CN105021414B - Movable wing following loading device - Google Patents
Movable wing following loading device Download PDFInfo
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- CN105021414B CN105021414B CN201410178574.8A CN201410178574A CN105021414B CN 105021414 B CN105021414 B CN 105021414B CN 201410178574 A CN201410178574 A CN 201410178574A CN 105021414 B CN105021414 B CN 105021414B
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- pressurized strut
- movable wing
- rocking arm
- hinged
- supporting section
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Abstract
The invention belongs to plane airfoil loading technique, and in particular to a kind of movable wing following loading device.The movable wing following loading device includes position control pressurized strut base, position control pressurized strut, rocking arm framework, rocking arm frame base and loading pressurized strut.The rocking arm framework includes loaded segment, linkage section, supporting section.Wherein, loaded segment and supporting section are connected to linkage section both sides, the supporting section at the top of rocking arm frame base with being hinged, the joint portion of linkage section and supporting section at the top of the control pressurized strut of position with being hinged, on the be hinged control pressurized strut base in place in position control pressurized strut bottom, loading pressurized strut one end is hinged with loaded segment, other end joint test part.The present invention can realize that movable wing test load remains the following loading of certain angle with the movable wing moved, and more real simulation, an approach for checking test are opened for the static(al) of similar shape movable wing structure, fatigue test.
Description
Technical field
The invention belongs to plane airfoil loading technique, and in particular to a kind of movable wing following loading device.
Background technology
Typically for aircraft movable wing static(al), fatigue test, substantially enter in the case where movable wing remains static
Capable, as requirement of the continuous development of experimental technique to experiment also increasingly improves, it is proposed that in test movable wing moves
While experiment loading unit carry out coordinate following loading requirement.
Following loading problem also once occurred in slow test and function test, and conventional solution method is all by more
The mode of individual load vector synthesis realizes, this method due to its for number of devices and equipment install requirement of control compared with
Height, its application is greatly limited, is only used for bench-scale testing.
The content of the invention
The purpose of the present invention is：The present invention provides one kind using displacement as controlled quentity controlled variable, can realize the big angle of loading equipemtn
Displacement following loading, the following loading device of real simulation movable wing loading conditions.
The technical scheme is that：A kind of movable wing following loading device, it includes position control pressurized strut base, position control
Pressurized strut, rocking arm framework, rocking arm frame base and loading pressurized strut, the rocking arm framework include loaded segment, linkage section, support
Section, wherein, loaded segment and supporting section are connected to linkage section both sides, and the supporting section and rocking arm frame base top are be hinged,
The joint portion of linkage section and supporting section is be hinged at the top of the control pressurized strut of position, the be hinged control pressurized strut base in place in position control pressurized strut bottom
On, loading pressurized strut one end is hinged with loaded segment, other end joint test part.
The angle of cut between loaded segment and supporting section and linkage section is all higher than 90 °.
The joint portion of linkage section and supporting section is provided with monaural with position control pressurized strut junction and embeds oscillating bearing.
The solution have the advantages that：
The folding and unfolding that the present invention controls pressurized strut by the position for determining to be arranged on following loading device instructs, and utilizes existing examination
Loading coordinated control system driving position control pressurized strut stretching motion is tested, driving rocking arm framework follows movable wing to rotate, realizes peace
Loading pressurized strut and the coordinated movement of various economic factors of movable wing on rocking arm framework, realize movable wing test load and the work of motion
Dynamic aerofoil remains the following loading of certain angle.Solving conventional test method can only be in the state of movable wing fixation
The problem of being loaded, more real simulation, a checking are opened for the static(al) of similar shape movable wing structure, fatigue test
The approach of experiment.
Brief description of the drawings
Fig. 1 is the structural representation of movable wing following loading device of the present invention；
Wherein, 1- positions control pressurized strut base, the control pressurized strut of 2- positions, 3- rocking arms framework, 4- rocking arms frame base, 5- loadings are made
Dynamic cylinder, 6- testpieces (movable wing).
Embodiment
The present invention will be further described with reference to the accompanying drawings and examples：
Referring to Fig. 1, it is the structural representation of movable wing following loading device of the present invention.The movable wing is servo-actuated
Loading device, it includes position control pressurized strut base, position control pressurized strut, rocking arm framework, rocking arm frame base and loading pressurized strut, institute
Stating rocking arm framework includes loaded segment, linkage section, supporting section.Wherein, loaded segment and supporting section are connected to linkage section both sides, institute
Supporting section is stated be hinged at the top of rocking arm frame base, joint portion and be hinged, the position at the top of the control pressurized strut of position of linkage section and supporting section
Control on the be hinged control pressurized strut base in place in pressurized strut bottom, loading pressurized strut one end is hinged with loaded segment, other end joint test
Part.
