CN204749958U - Fixing device of big parts of aviation transportation trailer - Google Patents
Fixing device of big parts of aviation transportation trailer Download PDFInfo
- Publication number
- CN204749958U CN204749958U CN201520350722.XU CN201520350722U CN204749958U CN 204749958 U CN204749958 U CN 204749958U CN 201520350722 U CN201520350722 U CN 201520350722U CN 204749958 U CN204749958 U CN 204749958U
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- China
- Prior art keywords
- aviation
- large parts
- vehicle frame
- frame
- swinging strut
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Abstract
The utility model provides a fixing device of big parts of aviation transportation trailer, includes: lie in frame both ends and the pressure disk mechanism and the tensioning mechanism that link to each other respectively with the big parts of aviation, lie in frame both sides and the clamping jig who links to each other with the big parts of aviation and have the runing rest of fixing the frock, the terminal rotation with the frame of runing rest is connected, and the middle part and the frame of runing rest pass through the hydro -cylinder to be connected, and this runing rest is two parallel arrangement's C font structure frame and constitutes. The utility model discloses a main part welded structure, the three hole of being connected with the big parts of aviation adopt ladder round pin axle, the tight copper sheathing that rises fixed, main part welded structure lateral pin is the primary load bearing piece, compresses tightly lateral pin, the motion of the big parts vertical height orientation of restriction aviation through the clamp plate, the motion of the big parts horizontal direction of splayed pull rod restriction aviation, universal joint bearing adjusting yoke to with nut locking, overall structure is simple, convenient assembling.
Description
Technical field
The utility model relates to a kind of technology of special transport vehicle field, specifically a kind ofly exceed for volume the large parts transtainer of aviation that communications and transportation specifies, the large components fixing device of aviation that it uses.
Background technology
It is all superelevation ultra-wide part that the large parts of aviation transport generally on highway, needs to use special transtainer to transport.Because China Aviation large parts manufacture starting is late, Special transport trailer supporting does not with it have yet, and transports so large for aviation parts are fixed on low flat-bed trailer by the simple fixed form of the basic employing of aviation large parts transport before.The large parts of such aviation are not fixedly rationally and actv. on transtainer, may tear, be out of shape, produce the dangerous destructions such as internal stress the large parts generation of aviation under limit traffic condition, thus also can produce imponderable loss to the performance of the large parts of aviation.
The transport of existing aviation large parts uses simple imitated structure part to be held by large for aviation parts, and imitated structure part is bolted or is weldingly fixed on vehicle frame.The shortcoming of prior art is that the large parts of aviation are placed on trailer simply by imitated structure, not by frock by large for aviation parts and trailer fastening, also the not good all directions by large for aviation parts retrain, and during transport, the large parts of aviation are fixing not firm.
The road transport of the large parts of aviation, is generally ultra-wide superelevation, and the overall dimensions superelevation ultra-wide of transtainer, center of gravity is higher.The large parts of aviation need be fixed with trailer chassis in transit, ensures transportation safety.Generally vehicle frame during transport, the large parts of aviation by frock be fixedly connected with one, security requirement is very high.Frock plays lifting, is fixedly connected with function with vehicle frame on transtainer.The impact load produced in the large parts own wt of aviation and transportation conducts to vehicle frame by frock.Namely frock will limit the large parts all directions motion of aviation, has enough intensity again to meet the requirement of multiple operating mode lower stress.As critical parts, frock, as being connected and fixed device between vehicle frame and the large parts of aviation, should being protected large piece safety, play fixing spacing, lifting effect again.
The large parts own wt of aviation bears by frock, profiling in transportation.Frock is fixed by swinging strut on vehicle frame, and swinging strut bears the large parts own wt of aviation and impact load.Frock is arranged on swinging strut, the large parts all directions motion of restriction aviation, at profiling supporting place aviation large parts both sides design clamping device, prevents the large member forward end of aviation at trailer left and right directions play.Meanwhile, also need to increase presser device and compress the large parts of aviation, the motion of restriction front height direction.Because aviation large parts overall dimensions is larger, in transportation may there is slope in road surface, avoids the large parts of aviation to appear on vehicle frame and tumble, need design splayed tensioner mechanism at the other end.
The large parts own wt of aviation is by frock in transportation, and profiling is born.Frock should meet requirement of strength, meets convenient installation, dismounting requirement again.Also need at frock place the large parts all directions of restriction aviation are moved simultaneously.
