CN102923558B - Combined airplane lifting lug - Google Patents
Combined airplane lifting lug Download PDFInfo
- Publication number
- CN102923558B CN102923558B CN201210431056.3A CN201210431056A CN102923558B CN 102923558 B CN102923558 B CN 102923558B CN 201210431056 A CN201210431056 A CN 201210431056A CN 102923558 B CN102923558 B CN 102923558B
- Authority
- CN
- China
- Prior art keywords
- attachment lug
- tie bolt
- suspension centre
- hanger
- lug
- 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.)
- Active
Links
Abstract
The invention discloses a combined airplane lifting lug. A first connecting bolt (5) penetrates through the upper portion of a first connecting lug sheet (7) and is fixed by a first nut (6), the first connecting lug sheet (7) and a joint bearing (3) are assembled in an interference fit mode, a second connecting bolt (1) is used for connecting a second connecting lug sheet (8) to the first connecting lug sheet (7), the first connecting lug sheet (7) is fixed to the middle of the second connecting bolt (1) by a stopping sleeve (2) and is locked by a second nut (4), a lifting point connecting bolt (9) penetrates through the bottom of the second connecting lug sheet (8), and the second connecting lug sheet (8) is fixed to a machine body lifting point. The lifting lug has a long service life and can be fixed to two sides of a machine body respectively. The interference of the lifting lug and the machine body is avoided, and the action angle range that the lifting lug bears a sling is wide.
Description
Technical field
The present invention relates to a kind of aircraft hanger, when connection when can realize aircraft hoisting between hoist cable and fuselage suspension centre or parachute-opening, the connection between fuselage suspension centre locked by umbrella.
Background technology
Airframe unavoidably needs lifting in the process of assembling and transport; in order to lift aircraft when assembling or transport; and for releasing a parachute when preventing unexpected generation from opening umbrella or landing in flight course, require to use hanger hoist cable or umbrella lock to be connected with fuselage suspension centre.There are 4 requirements to hanger: 1) connect reliable, most importantly ensure that power transmission is reliable; 2) mounting or dismounting are convenient, rapid; 3) interchangeability and manufacturability good; 4) life-span is longer, need not often change.
The hanger often used at present is circular ring type hanger, and the mounting or dismounting of circular ring type hanger are convenient, and load-carrying capacity is strong.But it requires that hanger must be installed vertically on workpiece planarization, and faying face needs smooth, and hanger and suspended object need in conjunction with tight.This just makes circular ring type hanger can only be installed on plane or cambered surface approximate radial direction, as annular arrangement hanger is installed in cambered surface near-tangential direction, hanger its annulus when screwing in cambered surface that is easy and suspended object interferes, thus make hanger and suspended object in conjunction with closely, its load-carrying capacity and service life can not be had a strong impact on.Zip need be adjusted to the draw direction of hanger by hoist cable when acting on circular ring type hanger, otherwise hanger just can bear the effect of larger torsion.
For making body in hoisting process more stable, need both sides aircraft suspension centre being arranged into as far as possible fuselage, and fuselage cross-section is generally circle, when easily occurring that hanger rotates when hanger and fuselage suspension centre are spirally connected and the body phenomenon of interfering, thus make ear stud root can not combine closely with suspension centre top, affect the load-carrying capacity of hanger, make hanger and suspension centre tie bolt easily occur the phenomenon bent, reduce hanger service life; Common circular ring type hanger also requires that hoist cable direction of pull is as far as possible along ear stud draw direction, otherwise can occur twisting resistance on annular arrangement hanger, and long-term use like this can reduce its service life.
Summary of the invention
Technical matters to be solved by this invention is to provide a kind of composite aircraft hanger of long service life, can be arranged in fuselage both sides, avoids the interference of hanger and body, and it is large that hanger can hold hoist cable effect angular range.
The present invention includes following technical scheme:
A kind of composite aircraft hanger, comprises the first tie bolt, the first nut, the first attachment lug, the second tie bolt, the second nut, two stop sleeves, the second attachment lug, oscillating bearing, suspension centre tie bolts; First tie bolt passes the top of the first attachment lug, and by the first nut locking; Described first attachment lug and oscillating bearing pass through interference fit; Described second tie bolt is for realizing the connection of the second attachment lug and the first attachment lug; First attachment lug is fixed on the centre of the second tie bolt by described stop sleeve, by the second nut locking; Second attachment lug, through the bottom of the second attachment lug, is fixed on fuselage suspension centre by described suspension centre tie bolt.
