CN103630442B - A kind of aircraft structure strength trial loads lever - Google Patents
A kind of aircraft structure strength trial loads lever Download PDFInfo
- Publication number
- CN103630442B CN103630442B CN201310652039.7A CN201310652039A CN103630442B CN 103630442 B CN103630442 B CN 103630442B CN 201310652039 A CN201310652039 A CN 201310652039A CN 103630442 B CN103630442 B CN 103630442B
- Authority
- CN
- China
- Prior art keywords
- channel
- section steel
- cable wire
- lever
- bolt
- 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
Landscapes
- Connection Of Plates (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to aircraft structure strength trial and add carrier technology, be specifically related to a kind of loading lever fixing for aircraft structure strength trial gap. Described aircraft structure strength trial loads lever and comprises two back ofs the body to the channel-section steel arranged, two channel-section steel bottom centerline are provided with some joint bolts, and channel-section steel two ends deviation position of center line is respectively arranged with tack bolt, thus fix the gap between two channel-section steels. The present invention secures the gap between lever two channel-section steels, avoids connection cable wire and is subject to extruding the unbalance stress caused inside channel-section steel; And cable wire position has been limited by tack bolt, ensure that connecting cable wire is fixed on joint bolt, avoid connecting cable wire disengaging joint bolt and be suspended on channel-section steel, lever stress is accurately transmitted by joint bolt; In addition, connect cable wire turning radius by increasing lining on joint bolt to increase, avoid cable wire be subject to curved, cut load, there is processing quick, it may also be useful to easy, practical, with low cost advantage.
Description
Technical field
The invention belongs to aircraft structure strength trial and add carrier technology, be specifically related to a kind of loading lever fixing for aircraft structure strength trial gap.
Background technology
In the quiet power/Stromeyer test of current full-scale aircraft structure, it is main loading form that adhesive tape loads regulations and parameters system. Loading lever and loading lever, loading between regulations and parameters and adhesive tape, usually adopting web member or connect cable wire connection.
Load lever and it be generally two panels channel-section steel, 3 joint bolt array configurations, when adopting connection cable wire to be connected with other regulations and parameters, adhesive tape, in test loading procedure, there will be following situation:
A) channel-section steel gap is uncertain, changes by power change with regulations and parameters;
B) channel-section steel gap is crossed hour, connects cable wire and is squeezed, causes and connect cable wire unbalance stress, connects the risk that cable wire has premature degradation when regulations and parameters bears high-load;
C) during channel-section steel excessive clearance, lever two ends connect cable wire by power have not in a plane situation occur, make lever bear moment of torsion, when regulations and parameters bears high-load easily occur torsion unstability situation;
D) when channel-section steel spacing is excessive, cannot retraining connection cable wire, cable wire easily departs from channel-section steel gap, occur hanging the phenomenon in lever outer, when testing, cause lever-loading inaccurate, and there will be the abnormal voice caused because of rope slip, it is necessary to carry out troubleshooting operation in eminence band load;
E) joint bolt diameter is crossed hour, connects cable wire turning radius and can not meet service requirements, cable wire by curved, cut load, supporting capacity reduces, and has the risk of premature degradation.
These situations meeting interference test process, causes test and loads risk, increases maintenance workload and the working aloft danger of process of the test, load applying also can be caused inaccurate, impact test loading accuracy, and then affect test-results.
Summary of the invention
The object of the present invention: in order to solve the problem, the present invention provides a kind of loading lever fixing for aircraft structure strength trial gap.
The technical scheme of the present invention: a kind of aircraft structure strength trial loads lever, it is characterized in that, comprise two back ofs the body to the channel-section steel arranged, two channel-section steel bottom centerline are arranged and uses some joint bolts, and channel-section steel two ends deviation position of center line is respectively arranged with tack bolt, thus fix the gap between two channel-section steels.
It is provided with mating sleeves between this tack bolt and channel-section steel.
This joint bolt is provided with lining, and the diameter of lining is greater than the twice for loading the rope diameter that lever connects.
The technique effect of the present invention is: the present invention effectively secures lever gap, avoids connecting cable wire and is subject to extruding inside channel-section steel causing unbalance stress; Ensure that connecting cable wire is fixed on joint bolt, avoid connecting cable wire disengaging joint bolt and be suspended to channel-section steel outer, ensure that lever stress is accurately transmitted by joint bolt; By increase on joint bolt lining with increase connect cable wire turning radius, avoid cable wire be subject to curved, cut load; Processing is quick, it may also be useful to easy, practical, with low cost.