Utility model content
The utility model, for prior art above shortcomings, proposes the anchor fitting of the large parts transtainer of a kind of aviation, and structure is simple, easy to assembly, safe and reliable.
The utility model is achieved through the following technical solutions:
The utility model relates to the anchor fitting of the large parts transtainer of a kind of aviation, comprising: be positioned at vehicle frame two ends and respectively the compressing mechanism that is connected of parts large with aviation with tensioner mechanism, be positioned at vehicle frame both sides and the clamping device be connected with the large parts of aviation and the swinging strut with fixing tool.
End and the vehicle frame of described swinging strut are rotationally connected, and the middle part of swinging strut is connected by oil cylinder with vehicle frame, and this swinging strut is two C character form structure frame compositions be arranged in parallel.
Described fixing tool is flexibly connected with swinging strut, and this fixing tool is inverted T-shape structure, and its top is provided with slip lateral pin, and two ends, bottom are respectively equipped with two rotating tension bars and form splayed Tiebar structure.
Described flexible connection to be connected with swinging strut by the slip lateral pin of fixing tool and swinging strut moving contact and splayed Tiebar structure and to be achieved.
Described moving contact to contact with described slip lateral pin be achieved by being arranged at sliding tray on swinging strut.
Described sliding tray is preferably provided with pressing plate.
Lockout mechanism is provided with between described fixing tool and swinging strut, for completing the relative position locked after swinging strut angular adjustment, fixing tool are connected with the large parts of aviation between the two, this lockout mechanism comprises: be arranged at knock hole on swinging strut and one end is connected with fixing tool, and the other end is through the radius stay of knock hole.
End and the vehicle frame of described clamping device are rotationally connected, and the middle part of clamping device is connected by oil cylinder with vehicle frame, and this clamping device is two C character form structure frame compositions be arranged in parallel.
Described tensioner mechanism comprises: the pull bar that one end is connected with vehicle frame and the tension frame be connected with pull bar, wherein: tension frame is fixedly connected with the large parts of aviation.
The large parts of described aviation are provided with chute, and described tension frame is achieved a fixed connection by the bolt be socketed on chute.
The position that described bolt contacts with chute is provided with protection copper sheathing.
The large parts of described aviation are provided with protection rubber block further, to reduce the breakage of stress concentration portion position to the large parts of aviation.
Described compressing mechanism comprises: the platen frame be connected with vehicle frame and rotation are arranged at the platen arm that on platen frame, parts large with aviation contact, wherein: the end of platen arm is provided with platen, this platen contacts with the large part side of aviation and applies the thrust parallel with vehicle frame direction.
Described vehicle frame front end is provided with profiling beam support, and this profiling beam support is perpendicular to vehicle frame length direction using as vehicle frame main beam, and the upper surface of the beam support of profiling simultaneously and the head end bottom shape of the large parts of aviation match.
The upper surface of described profiling beam support and the position of the large component contact of aviation are provided with the sponge shock absorber that canvas wraps up.
Technique effect
Compared with prior art, the utility model adopts main body welded structure, three holes being connected with the large parts of aviation adopt ladder pin shaft, tensioner copper sheathing is fixed.Main body welded structure lateral pin is main load-bearing part, compresses lateral pin by pressing plate, the motion of restriction aviation large parts vertical dimension direction.Splayed pull bar restriction aviation large component level direction motion, gimbal suspension bearing adjusting yoke, and use nut locking.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation;
Fig. 2 is swinging strut schematic diagram;
In figure: a is lateral plan, b is close-up schematic view;
Fig. 3 is fixing tool scheme of installation;
Fig. 4 is fixing tool schematic diagram;
Fig. 5 is Fig. 4 installation process schematic diagram;
In figure: a is lateral plan, b is close-up schematic view;
Fig. 6 is clamping device schematic diagram;
In figure: a is lateral plan, b is close-up schematic view;
Fig. 7 is tensioner mechanism schematic diagram;
In figure: a is lateral plan, b is close-up schematic view;
Fig. 8 is compressing mechanism schematic diagram;
Fig. 9 is profiling beam schematic diagram.
Detailed description of the invention
Below embodiment of the present utility model is elaborated; the present embodiment is implemented under premised on technical solutions of the utility model; give detailed embodiment and concrete operating process, but protection domain of the present utility model is not limited to following embodiment.
