CN105329767B - A kind of aircraft lifting tool - Google Patents
A kind of aircraft lifting tool Download PDFInfo
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- CN105329767B CN105329767B CN201510844527.7A CN201510844527A CN105329767B CN 105329767 B CN105329767 B CN 105329767B CN 201510844527 A CN201510844527 A CN 201510844527A CN 105329767 B CN105329767 B CN 105329767B
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- hanging beam
- aircraft
- hanging
- hanger bolt
- main body
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Abstract
The present invention provides a kind of aircraft lifting tool, belongs to Air Ground Equipment structure-design technique field, and for aircraft production and the slinging work in installation process, hanging beam main body is fixedly connected into closed frame structure by hanging beam connector；Hanger bolt is the integrated formed structure that screw rod one end is fixedly connected with auricle；Hanging beam is fixed on lifting point at hanging beam connector by the hoist cable, and hanging beam connector connects the hanger bolt by the hoist cable, and hanger bolt is threadedly coupled with the body of aircraft.Aircraft lifting tool provided by the invention reduces the attachment moment of flexure of hanging beam by triangular truss plane loading characteristic；Pass through the hanger bolt with corner, eliminate the additional bending moment of body sling point, the stress level for reducing housing construction hanging regional structure and suspender, reduces the design weight of housing construction and suspender, improves the degree of safety of body lifting process and the portability of body hanging.
Description
Technical field
The invention belongs to Air Ground Equipment structure-design technique fields, and work is lifted by crane in particular to a kind of aircraft
Tool, for aircraft production and the slinging work in installation process.
Background technology
Aircraft needs, by airframe components integral lifting, to be transported, turned during the manufacturing and flight-line service
The work such as shifting, installation.Design principle of the conventional aircraft suspender based on vertical lifting is arranged according to aircraft component hanging structure
It is designed installation (as shown in Figure 6).
Aircraft component size length-width ratio of new generation is big, and hanging structure arrangement is uneven；To safeguard aircraft surface shape
Smoothness, with outer surface normal direction there are angle, these factors lead to aircraft suspender in lifting direction at aircraft sling point
It needs to undertake prodigious additional bending moment.To ensure that the hanging safety of aircraft, the influence of offsetting additional moment of flexure, suspender need to increase
Additional weight occupies larger operating space, increases the difficulty of outfield lifting.
The technical issues of present urgent need to resolve is how to design a kind of aircraft lifting tool, to solve to deposit in the prior art
Defect.
Invention content
It is an object of the invention to solve above-mentioned deficiency in the prior art, a kind of aircraft lifting tool is provided, is used for
Aircraft produces and the slinging work in installation process.
The purpose of the present invention is achieved through the following technical solutions：A kind of aircraft lifting tool, including hoist cable, hanging beam, hang
Bolt is hung, hanging beam includes hanging beam main body, hanging beam connector, and hanging beam main body is fixedly connected into closed frame knot by hanging beam connector
Structure；
Hanger bolt is the integrated formed structure that screw rod one end is fixedly connected with auricle, definition：Pitch axis is in auricle
Projection in the plane and angle formed by pitch axis be a, wherein 00A≤90 ＜0。
Hanging beam is fixed on lifting point at hanging beam connector by the hoist cable, described in hanging beam connector is connected by hoist cable
Hanger bolt, hanger bolt are threadedly coupled with the body of aircraft.
In said program preferably, hanging beam main body be provided at both ends with the matched bonding pad of hanging beam connector, in hanging beam
Hanging auricle is provided in main body, for adjusting lifting center of gravity.There is higher want in bonding pad to the rigidity of structure compared with other positions
It asks, ensures that bonding pad cannot generate structural damage due to by the concentrated stress lifted by crane.
In any of the above-described scheme preferably, hanging beam main body is that machinery is integrally machined shaped structure or welding fabrication structure.