The through hole passed for suspension centre tie bolt is provided with bottom described second attachment lug; Second attachment lug top is provided with the through hole passed for the second tie bolt.
Described second attachment lug top is that ears hold and cut auricle.
The bottom of described second attachment lug is circular platform type.
Described first attachment lug top is provided with the through hole passed for the first tie bolt, and bottom is provided with the through hole for assembling oscillating bearing.
Described first attachment lug top is that ears hold and cut auricle.
The present invention's advantage compared with prior art:
(1) hanger of the present invention adopts the piece combined carrying of ears, fast easy to assembly, fuselage suspension centre can be arranged in fuselage both sides as far as possible, and can effectively avoid hanger and body interference.
(2) hanger of the present invention can hold hoist cable effect angular range greatly, does not require that hoist cable is along tie bolt direction of pull; Hanger load path is reliably clear, and each part stress form is single, and the life-span is long.
(3) the present invention has the large feature of loading angle that common annular arrangement hanger has, and what also have that common annular arrangement hanger do not have installs in fuselage cylindrical cross-section side, the advantage that when hoist cable angle is large, hanger internal torsion power is little.
Accompanying drawing explanation
Fig. 1 is split shackle assembly drowing of the present invention, and wherein Fig. 1 a is front view, and Fig. 1 b is lateral plan;
Fig. 2 is split shackle part sectional view of the present invention;
Fig. 3 is for be installed on schematic diagram on fuselage by split shackle of the present invention;
Fig. 4 is the enlarged diagram be installed on by split shackle of the present invention on fuselage.
Detailed description of the invention
As shown in Figure 1-2, composite aircraft hanger of the present invention comprises the first tie bolt 5, first nut 6, first attachment lug 7, second tie bolt 1, second nut 4, two stop sleeve 2, second attachment lugs 8, oscillating bearing 3, suspension centre tie bolts 9.First attachment lug 7 top adopts ears to hold and cuts auricle, and the first attachment lug 7 top is provided with the through hole passed for the first tie bolt 5; The through hole for assembling oscillating bearing 3 is provided with bottom first attachment lug 7.The through hole passed for suspension centre tie bolt 9 is provided with bottom second attachment lug 8; Second attachment lug 8 top adopts ears to hold and cuts auricle, and the second attachment lug 8 top is provided with the through hole passed for the second tie bolt 1.The connection of the second attachment lug 8 and the first attachment lug 7 is realized by the second tie bolt 1.First tie bolt 5 is connected with hoist cable, is locked by nut 6, and can be got by the tolerance on fit that the pulling force of hoist cable passes between the first attachment lug 7, first attachment lug 7 and the first tie bolt 5 with shearing form
bottom first attachment lug 7, oscillating bearing 3 is installed, ensure that the first attachment lug 7 can be followed hoist cable and be carried out big angle rotary, stressed on attachment lug is shearing all the time and does not have twisting resistance, and the tolerance on fit between the first attachment lug 7 and oscillating bearing 3 can be got
the first attachment lug 7 installing oscillating bearing 3 is positioned in the middle part of the second tie bolt 1 by two stop sleeves 2, prevent hoist cable angle comparatively large and the first attachment lug 7 is slid axially along the second tie bolt 1, the tolerance on fit between the second tie bolt 1 and stop sleeve 2 can be got
tolerance on fit between second tie bolt 1 and oscillating bearing 3 can be got
dynamic changes process can get to the tolerance on fit between the second attachment lug 8, second tie bolt 1 and the second attachment lug 8 by the form of shearing by the second tie bolt 1
be preferably circular platform type bottom second attachment lug 8, be close to fuselage suspension centre bottom the second attachment lug 8, by suspension centre tie bolt 9, second attachment lug 8 and fuselage suspension centre are compressed, and by the form of pulling force by dynamic changes process to fuselage suspension centre.By suspension centre tie bolt 9, second attachment lug 8 and fuselage suspension centre are compressed, to make the moment of flexure bottom the second attachment lug 8 in round platform and suspension centre tie bolt 9 shared hoisting process, greatly reduce the probability that suspension centre tie bolt 9 bends.