Embodiment 1
As shown in Figure 1, the present embodiment comprises: be positioned at vehicle frame 1 two ends and respectively the compressing mechanism 3 that is connected of parts 2 large with aviation with tensioner mechanism 4, be positioned at vehicle frame 1 both sides and the clamping device 5 be connected with the large parts 2 of aviation and the swinging strut 7 with fixing tool 6.
As shown in Figure 2, described swinging strut 7, by oil cylinder 8 Telescopic rotating, contacts with vehicle frame 1 bottom swinging strut 7, and bolt 9 is fixed.
Described swinging strut 7 top is provided with for fixing tool lateral pin standing groove 10, and the slip lateral pin 11 of the large parts fixing tool 6 of lifting aviation is placed in groove 10 and also can rotates adjustment.
As shown in Figure 3 and Figure 4, described fixing tool 6 is flexibly connected with swinging strut 7, and this fixing tool 6 is inverted T-shape structure, and its top is provided with slip lateral pin 11, and two ends, bottom are respectively equipped with two rotating tension bars and form splayed Tiebar structure 12.
As shown in Figure 4, described fixing tool 6 comprises: the main body welding body 13 of slip lateral pin 11, splayed Tiebar structure 12, inverted T-shape structure, wherein: the two ends of splayed Tiebar structure 12 weld body 13 with main body respectively and swinging strut 7 is rotationally connected.
Described splayed Tiebar structure 12 is made up of two rotating tension bars, each rotating tension bar comprises: U-joint 14, drag link body 15 and gimbal suspension bearing 16, wherein: U-joint 14 welds body 13 and is rotationally connected with main body, the two ends of drag link body 15 are rotationally connected with U-joint 14 and gimbal suspension bearing 16 respectively, and gimbal suspension bearing 16 is rotationally connected by pivot pin 17 and swinging strut 7.
Described drag link body 15 is connected by jam nut 18 with between gimbal suspension bearing 16.
Described slip lateral pin 11 and U-joint 14 all weld body 13 by nut shaft pin mechanism 19,20 and main body and are connected.
Because aviation large parts 2 are long, be connected with two places with vehicle frame 1, a place is three holes 21 that fixing tool 6 connects, and another place is aviation large parts belly profiling beam support 22.
After installing, fixing tool 6 and the large parts 2 of aviation fix, and the large parts of lifting aviation are on vehicle frame 1, and radius stay 23 locates knock hole 21.Slip lateral pin 11 is placed on swinging strut 7, pressing plate 24 is installed, take out radius stay 23, splayed Tiebar structure 12 is installed, nut shaft pin mechanism 19,20, gimbal suspension bearing 16, and regulated the length of splayed Tiebar structure 12 by gimbal suspension bearing 16, after fixed pin shaft is fixing, jam nut is fixed, as shown in figure 5 a and 5b.
During dismounting, take out fixed pin shaft, two pull bars can be shown outward, unscrew pull bar and take out, and lateral pin top board takes out simultaneously.Now can lift the large parts of aviation.Dismantle bearing pin one and bearing pin two again, pull down fixing tool welding body.
As shown in figures 6 a and 6b, described clamping device 6, by oil cylinder 25 Telescopic rotating, after fitting, is fixed by bolt 26 bottom clamping device 6 with vehicle frame 1.
The top swivel mount 27 being provided with parts 2 large with aviation and being connected is rotated at the top of described clamping device 6, this top swivel mount 27 is fixed by two bearing pins 28,29, bearing pin 28 upper back swivel mount 27 of dismantling can turn up, and does not interfere when ensureing the large parts entrucking of aviation with clamping device 6.
As shown in Figure 7a, the tension frame 30 of described tensioner mechanism 4 there is through hole, be connected to by bolt 31 in the chute 32 of the large parts 2 of aviation, be configured with copper sheathing 33 in addition for the protection of the large parts 2 of aviation.
As shown in Figure 7b, between described tension frame 30 and chute 32, there is rubber block 34, to avoid stressed generation impression in the rear transport of fastening nut 37.
The lower end of described pull bar 35 is connected with vehicle frame 1, and bearing pin 36 is fixed.In transportation, run into slope can prevent the large parts of aviation from tumbling on vehicle frame 1.