In any of the above-described scheme preferably, hanging beam connector is the angled construction that machinery is integrally machined forming, horn shape knot
The vertex of structure is provided with the connecting pole for being connect with hoist cable, and two arms of angle are provided with the mounting groove coordinated with hanging beam main body.
The advantageous effect of aircraft life cycle load real-time monitoring method provided by the present invention is, passes through triangle purlin
Frame plane loading characteristic, reduces the moment of flexure of the attachment of hanging beam；By the hanger bolt with corner, body sling point is eliminated
Additional bending moment.By above 2 points, the stress level of housing construction hanging regional structure and suspender is reduced, machine is reduced
The design weight of body structure and suspender improves the degree of safety of body lifting process and the portability of body hanging.
Description of the drawings
Fig. 1 is the structural schematic diagram of a preferred embodiment and body cooperation for aircraft lifting tool according to the invention；
Fig. 2 is the side view of the hanging beam of preferred embodiment shown in Fig. 1 of aircraft lifting tool according to the invention；
Fig. 3 is that the cross-section structure of the hanging beam of preferred embodiment shown in Fig. 1 of aircraft lifting tool according to the invention shows
It is intended to；
Fig. 4 is the knot of the hanging beam jointing of preferred embodiment shown in Fig. 1 of aircraft lifting tool according to the invention
Structure schematic diagram；
Fig. 5 is the attachment lug of preferred embodiment shown in Fig. 1 of aircraft lifting tool according to the invention and connect spiral shell
The structural schematic diagram of bolt cooperation；
Fig. 6 is the stress diagram of aircraft hanging structure in the prior art.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
The every other embodiment that member is obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, and does not indicate or imply the indicated dress
It sets or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as protecting the present invention
The limitation of range.
As Figure 1-Figure 5, aircraft lifting tool provided by the invention, in aircraft production and installation process
Slinging work, including hoist cable 1, hanging beam 2, hanger bolt 4,2 main body of hanging beam are fixedly connected into closed frame by hanging beam connector
Structure；Hanger bolt 4 is the integrated formed structure that screw rod one end is fixedly connected with auricle, definition：Pitch axis is in auricle institute
Projection in the plane is a with angle formed by pitch axis, wherein 00A≤90 ＜0.Hanging beam 2 is at hanging beam connector
It is fixed on lifting point by hoist cable 1,2 connector of hanging beam connects the hanger bolt 4, hanger bolt 4 and aircraft by hoist cable 1
Body 5 is threadedly coupled.Hanging beam main body be provided at both ends with the matched bonding pad 3 of hanging beam connector, be provided in hanging beam main body
Auricle 6 is hung, for adjusting lifting center of gravity.Hanging beam main body is that machinery is integrally machined shaped structure.Hanging beam main body is welded for structural member
It is the angled construction that machinery is integrally machined forming to connect molding structure or hanging beam connector, vertex be provided with for hang
The connecting pole that rope 1 connects, two arms of angle are provided with the mounting groove coordinated with hanging beam main body.
Aircraft hanger is triangular truss structure, and three sides of hanger are three load metallic rods of pin connection,
Hanger is parallel with horizontal plane during lifting, and hanger skeleton is subjected only to compressive load in face；Hanger bolt 4 is turnover integral type knot
Structure, deflection angle are equal to body outer surface tangent line angle with horizontal plane, and hanger bolt 4 is connect with body 5 by screw thread, ensured simultaneously
Bolt turnover region is not interfered with housing construction.
Hanger structure includes hanging beam, hanging beam jointing.Hanging beam is that metal machine adds or welding structure, both ends need to retain with
The bonding pad of hanging beam jointing, several hanging auricles are arranged in both sides, for adjusting lifting center of gravity；Hanging beam jointing is metal
Machine adds or welding structure, and it is the bonding pad being connect with hanging beam that intermediate arrangement, which has the connecting pole being connect with hoist cable, outside,；Hanging beam with hang
Beam attachment lug, through being bolted, plays the role of transmitting hanging beam axle power by side.