The setting-up procedure of composite aircraft hanger of the present invention is: first oscillating bearing 3 is pressed into the first attachment lug 7, guarantees that it is as a whole; Second step passes through suspension centre tie bolt 9 by fastening with fuselage suspension centre for the second attachment lug 8; 3rd step by the second tie bolt 1 and nut 4 by fastening for stop sleeve 2, first attachment lug 7, second attachment lug 8; Hoist cable is connected with hanger with nut 6 finally by the first tie bolt 5.
As shown in Figure 3,4, composite aircraft hanger of the present invention is arranged on airframe suspension centre 10.Airframe suspension centre 10 is positioned at fuselage 12 both sides.The situation of fuselage both sides is arranged in for fuselage suspension centre, round platform diameter bottom the second attachment lug 8 is determined according to hoisting point position, guarantee to fit closely with fuselage suspension centre 10 bottom the second attachment lug 8 round platform, frustum cone height is not to be as the criterion with body interference, by suspension centre tie bolt 9, second attachment lug 8 and fuselage suspension centre 10 are compressed, form clamping plane 11.Guarantee a suspension centre tie bolt 9 almost tension power effect; Top first attachment lug 7 because hoist cable pulling force with hoist cable direction transformation angle, and can be passed to bottom second tie bolt 1 and the second attachment lug 8 with shearing form by oscillating bearing, and passes through suspension centre tie bolt by pull transfer to fuselage suspension centre.
Hanger adopts the piece combined carrying of ears, the suspension centre tie bolt 9 be connected with fuselage suspension centre only need be rotated when being arranged on fuselage suspension centre by hanger, and do not need to rotate whole hanger, reduce radius of rotation, avoid auricle and rotate the generation with body interference phenomenon.The invention solves the problem that fuselage cylindrical cross-section radius is less and hope lifting span is large, both ensured that load path was clear, reliable, ensure that again screwing in thread root is close to body suspension centre, bolt moment of flexure is less, extends the service life of hanger.The use of oscillating bearing 3 increases hanger stand under load angle, when hoist cable is not when acting on hanger along draw direction, top ears attachment lug can rotate with hoist cable, makes the pull transfer of hoist cable to split shackle also only has pulling force and does not have twisting resistance, thus makes working process safer; Split shackle flexible rotation, bear hoist cable pulling force angle comparatively greatly, stress form is simple, and the hanger life-span is longer.
Claims (1)
1. a composite aircraft hanger, is characterized in that: comprise the first tie bolt (5), the first nut (6), the first attachment lug (7), the second tie bolt (1), the second nut (4), two stop sleeves (2), the second attachment lug (8), oscillating bearing (3) and suspension centre tie bolts (9);
Described first attachment lug (7) top is that ears hold and cut auricle; Described first attachment lug (7) top is provided with the through hole passed for the first tie bolt (5), and bottom is provided with the through hole for assembling oscillating bearing (3); First tie bolt (5) through the top of the first attachment lug (7), and is locked by the first nut (6); Described first attachment lug (7) and oscillating bearing (3) pass through interference fit; Described second tie bolt (1) is for realizing the connection of the second attachment lug (8) and the first attachment lug (7); First attachment lug (7) is fixed on the centre of the second tie bolt (1) by described stop sleeve (2), is locked by the second nut (4);
Described second attachment lug (8) top is that ears hold and cut auricle, and the bottom of described second attachment lug (8) is the frustum of a cone; The frustum of a cone of described second attachment lug (8) is provided with the through hole passed for suspension centre tie bolt (9); Second attachment lug (8) top is provided with the through hole passed for the second tie bolt (1); Described suspension centre tie bolt (9) is through the through hole on the frustum of a cone of the second attachment lug (8), second attachment lug (8) is fixed on fuselage suspension centre (10), the bottom surface of the frustum of a cone of the second attachment lug (8) and fuselage suspension centre (10) is close to and forms clamping plane (11);
