CN203365167U - Jack loading structure with loading connector for aircraft jack static test - Google Patents
Jack loading structure with loading connector for aircraft jack static test Download PDFInfo
- Publication number
- CN203365167U CN203365167U CN 201320481009 CN201320481009U CN203365167U CN 203365167 U CN203365167 U CN 203365167U CN 201320481009 CN201320481009 CN 201320481009 CN 201320481009 U CN201320481009 U CN 201320481009U CN 203365167 U CN203365167 U CN 203365167U
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- loading
- jack
- aircraft
- static test
- connector
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Abstract
The utility model relates to a jack loading structure with a loading connector for an aircraft jack static test, and belongs to the technical field of the aircraft static test. The jack loading structure with the loading connector for the aircraft jack static test includes an aircraft body structure, a jack support lacuna under the aircraft body structure, and the loading connector assembled inside the jack support lacuna; and one end of the loading connector is a conical structure, and the other end of the loading connector is a cylindrical structure. The jack loading structure with the loading connector for the aircraft jack static test well solves the loading problem of the lacunae-type jack support in the static test, and is simple in operation; and the certain popularization value for the military aircraft and the civil aircraft is realized.
Description
Technical field
The utility model relates to and a kind ofly for having of aircraft lifting jack slow test, loads joint lifting jack loading structure, belongs to the technical field of aircraft slow test.
Background technology
Aircraft is when carrying out ground-mounted, repair and maintenance and horizontal survey, need to adopt the jack pair aircraft to be supported, now aircraft body structure bears larger centre-point load, therefore need to be on the basis of carrying out the theoretical strength check, by slow test, near structure jacking bracket is examined, with checking, whether met the static strength requirement.
Dopey is designed to jacking bracket independently joint type part usually, and is arranged on housing construction by web member, and this structure can directly be loaded by jacking bracket when slow test.And high-speed aircraft is in order to meet pneumatic design and stealthy requirement, need to guarantee the smooth of housing construction surface, therefore usually at housing construction (beam, rib etc.), above design lacuna as jacking bracket, can't directly be loaded when this version causes slow test.
Summary of the invention
The utility model is in order to overcome above-mentioned defect, and purpose is to provide a kind of simple, effective slow test loading method, and what meet the slow test requirement has the joint of a loading lifting jack loading structure for the slow test of aircraft lifting jack.
The utility model in order to achieve the above object, adopts following technical scheme:
A kind ofly for having of aircraft lifting jack slow test, load joint lifting jack loading structure, it comprises housing construction, and the jacking bracket lacuna under housing construction is equipped with the loading joint in the jacking bracket lacuna, described loading joint one end is cone structure, and the other end is cylindrical structure.
When carrying out slow test, the load of the vertical horizontal basis plane direction of aircraft acts on and loads joint cylinder end face by load maintainer, and horizontal direction load acts on the loading joint by cable wire.
Loading joint one end is cone structure, with for the lacuna laminating, the other end is cylindrical structure, for loading.
The beneficial effects of the utility model:
The fine loading problem of jacking bracket in slow test that has solved the lacuna form of the utility model, simple to operate, military secret, civil aircraft are all existed to certain promotional value.
The accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is jacking bracket lacuna structure diagram.
Embodiment
Below in conjunction with 1,2 pairs of the utility model of accompanying drawing, be elaborated:
A kind ofly for having of aircraft lifting jack slow test, load joint lifting jack loading structure
, it comprises housing construction 1, and the jacking bracket lacuna 2 under housing construction 1 is equipped with and loads joint 3 in jacking bracket lacuna 2, and described loading joint 3 one ends are cone structure, and the other end is cylindrical structure.
Load joint, guarantee joint circular conical surface and the laminating of bearing lacuna, when test loads, vertical loads 4 and horizontal direction load 5 all act on and load on joint.
Claims (1)
1. one kind loads joint lifting jack loading structure for having of aircraft lifting jack slow test
It comprises housing construction (1), and the jacking bracket lacuna (2) under housing construction (1) is characterized in that: be equipped with in jacking bracket lacuna (2) and load joint (3), described loading joint (3) one ends are cone structure, and the other end is cylindrical structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320481009 CN203365167U (en) | 2013-08-08 | 2013-08-08 | Jack loading structure with loading connector for aircraft jack static test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320481009 CN203365167U (en) | 2013-08-08 | 2013-08-08 | Jack loading structure with loading connector for aircraft jack static test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203365167U true CN203365167U (en) | 2013-12-25 |
Family
ID=49812913
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320481009 Expired - Lifetime CN203365167U (en) | 2013-08-08 | 2013-08-08 | Jack loading structure with loading connector for aircraft jack static test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203365167U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109665A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Multi-functional wing jack pit |
| CN109866940A (en) * | 2017-12-01 | 2019-06-11 | 中国飞机强度研究所 | A kind of both sides' steel carrying transition beam and manufacturing method |
-
2013
- 2013-08-08 CN CN 201320481009 patent/CN203365167U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109665A (en) * | 2015-09-24 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Multi-functional wing jack pit |
| CN105109665B (en) * | 2015-09-24 | 2017-11-14 | 江西洪都航空工业集团有限责任公司 | A kind of multi-functional wing jack nest |
| CN109866940A (en) * | 2017-12-01 | 2019-06-11 | 中国飞机强度研究所 | A kind of both sides' steel carrying transition beam and manufacturing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131225 |