CN105021414A - Movable wing surface servo loading device - Google Patents
Movable wing surface servo loading device Download PDFInfo
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- CN105021414A CN105021414A CN201410178574.8A CN201410178574A CN105021414A CN 105021414 A CN105021414 A CN 105021414A CN 201410178574 A CN201410178574 A CN 201410178574A CN 105021414 A CN105021414 A CN 105021414A
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- movable wing
- loading
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- pressurized strut
- wing surface
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Abstract
The invention belongs to an airplane wing surface loading technology, and particularly relates to a movable wing surface servo loading device. The movable wing surface servo loading device comprises a position control actuator cylinder base, a position control actuator cylinder, a rocker frame, a rocker frame base and a loading actuator cylinder, wherein the rocker frame comprises a loading section, a connecting section and a supporting section, the loading section and the supporting section are connected at two sides of the connection section respectively, the supporting section is hinged with the top part of the rocker frame base, a junction of the connecting section and the supporting section is hinged with the top part of the position control actuator cylinder, the bottom part of the position control actuator cylinder is hinged on the position control actuator cylinder base, one end of the loading actuator cylinder is hinged with the loading section, and the other end of the loading actuator cylinder is connected to a test piece. The movable wing surface servo loading device can realize that a movable wing surface test load always keeps servo loading with a certain angle with a moving movable wing surface, and provides a more realistic simulation and verification test approach for static force and fatigue tests of movable wing surface structures of the same kind.
Description
Technical field
The invention belongs to plane airfoil loading technique, be specifically related to a kind of movable wing following loading device.
Background technology
Usually, for aircraft movable wing static(al), torture test, substantially carry out under movable wing remains static, along with the requirement of development to test of experimental technique also improves day by day, while proposing in test movable wing motion, experiment loading unit carries out coordinating the requirement of following loading.
Following loading problem also once occurred in slow test and function test, solution is in the past all that the mode of being synthesized by multiple load vector is realized, the requirement that this method installs control due to it for number of devices and equipment is higher, limit its range of application greatly, can only bench-scale testing be used for.
Summary of the invention
The object of the invention is: the invention provides a kind of using displacement as controlled quentity controlled variable, the Angular Displacement following loading of loading equipemtn can be realized, the following loading device of real simulation movable wing loading conditions.
Technical scheme of the present invention is: a kind of movable wing following loading device, it comprises position control pressurized strut base, position control pressurized strut, rocking arm framework, rocking arm frame base and loading pressurized strut, described rocking arm framework comprises loaded segment, linkage section, supporting section, wherein, loaded segment and supporting section are connected to linkage section both sides, described supporting section and rocking arm frame base top hinged, it is hinged that pressurized strut top is controlled in the joint portion of linkage section and supporting section and position, on position control pressurized strut bottom-hinged control pressurized strut in place base, load pressurized strut one end and loaded segment hinged, other end joint test part.
Loaded segment and the angle of cut between supporting section and linkage section are all greater than 90 °.
The joint portion of linkage section and supporting section and position are controlled pressurized strut junction and are provided with the embedded oscillating bearing of monaural.
Technique effect of the present invention is:
The present invention is by determining the folding and unfolding instruction of the position control pressurized strut be arranged on following loading device, utilize existing test to load coordinated control system and drive position control pressurized strut stretching motion, drive rocking arm framework to follow movable wing to rotate, realize the coordinated movement of various economic factors of loading pressurized strut and the movable wing be arranged on rocking arm framework, the movable wing realizing movable wing test load and motion remains the following loading of certain angle.Carry out the problem loaded under solving the state that test method can only be fixed at movable wing in the past, for the static(al) of similar shape movable wing structure, torture test open one simulate more really, the approach of demonstration test.
Accompanying drawing explanation
Fig. 1 is the structural representation of movable wing following loading device of the present invention;
Wherein, 1-position control pressurized strut base, the control pressurized strut of 2-position, 3-rocking arm framework, 4-rocking arm frame base, 5-load pressurized strut, 6-testpieces (movable wing).
Embodiment
Below in conjunction with drawings and Examples, the present invention will be further described:
Refer to Fig. 1, it is the structural representation of movable wing following loading device of the present invention.Described movable wing following loading device, it comprises position control pressurized strut base, position control pressurized strut, rocking arm framework, rocking arm frame base and loads pressurized strut, and described rocking arm framework comprises loaded segment, linkage section, supporting section.Wherein, loaded segment and supporting section are connected to linkage section both sides, described supporting section and rocking arm frame base top hinged, it is hinged that pressurized strut top is controlled in the joint portion of linkage section and supporting section and position, on position control pressurized strut bottom-hinged control pressurized strut in place base, load pressurized strut one end and loaded segment hinged, other end joint test part.