Accompanying drawing explanation
Fig. 1 is the structural representation that aircraft structure strength trial of the present invention loads lever;
The A-A that Fig. 2 is Fig. 1 cuts open figure;
The B-B that Fig. 3 is Fig. 1 cuts open figure,
Wherein, 1-channel-section steel, 2-joint bolt, 3-tack bolt, 4-joint bolt lining, 5-tack bolt lining.
Embodiment
It is further described below in conjunction with drawings and Examples:
Please refer to Fig. 1, Fig. 2, Fig. 3, wherein, Fig. 1 is the structural representation that aircraft structure strength trial of the present invention loads lever, and the A-A that Fig. 2 is Fig. 1 cuts open figure, and the B-B that Fig. 3 is Fig. 1 cuts open figure. The present invention loads lever and is made up of 2 channel-section steels, 3 joint bolts (containing pad, nut), 3 joint bolt linings, 2 tack bolts (containing nut) and 2 tack bolt linings. Wherein, channel-section steel bears bending load. 3 joint bolts are arranged on the bottom centerline of 2 channel-section steels, for the connection connecting channel-section steel and load between lever and other loading lever, and carry cable wire and connect the load transmitted. Described joint bolt lining is arranged between joint bolt and channel-section steel, increases the relative diameter of joint bolt, thus increases turning radius when cable wire uses so that it is meet cable wire service requirements. 2 tack bolts are separately positioned on the position of channel-section steel two ends deviation medullary ray, cable wire position is limited, ensure that connecting cable wire is fixed on joint bolt, avoid connecting cable wire disengaging joint bolt and be suspended on channel-section steel, lever stress is accurately transmitted by joint bolt. Described tack bolt lining is arranged between tack bolt and channel-section steel, liner sleeve length is slightly larger than rope diameter, thus fixing channel-section steel gap, avoid occurring that channel-section steel gap is crossed and hour connect a cable wire when being subject to extruding the unbalance stress caused or channel-section steel excessive clearance inside channel-section steel, lever two ends connect cable wire does not make lever bear moment of torsion by power in a plane, occurs when regulations and parameters bears high load reversing unstability situation.
The loading lever that the gap become by above component combination is fixing, tack bolt defines the position connecting cable wire, connection cable wire is made to be fixed on correct position, tack bolt mating sleeves secures channel-section steel gap, avoid cable wire and bear torsion problem by channel-section steel extruding or cable wire by the lever that power does not cause in same plane, ensureing that loading lever is transmitted by joint bolt by shearing, by loading, lever itself transmits moment of flexure, and dynamic changes process is accurate. Joint bolt mating sleeves diameter is greater than 2 times of rope diameter, ensures that cable wire turning radius meets service requirements. In strength trial, the connection cable wire unbalance stress, shearing carrying, abnormal voice and the lever that occur when the loading lever that gap is fixed avoids carrying reverse the problems such as unstability, failure rate is low, reliability height, it is possible to effectively complete the effect of load distribution and transmission.