As shown in Figure 8, described compressing mechanism 3 comprises: the platen frame 38 be connected with vehicle frame 1 and rotate and be arranged at the platen arm 39 that on platen frame 38, parts 2 large with aviation contact, wherein: the end of platen arm is provided with platen 40, this platen contacts with the large part side of aviation and applies the thrust parallel with vehicle frame direction.
When the large parts 2 of aviation load, pull down platen arm 39, platen frame 38 rotates to outside, after the large parts 2 of aviation place, then rotary platen frame 38, assembling pull bar fixed platen mechanism 3, compresses the large parts of aviation by platen 40, nut locking.
As shown in Figure 9, described vehicle frame 1 front end is provided with profiling beam support 41, and this profiling beam support 41 is perpendicular to vehicle frame 1 length direction using as vehicle frame main beam, and the upper surface of the beam support of profiling simultaneously 41 and the head end bottom shape of the large parts of aviation match.
The upper surface of described profiling beam support and the position of the large component contact of aviation are provided with the sponge shock absorber 42 that canvas wraps up.
When the large parts 2 of aviation load, fixing tool joint lateral pin is first placed on swinging strut 7, take lateral pin as S. A., and the large parts of slow circumvolve are until large parts laminating profiling beam.
The present embodiment realizes fixing in the following manner:
1) oil cylinder by being connected with vehicle frame 1 in the middle part of swinging strut 7 stretches, and swinging strut 7 is rotated to position shown in Fig. 1, and is tightened by the bolt 9 in Fig. 2;
2) oil cylinder by being connected with vehicle frame 1 in the middle part of clamping device 6 stretches, and clamping device 6 is rotated to position shown in Fig. 6, and is tightened by the bolt 26 in Fig. 6;
3) the top swinging strut 7 in Fig. 6 is rotated laterally;
4) fitting device shown in Fig. 3 is first connected with hole two with the respective aperture one of the large parts of the aviation in Fig. 4;
5) large for aviation parts are lifted on transtainer together with fitting device, the large parts of aviation are contacted with the profiling beam of Fig. 9, and fitting device is connected with swinging strut 7, as shown in Figure 3;
6) the top swinging strut 7 in Fig. 6 is inwardly rotated, make platen and the large component contact of aviation and compress;
7) compressing mechanism 3 of rotation diagram 8, makes platen be pressed in above the large parts of aviation, and is connected and fixed by pull bar;
8) bolt shown in Fig. 7 and copper sheathing are assembled on the large parts of aviation by Fig. 7, then by framework by hole to on bolt, and tighten nut above;
9) be connected above the pull bar in Fig. 7 with framework, be connected with vehicle frame 1 below, and strain.
Compared with prior art, the advantage of this device comprises:
1. clamping device 6 is when loading, and upper swivel mount can turn up, and does not interfere when loading the large parts of aviation with clamping device 6.
2. compressing mechanism 3 adopts rotation mode, and structure is simple, easy to operate.
3. when the large parts of aviation load, frock lateral pin is first placed on swinging strut 7, take lateral pin as S. A., and the large parts of slow circumvolve aviation are until aviation large parts laminating profiling beam.
4. adopt swinging strut 7, clamping device 6, tensioner mechanism 4 and the large parts of compressing mechanism 3 combined action restriction aviation to move in all directions during the transport of aviation large parts, ensure the large parts of aviation and vehicle frame 1 fixing-stable, transport safely.
5. due to special connection mode, frock lateral pin namely bear to impact load and the large parts own wt of aviation, with limit aviation large parts all directions degree of freedom.
Claims (10)
1. the anchor fitting of the large parts transtainer of aviation, it is characterized in that, comprising: be positioned at vehicle frame two ends and respectively the compressing mechanism that is connected of parts large with aviation with tensioner mechanism, be positioned at vehicle frame both sides and the clamping device be connected with the large parts of aviation and the swinging strut with fixing tool;
End and the vehicle frame of described swinging strut are rotationally connected, and the middle part of swinging strut is connected by oil cylinder with vehicle frame, and this swinging strut is two C character form structure frame compositions be arranged in parallel.
2. the anchor fitting of the large parts transtainer of aviation according to claim 1, it is characterized in that, described fixing tool is flexibly connected with swinging strut, this fixing tool is inverted T-shape structure, its top is provided with slip lateral pin, and two ends, bottom are respectively equipped with two rotating tension bars and form splayed Tiebar structure.