When testpieces (movable wing) moves, experiment control system control bit control pressurized strut elongates or shortens, promoting whole rocking arm framework around the coercive mechanism of rocking arm frame base rotates, drive be arranged on rocking arm framework loading pressurized strut arrive same position with testpieces (movable wing) with phase same rate, make to be arranged on the coordinated movement of various economic factors of loading pressurized strut on rocking arm framework and movable wing, load pressurized strut simultaneously and corresponding load is applied to testpieces, the movable wing realizing movable wing test load and motion remains the following loading of certain angle, in real simulation aircraft flight its movable wing motion process in stand under load.Controlled the adjustment of geometric relationship between pressurized strut base and rocking arm frame base by the selection of contraposition control pressurized strut stroke and position control pressurized strut base and rocking arm frame base physical dimension and position, the following loading being not more than 75 ° can be realized.
Loaded segment and the angle of cut between supporting section and linkage section are all greater than 90 °, and the collision avoiding testpieces and rocking arm framework and the collision loaded between pressurized strut and rocking arm framework, ensure that the safety of testpieces and test facilities.
The joint portion of linkage section and supporting section and position are controlled pressurized strut junction and are provided with the embedded oscillating bearing of monaural, avoid the clamping stagnation of coercive mechanism.
The present invention is by determining the folding and unfolding instruction of the position control pressurized strut be arranged on following loading device, utilize existing test to load coordinated control system and drive position control pressurized strut stretching motion, drive rocking arm framework to follow movable wing to rotate, realize the coordinated movement of various economic factors of loading pressurized strut and the movable wing be arranged on rocking arm framework, the movable wing realizing movable wing test load and motion remains the following loading of certain angle.Carry out the problem loaded under solving the state that test method can only be fixed at movable wing in the past, for the static(al) of similar shape movable wing structure, torture test open one simulate more really, the approach of demonstration test.
Claims (3)
1. a movable wing following loading device, it is characterized in that, comprise 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), described rocking arm framework (3) comprises loaded segment, linkage section, supporting section, wherein, loaded segment and supporting section are connected to linkage section both sides, described supporting section and rocking arm frame base (4) top hinged, it is hinged that pressurized strut (2) top is controlled in the joint portion of linkage section and supporting section and position, on position control pressurized strut bottom-hinged control pressurized strut in place base (1), load pressurized strut one end and loaded segment hinged, other end joint test part.
2. movable wing following loading device according to claim 1, is characterized in that, loaded segment and the angle of cut between supporting section and linkage section are all greater than 90 °.
3. movable wing following loading device according to claim 2, is characterized in that, the joint portion of linkage section and supporting section and position are controlled pressurized strut junction and be provided with the embedded oscillating bearing of monaural.
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 |
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| CN105021414A true CN105021414A (en) | 2015-11-04 |
| CN105021414B CN105021414B (en) | 2018-03-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410178574.8A Active CN105021414B (en) | 2014-04-29 | 2014-04-29 | Movable wing following loading device |
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| CN (1) | CN105021414B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105336252A (en) * | 2015-12-14 | 2016-02-17 | 中国航空工业集团公司西安飞机设计研究所 | Redundant structure load displacement coordination loading method |
| CN107264836A (en) * | 2017-07-28 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | The a wide range of following loading experimental rig of hatch door and test method |
| CN111159826A (en) * | 2019-12-25 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Multi-fulcrum airfoil structure fulcrum position optimization method and device |
| 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 |
| CN114509251A (en) * | 2021-12-31 | 2022-05-17 | 中国飞机强度研究所 | Follow-up loading device for movable wing surface of aircraft |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105336252A (en) * | 2015-12-14 | 2016-02-17 | 中国航空工业集团公司西安飞机设计研究所 | Redundant structure load displacement coordination loading method |
| 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 |
| CN107264836A (en) * | 2017-07-28 | 2017-10-20 | 中国航空工业集团公司西安飞机设计研究所 | The a wide range of following loading experimental rig of hatch door and test 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 |
| CN111159826A (en) * | 2019-12-25 | 2020-05-15 | 中国航空工业集团公司西安飞机设计研究所 | Multi-fulcrum airfoil structure fulcrum position optimization method and device |
| 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 |
| CN114509251A (en) * | 2021-12-31 | 2022-05-17 | 中国飞机强度研究所 | Follow-up loading device for movable wing surface of aircraft |
| 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 |
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|---|---|
| CN105021414B (en) | 2018-03-02 |
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