Claims (1)
1. an aircraft structure strength trial loads lever, it is characterized in that, comprise two back ofs the body to the channel-section steel arranged, two channel-section steel bottom centerline are provided with some joint bolts, and channel-section steel two ends deviation position of center line is respectively arranged with tack bolt, thus fix the gap between two channel-section steels, it is provided with length between this tack bolt and channel-section steel and it is greater than rope diameter, in order to the tack bolt lining in fixing channel-section steel gap, this joint bolt is provided with the lining of the relative diameter for increasing joint bolt, and the diameter of lining is greater than the twice for loading the rope diameter that lever connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310652039.7A CN103630442B (en) | 2013-12-04 | 2013-12-04 | A kind of aircraft structure strength trial loads lever |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310652039.7A CN103630442B (en) | 2013-12-04 | 2013-12-04 | A kind of aircraft structure strength trial loads lever |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103630442A CN103630442A (en) | 2014-03-12 |
| CN103630442B true CN103630442B (en) | 2016-06-01 |
Family
ID=50211721
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310652039.7A Active CN103630442B (en) | 2013-12-04 | 2013-12-04 | A kind of aircraft structure strength trial loads lever |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103630442B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103954502A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Fatigue test loading mechanism with tensile pressing cushion |
| CN105606452B (en) * | 2016-03-04 | 2018-02-09 | 国机集团北京飞机强度研究所有限公司 | The power rod member outfield load calibration of aircraft two/strength test portable unit |
| CN106768926A (en) * | 2016-11-30 | 2017-05-31 | 江西洪都航空工业集团有限责任公司 | A kind of clamp plate type experiment loading unit |
| CN109703781B (en) * | 2018-12-07 | 2022-04-19 | 中国飞机强度研究所 | Calculation design method of lever system |
| CN111301707B (en) * | 2020-03-02 | 2021-10-01 | 中国飞机强度研究所 | Aircraft structural strength ground test secondary loading structure |
| CN111951645A (en) * | 2020-07-24 | 2020-11-17 | 淮阴工学院 | Flexural bolt group mechanics model teaching aid |
| CN113029799B (en) * | 2021-03-31 | 2022-07-29 | 武汉理工大学 | Detachable surface load loading device |
| CN113405902B (en) * | 2021-05-19 | 2024-05-24 | 中航西安飞机工业集团股份有限公司 | Loading lever and loading method for strength test |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201165452Y (en) * | 2007-12-07 | 2008-12-17 | 中国石化集团胜利石油管理局渤海钻井总公司 | Novel overhead traveling crane anti-groove jumping rope stopping device |
| CN201419970Y (en) * | 2009-04-02 | 2010-03-10 | 天津港第五港埠有限公司 | Billet anti-overlapping hanger |
| CN102013645A (en) * | 2010-11-18 | 2011-04-13 | 重庆市电力公司江北供电局 | Hauling cable positioning labor-saving guide wheel |
-
2013
- 2013-12-04 CN CN201310652039.7A patent/CN103630442B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201165452Y (en) * | 2007-12-07 | 2008-12-17 | 中国石化集团胜利石油管理局渤海钻井总公司 | Novel overhead traveling crane anti-groove jumping rope stopping device |
| CN201419970Y (en) * | 2009-04-02 | 2010-03-10 | 天津港第五港埠有限公司 | Billet anti-overlapping hanger |
| CN102013645A (en) * | 2010-11-18 | 2011-04-13 | 重庆市电力公司江北供电局 | Hauling cable positioning labor-saving guide wheel |
Non-Patent Citations (1)
| Title |
|---|
| 基于CATIA的飞机结构试验加载杠杆系统参数化建模方法;巴塔西等;《实验室研究与探索》;20120215;第31卷(第2期);图2 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103630442A (en) | 2014-03-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103630442B (en) | A kind of aircraft structure strength trial loads lever | |
| CN102092648B (en) | Tower crane and balance detection system thereof | |
| CN203889083U (en) | Adhesive tape loading rod fixing device for adhesive tape and lever loading system | |
| CN203798519U (en) | Large-scale control surface transmission mechanism vibration impact test system | |
| CN103482373B (en) | Leveling style large span gate-type scraper | |
| CN203275107U (en) | Structural-component static strength test load transmission apparatus | |
| CN106229913A (en) | A kind of detachable cable protection tubular construction | |
| CN207229617U (en) | Pin type safety coupling | |
| CN203529850U (en) | Braking device used for winch and dynamic compactor | |
| CN203230790U (en) | Connecting assembly | |
| CN203601560U (en) | Connecting structure of wing flap torsion tube in airplane | |
| CN204076155U (en) | A kind of special tooling for wedge ring dismounting | |
| CN107512399B (en) | Box-shaped beam type engine main mounting joint | |
| CN203239787U (en) | Flexible coupler | |
| CN208311332U (en) | A kind of spring column pin braked wheel gear coupling | |
| CN203641300U (en) | Winding drum hub and shaft flange disc structure | |
| CN204704282U (en) | Novel main shaft head sheave encoder coupler | |
| CN102236328A (en) | Wharf centralized monitoring and management system | |
| CN104443401A (en) | Novel engine installing structure | |
| CN103698069A (en) | Method for detecting tensile force of ratchet fastener | |
| CN211371001U (en) | Bidirectional freedom degree lining | |
| CN104696659A (en) | Bellows joint | |
| CN201376859Y (en) | Brake speed-testing transmission structure for hoisting drum of crane | |
| CN204096844U (en) | Trailing cable embedding video line structure elevator | |
| CN204849590U (en) | Cable road bridge wire rope cable body coupling ground tackle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 |