Hanger bolt is that metal machine adds structure, upper end to be hanging ring structure, and lower end is to have external screw thread, and both ends axis is in a clamp
Angle is the tangential angle with horizontal plane of Hangtag machine external surface.Hanger is connect by connecting pole, hoist cable with lifting instrument, and company is passed through
It connects column, hoist cable and hanger bolt to connect, hanger bolt is connect with body by screw thread, has the function that play body.
2 main body of hanging beam is " mouth " word beam, bears to hang load in the plane of hanging beam being subject to；Both ends setting hanging auricle,
Center of gravity for adjusting sling load ensures lifting plane；Bonding pad 7 is arranged in 2 both ends of hanging beam, and side arrangement 3 or more connects
Pillar 8 for being connect with hanging beam jointing 3, and ensures load transmission.3 end of hanging beam jointing is connection pillar, is used for
Upper and lower two hoist cables 1 are connected, are connect with lifting appliance by 1 hoist cable, are connect with hanger bolt 4 by lower suspender.Hoist cable 1
Type of attachment is ears --- monaural type of attachment ensures that 1 load of hoist cable is transmitted on pillar with shear pattern, avoids generating attached
Add moment of flexure.The stress form of hanging beam of the present invention is compared with traditional hanging beam stress form, is effectively reduced additional bending moment, is improved and hang
The integrated carrying efficiency of beam.
Hanger bolt 4, upper end are attachment lug 6, and lower end is the screw thread being connect with body, and the axis angle at both ends is body
Outer surface tangential direction angle with horizontal plane；Hanger bolt 4 is connect by hanging auricle 6 and hoist cable 1 with hanging beam 2, by outer
Screw thread is connect with body 5；Using deflection angle, the additional bending moment on hanger bolt is eliminated, reduces the stress level of auricle.It is
The stress form of hanger bolt 4 of the present invention and traditional hanger bolt 4 compares, and hanger bolt 4 of the invention optimizes load path,
Reduce the design weight of auricle.
It is described in detail above in association with the specific embodiment of the aircraft lifting tool of the present invention, but is not to this hair
Bright limitation, every any simple modification made to the above embodiment according to the technical essence of the invention belong to the present invention's
Technical scope, it is also necessary to which the scope of explanation, aircraft lifting tool technical solution according to the invention includes above-mentioned each portion
/ arbitrary combination.
Claims (5)
1. a kind of aircraft lifting tool, for aircraft production and the slinging work in installation process, including hoist cable (1), hang
Beam (2), hanger bolt (4), it is characterised in that：The hanging beam (2) includes hanging beam main body, hanging beam connector, and hanging beam main body passes through
Hanging beam connector is fixedly connected into closed frame structure；
The hanger bolt (4) is the integrated formed structure that screw rod one end is fixedly connected with auricle, definition：Pitch axis is in ear
Piece projection in the plane and angle formed by pitch axis be a, wherein 0 ° of a≤90 ° ＜；
The hanging beam (2) is fixed on lifting point at hanging beam connector by the hoist cable (1), and hanging beam connector is hung by described
Rope connects the hanger bolt (4), and the hanger bolt (4) is threadedly coupled with the body (5) of aircraft.
2. aircraft lifting tool as described in claim 1, it is characterised in that：The hanging beam main body is provided at both ends with and hanging beam
The matched bonding pad of connector (3) is provided with hanging auricle (6), for adjusting lifting center of gravity in the hanging beam main body.
3. aircraft lifting tool as claimed in claim 2, it is characterised in that：The hanging beam main body is that machinery is integrally machined into
Shape structure.
4. aircraft lifting tool as claimed in claim 2, it is characterised in that：The hanging beam main body is welding fabrication structure.