3. the anchor fitting of the large parts transtainer of aviation according to claim 2, is characterized in that, described flexible connection to be connected with swinging strut by the slip lateral pin of fixing tool and swinging strut moving contact and splayed Tiebar structure and to be achieved.
4. the anchor fitting of the large parts transtainer of aviation according to claim 3, is characterized in that, described moving contact to contact with described slip lateral pin be achieved by being arranged at sliding tray on swinging strut.
5. the anchor fitting of the large parts transtainer of aviation according to claim 1, it is characterized in that, lockout mechanism is provided with between described fixing tool and swinging strut, for completing the relative position locked after swinging strut angular adjustment, fixing tool are connected with the large parts of aviation between the two, this lockout mechanism comprises: be arranged at knock hole on swinging strut and one end is connected with fixing tool, and the other end is through the radius stay of knock hole.
6. the anchor fitting of the large parts transtainer of aviation according to claim 1, it is characterized in that, end and the vehicle frame of described clamping device are rotationally connected, and the middle part of clamping device is connected by oil cylinder with vehicle frame, and this clamping device is two C character form structure frame compositions be arranged in parallel.
7. the anchor fitting of the large parts transtainer of aviation according to claim 1, it is characterized in that, described tensioner mechanism comprises: the pull bar that one end is connected with vehicle frame and the tension frame be connected with pull bar, wherein: tension frame is fixedly connected with the large parts of aviation.
8. the anchor fitting of the large parts transtainer of aviation according to claim 7, is characterized in that, the large parts of described aviation are provided with chute, and described tension frame is achieved a fixed connection by the bolt be socketed on chute.
9. the anchor fitting of the large parts transtainer of aviation according to claim 1, it is characterized in that, described compressing mechanism comprises: the platen frame be connected with vehicle frame and rotation are arranged at the platen arm that on platen frame, parts large with aviation contact, wherein: the end of platen arm is provided with platen, this platen contacts with the large part side of aviation and applies the thrust parallel with vehicle frame direction.
10. the anchor fitting of the large parts transtainer of aviation according to claim 1, it is characterized in that, described vehicle frame front end is provided with profiling beam support, this profiling beam support is perpendicular to vehicle frame length direction using as vehicle frame main beam, and the upper surface of the beam support of profiling simultaneously and the head end bottom shape of the large parts of aviation match.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520350722.XU CN204749958U (en) | 2015-05-27 | 2015-05-27 | Fixing device of big parts of aviation transportation trailer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520350722.XU CN204749958U (en) | 2015-05-27 | 2015-05-27 | Fixing device of big parts of aviation transportation trailer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204749958U true CN204749958U (en) | 2015-11-11 |
Family
ID=54464702
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520350722.XU Expired - Fee Related CN204749958U (en) | 2015-05-27 | 2015-05-27 | Fixing device of big parts of aviation transportation trailer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204749958U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104842852A (en) * | 2015-05-27 | 2015-08-19 | 中航（上海）汽车技术有限公司 | Fixing device of large-size aviation component transport trailer |
| CN105383368A (en) * | 2015-11-23 | 2016-03-09 | 贵州航天天马机电科技有限公司 | Transportation fixing device of landing gear brackets |
-
2015
- 2015-05-27 CN CN201520350722.XU patent/CN204749958U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104842852A (en) * | 2015-05-27 | 2015-08-19 | 中航（上海）汽车技术有限公司 | Fixing device of large-size aviation component transport trailer |
| CN104842852B (en) * | 2015-05-27 | 2017-08-29 | 上海航空特种车辆有限责任公司 | The fixing device of the big part transtainer of aviation |
| CN105383368A (en) * | 2015-11-23 | 2016-03-09 | 贵州航天天马机电科技有限公司 | Transportation fixing device of landing gear brackets |
| CN105383368B (en) * | 2015-11-23 | 2018-06-22 | 贵州航天天马机电科技有限公司 | A kind of transport fixing device of undercarriage bracket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160525 Address after: 201906 Baoshan District, Gu village, an industrial park, No. 1 Fu Road, No. 758, Shanghai Patentee after: Special/Aviation Vehicles Co., Ltd., Shanghai Address before: 200092, room 32, 1106-9 Tieling Road, Shanghai, Yangpu District Patentee before: AVIC (Shanghai) Automotive Technology Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151111 Termination date: 20210527 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |