航***工程研究所 | The slow test method of integrated carrier rocket satellite fairing |
| CN105619145A (en) * | 2015-12-28 | 2016-06-01 | 哈尔滨工业大学 | Clamping device and method used for precise machining of outer surface of shape-preserving fairing |
| CN105619145B (en) * | 2015-12-28 | 2017-11-03 | 哈尔滨工业大学 | For the precision machined clamping device in conformal dome outer surface and clamping method |
| CN105540436A (en) * | 2016-01-06 | 2016-05-04 | 天津航天长征火箭制造有限公司 | Locking device and closing method for fairing adopting locking device |
| CN106926006A (en) * | 2017-04-25 | 2017-07-07 | 哈尔滨工业大学 | A kind of clamping device and clamping method for the conformal head-shield Surface Machining of steepness high |
| CN106926006B (en) * | 2017-04-25 | 2019-01-18 | 哈尔滨工业大学 | A kind of clamping device and clamping method for the conformal head-shield surface processing of high steepness |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121226 Termination date: 20131227 |