5. aircraft lifting tool as described in claim 1, it is characterised in that：Hanging beam connector is that machinery is integrally machined forming
Angled construction, vertex is provided with the connecting pole for being connect with the hoist cable (1), and two arms of angle are provided with and the hanging beam master
The mounting groove of body cooperation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510844527.7A CN105329767B (en) | 2015-11-26 | 2015-11-26 | A kind of aircraft lifting tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510844527.7A CN105329767B (en) | 2015-11-26 | 2015-11-26 | A kind of aircraft lifting tool |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105329767A CN105329767A (en) | 2016-02-17 |
| CN105329767B true CN105329767B (en) | 2018-08-24 |
Family
ID=55280584
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510844527.7A Active CN105329767B (en) | 2015-11-26 | 2015-11-26 | A kind of aircraft lifting tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105329767B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107188024B (en) * | 2017-07-10 | 2019-04-19 | 北京航天发射技术研究所 | A kind of aircraft combined sling |
| CN111017844A (en) * | 2019-12-04 | 2020-04-17 | 中国直升机设计研究所 | Collapsible easy dismouting's helicopter hoist |
| CN112408178B (en) * | 2020-11-06 | 2022-10-11 | 中国航发四川燃气涡轮研究院 | Centering lifting appliance for combustion chamber of aero-engine |
| CN113734950B (en) * | 2021-08-25 | 2023-10-20 | 湖北三江航天红阳机电有限公司 | Large-scale solid carrier horizontal modal test suspension device |
| CN117228500A (en) * | 2023-09-13 | 2023-12-15 | 成都飞机工业（集团）有限责任公司 | Unmanned aerial vehicle lifting system and lifting method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4074519A (en) * | 1977-03-31 | 1978-02-21 | American Hoist & Derrick Company | Swivel shackle |
| DE29611837U1 (en) * | 1996-07-06 | 1996-10-31 | HM-Betonfertigteilwerk Hans Mauthe GmbH & Co KG, 88319 Aitrach | Device for moving basement window walls |
| DE20021334U1 (en) * | 2000-12-16 | 2001-03-22 | J. D. Theile GmbH & Co KG, 58239 Schwerte | Stop ring |
| JP2008068973A (en) * | 2006-09-13 | 2008-03-27 | Daiwa House Ind Co Ltd | Hanging tool |
| CN103434922A (en) * | 2013-09-12 | 2013-12-11 | 中国海洋石油总公司 | Lifting point of all-rotation shell flange |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09118489A (en) * | 1995-10-24 | 1997-05-06 | Toshiba Corp | Hoisting accessory |
| CN202400723U (en) * | 2011-12-30 | 2012-08-29 | 中天建设集团有限公司 | Lifting tool type hanger frame for prefabricated parts |
| CN203474241U (en) * | 2013-10-10 | 2014-03-12 | 中国十九冶集团有限公司 | Balanced hoisting beam |
| CN203959640U (en) * | 2014-05-27 | 2014-11-26 | 北京航天发射技术研究所 | Oblique pull suspension cable type frame lifting appliance |
-
2015
- 2015-11-26 CN CN201510844527.7A patent/CN105329767B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4074519A (en) * | 1977-03-31 | 1978-02-21 | American Hoist & Derrick Company | Swivel shackle |
| DE29611837U1 (en) * | 1996-07-06 | 1996-10-31 | HM-Betonfertigteilwerk Hans Mauthe GmbH & Co KG, 88319 Aitrach | Device for moving basement window walls |
| DE20021334U1 (en) * | 2000-12-16 | 2001-03-22 | J. D. Theile GmbH & Co KG, 58239 Schwerte | Stop ring |
| JP2008068973A (en) * | 2006-09-13 | 2008-03-27 | Daiwa House Ind Co Ltd | Hanging tool |
| CN103434922A (en) * | 2013-09-12 | 2013-12-11 | 中国海洋石油总公司 | Lifting point of all-rotation shell flange |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105329767A (en) | 2016-02-17 |
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