When testpieces (movable wing) moves, experiment control system control bit control pressurized strut elongates or shortens, and promotes whole
Individual rocking arm framework rotates around the coercive mechanism of rocking arm frame base, drives the loading pressurized strut and experiment being arranged on rocking arm framework
Part (movable wing) reaches same position with phase same rate, makes to be arranged on loading pressurized strut and movable wing on rocking arm framework
The coordinated movement of various economic factors, while load pressurized strut and corresponding load is applied to testpieces, realize movable wing test load and the work of motion
Dynamic aerofoil remains the following loading of certain angle, in real simulation aircraft flight in the motion process of its movable wing
Stand under load.Pressurized strut base is controlled by the selection and position that align control start barrel stroke to control with rocking arm frame base physical dimension and position
The adjustment of geometrical relationship between pressurized strut base and rocking arm frame base, the following loading no more than 75 ° can be achieved.
The angle of cut between loaded segment and supporting section and linkage section is all higher than 90 °, avoids the collision of testpieces and rocking arm framework
And the collision between loading pressurized strut and rocking arm framework, it ensure that the safety of testpieces and test facilities.
The joint portion of linkage section and supporting section is provided with monaural with position control pressurized strut junction and embeds oscillating bearing, avoids cutting with scissors
The clamping stagnation of fulcrum.
The folding and unfolding that the present invention controls pressurized strut by the position for determining to be arranged on following loading device instructs, and utilizes existing examination
Loading coordinated control system driving position control pressurized strut stretching motion is tested, driving rocking arm framework follows movable wing to rotate, realizes peace
Loading pressurized strut and the coordinated movement of various economic factors of movable wing on rocking arm framework, realize movable wing test load and the work of motion
Dynamic aerofoil remains the following loading of certain angle.Solving conventional test method can only be in the state of movable wing fixation
The problem of being loaded, more real simulation, a checking are opened for the static(al) of similar shape movable wing structure, fatigue test
The approach of experiment.
Claims (3)
1. a kind of movable wing following loading device, it is characterised in that including position control pressurized strut base (1), position control pressurized strut
(2), rocking arm framework (3), rocking arm frame base (4) and loading pressurized strut (5), the rocking arm framework (3) include loaded segment, connection
Section, supporting section, wherein, loaded segment and supporting section are connected to linkage section both sides, the supporting section and rocking arm frame base (4)
Top is hinged, and be hinged at the top of position control pressurized strut (2), position control pressurized strut bottom is be hinged in place for the joint portion of linkage section and supporting section
Control on pressurized strut base (1), loading pressurized strut one end is hinged with loaded segment, other end joint test part.
2. movable wing following loading device according to claim 1, it is characterised in that loaded segment and supporting section and connection
The angle of cut between section is all higher than 90 °.
3. movable wing following loading device according to claim 2, it is characterised in that the combination of linkage section and supporting section
Portion is provided with monaural with position control pressurized strut junction and embeds oscillating bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410178574.8A CN105021414B (en) | 2014-04-29 | 2014-04-29 | Movable wing following loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410178574.8A CN105021414B (en) | 2014-04-29 | 2014-04-29 | Movable wing following loading device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105021414A CN105021414A (en) | 2015-11-04 |
| CN105021414B true CN105021414B (en) | 2018-03-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410178574.8A Active CN105021414B (en) | 2014-04-29 | 2014-04-29 | Movable wing following loading device |
Country Status (1)
| Country | Link |
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| CN (1) | CN105021414B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105336252B (en) * | 2015-12-14 | 2018-03-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of redundant structure load displacement Coordination Loading Method |
| CN107264836B (en) * | 2017-07-28 | 2020-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Cabin door large-range follow-up loading test device and test method |
| CN111159826B (en) * | 2019-12-25 | 2023-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Method and equipment for optimizing fulcrum positions of multi-fulcrum airfoil structure |
| CN112730052A (en) * | 2020-12-01 | 2021-04-30 | 成都飞机工业（集团）有限责任公司 | Adjustable modular clamping plate loading device |
| CN114509251B (en) * | 2021-12-31 | 2023-06-23 | 中国飞机强度研究所 | Follow-up loading device for movable airfoil surface of aircraft |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203616114U (en) * | 2013-12-04 | 2014-05-28 | 中国飞机强度研究所 | High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102023093B (en) * | 2009-09-11 | 2013-07-03 | 中国商用飞机有限责任公司 | Rocker arm type loading mechanism |
| CN101870358B (en) * | 2010-06-23 | 2012-12-26 | 南京航空航天大学 | Toggle type nose wheel steering mechanism and work method |
| CN202083541U (en) * | 2011-01-05 | 2011-12-21 | 哈尔滨飞机工业集团有限责任公司 | Follow-up loading structure for airplane flap test |
| KR101049217B1 (en) * | 2011-04-06 | 2011-07-13 | 부산대학교 산학협력단 | Lift power generation system |
| CN202403925U (en) * | 2011-12-20 | 2012-08-29 | 中国飞机强度研究所 | Push-followed loading device for aircraft flap |
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2014
- 2014-04-29 CN CN201410178574.8A patent/CN105021414B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203616114U (en) * | 2013-12-04 | 2014-05-28 | 中国飞机强度研究所 | High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test |
Non-Patent Citations (1)
| Title |
|---|
| 飞机襟缝翼收放功能试验随动加载研究;***;《工程与试验》;20150915;第55卷(第3期);全文 * |
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| Publication number | Publication date |
|---|---|
| CN105021414A (en) | 2015-11-04 |
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