Fuselage suspension centre (10) is positioned at fuselage (12) both sides, and the first tie bolt (5) is connected with hoist cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210431056.3A CN102923558B (en) | 2012-10-31 | 2012-10-31 | Combined airplane lifting lug |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210431056.3A CN102923558B (en) | 2012-10-31 | 2012-10-31 | Combined airplane lifting lug |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102923558A CN102923558A (en) | 2013-02-13 |
| CN102923558B true CN102923558B (en) | 2014-12-31 |
Family
ID=47638523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210431056.3A Active CN102923558B (en) | 2012-10-31 | 2012-10-31 | Combined airplane lifting lug |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102923558B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112758331B (en) * | 2020-12-29 | 2023-07-21 | 中国航空工业集团公司西安飞机设计研究所 | Front lifting point structure of airplane |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB492127A (en) * | 1937-09-22 | 1938-09-15 | Hubert Scott Paine | Improvements in or relating to lifting and lowering slings |
| CN1569603A (en) * | 2003-07-14 | 2005-01-26 | 巨力集团有限公司 | High-strength shackle |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4403785A1 (en) * | 1993-10-25 | 1995-08-10 | Rud Ketten Rieger & Dietz | Eye bolt |
| JPH08143267A (en) * | 1994-11-25 | 1996-06-04 | Jgc Corp | Skid with hoist lug for long large material and long large material carrying method using it |
| JP3176564B2 (en) * | 1997-06-05 | 2001-06-18 | 株式会社荏原製作所 | Submersible motor pump |
| JP3232061B2 (en) * | 1999-03-26 | 2001-11-26 | 株式会社協和ロープ | Synthetic resin coated wire tensioner |
| JP2010048377A (en) * | 2008-08-22 | 2010-03-04 | Mitaka Koki Co Ltd | Opening/closing type eye bolt |
| US8256981B2 (en) * | 2009-09-01 | 2012-09-04 | Delta Rigging & Tools, Inc. | Thimble with element retaining feature |
-
2012
- 2012-10-31 CN CN201210431056.3A patent/CN102923558B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB492127A (en) * | 1937-09-22 | 1938-09-15 | Hubert Scott Paine | Improvements in or relating to lifting and lowering slings |
| CN1569603A (en) * | 2003-07-14 | 2005-01-26 | 巨力集团有限公司 | High-strength shackle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102923558A (en) | 2013-02-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9068555B2 (en) | Element for lifting the blade and method followed | |
| EP2661550B1 (en) | Wind turbine blade bearing removal apparatus and method | |
| CN104691769B (en) | Novel unmanned aerial vehicle airborne pod hanging frame | |
| CN107356164B (en) | A kind of airvane drive mechanism | |
| CN102923558B (en) | Combined airplane lifting lug | |
| CN106429827A (en) | Rotor overturning and hoisting device | |
| CN110036198A (en) | rotor blade assembly | |
| CN101665152B (en) | Quick detachable combined cover cap capable of bearing stress | |
| CN106838123B (en) | Mooring rigging switching device | |
| CN208666888U (en) | Double ring type rotating hoisting ring | |
| CN202048082U (en) | Load balancing type tire bolt component | |
| CN216272659U (en) | Main transformer sleeve hoisting balancing tool | |
| CN112623182B (en) | Wing body connection structure and contain wing body connection structure's unmanned aerial vehicle | |
| CN103363083A (en) | Planetary frame for large wind power gear box | |
| CN212127273U (en) | Hoisting accessory of large-scale cylindric spare part | |
| CN201538642U (en) | Lifting clasp for heavy-duty post | |
| CN219860061U (en) | Lifting tool and lifting equipment | |
| CN205401376U (en) | Aircraft cockpit lid hanger bolt | |
| CN218670415U (en) | Safety hook with warning function | |
| CN214243366U (en) | Lightweight tail rope suspension device for lifting container | |
| CN205533595U (en) | Arm -tie pivort fixation device | |
| CN205820717U (en) | A kind of anti-rolling wheel support of pin type | |
| CN211225984U (en) | Unmanned aerial vehicle hoist and mount connection structure | |
| CN202030436U (en) | Anti-rotation mechanism for lifting appliance | |
| CN204533134U (en) | A kind of bow shackle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170306 Address after: 065500 Guan Industrial Park, Langfang, Hebei Patentee after: Rainbow UAV Technology Co., Ltd. Address before: 100074 Beijing, Fengtai District Yungang West Road, No. 17 Patentee before: China Aerospace Aerodynamic Technology Institute |