CN203616114U - High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test - Google Patents
High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test Download PDFInfo
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- CN203616114U CN203616114U CN201320797416.1U CN201320797416U CN203616114U CN 203616114 U CN203616114 U CN 203616114U CN 201320797416 U CN201320797416 U CN 201320797416U CN 203616114 U CN203616114 U CN 203616114U
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- balance arm
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- pressurized strut
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- loading mechanism
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- 239000002390 adhesive tape Substances 0.000 abstract 1
- 238000001228 spectrum Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 210000005069 ears Anatomy 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
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Abstract
The utility model relates to a loading mechanism, particularly to high-position swing beam follow-up loading mechanism for aircraft flap/slat retractable tests. The high-position swing beam follow-up loading mechanism is formed by arranging a rotatable swing beam above a flap/slat, so as to avoid the problem of motion interference between a movement mechanism and the flap/slat, and reduce the low-position space of the flap/slat and a supporting rack occupied by the high-position swing beam follow-up loading mechanism; the high-position swing beam follow-up loading mechanism is composed of a high-position swing beam, a displacement actuating cylinder, a load actuating cylinder, a swing beam, a supporting column, a lever and an adhesive tape; the displacement actuating cylinder pushes the swing beam to rotate around a hinge point to trace the motion of a flap/slat loading point, so that a loading application line of the load actuating cylinder is vertical to the flap/slat surface on which the loading point is located; and the swing beam, the displacement actuating cylinder and the load actuating cylinder are arranged in a vertical plane of the motion trail of the loading point or a trail-approximate-to median-position vertical plane.
Description
Technical field
The utility model relates to a kind of following loading mechanism, particularly relates to the folding and unfolding of a kind of aircraft flap/slat and tests high-order balance arm following loading mechanism.
Background technology
Aircraft flap/slat folding and unfolding test following loading mechanism is the basis of carrying out wing flap/slat folding and unfolding test following loading, is to carry out the problem that first test design need to be considered and solve; In reality, wing flap/slat is installed support platform and wing flap/slat folding and unfolding angle when larger, causes the very limited and movement interference problem of low bit space to be difficult to process, and multiple degrees of freedom platform and low level rotation rocker are difficult to address these problems.
The utility model patent " a kind of follow-up loading structure for airplane flap test " of Granted publication CN202083541U, loading actuator two ends sister block structure has been proposed, realize with two coasters on two displacement actuators control guide rails the location and the loading direction that load pressurized strut respectively, the structural design of this utility model patent, processed complex, and can only use at low level, be difficult to use for wing flap/slat folding and unfolding test of low level limited space.
Utility model summary of the invention
The purpose of this utility model is: provide the folding and unfolding of a kind of aircraft flap/slat to test high-order balance arm following loading mechanism, solve the problem of wing flap/slat low level limited space, solve the movement interference problem of the folding and unfolding of wing flap/slat and low level following loading mechanism.
The technical solution of the utility model is: high-order balance arm following loading mechanism is tested in the folding and unfolding of a kind of aircraft flap/slat, it comprises high-order balance arm, displacement pressurized strut, load pressurized strut, support post, wherein, displacement pressurized strut afterbody is hinged on support post, displacement pressurized strut head and high-order balance arm are hinged, high-order balance arm upper end and support post hinge, lower end and load pressurized strut afterbody are hinged, and load pressurized strut head is connected with wire rope, and wire rope is connected with aerofoil with rubberized tape by lever.
Support post is fixing by column diagonal brace 9 and firm banking 10.
When load(ing) point movement locus is in a vertical plane, high-order balance arm, displacement pressurized strut, load pressurized strut, balance arm and the support post of high-order balance arm following loading mechanism are in this vertical plane.
When load(ing) point movement locus is not in a vertical plane, make vertical of a track meta or basic meta, high-order balance arm, displacement pressurized strut, load pressurized strut, balance arm and the support post of high-order balance arm following loading mechanism are in this meta vertical plane.
Technique effect of the present utility model is: for the each load(ing) point of wing flap/slat, rotated to follow the folding and unfolding campaign of wing flap/slat by a displacement pressurized strut promotion balance arm, realize the dynamic load to load(ing) point by a load pressurized strut; Because moving component balance arm is in a high position, can avoids the folding and unfolding campaign of wing flap/slat and motion interference problem, and can avoid wing flap/slat and support stand causes low level limited space to cause the problem of test design difficulty.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
In Fig. 1: the high-order balance arm of 1-; 2-displacement pressurized strut; The pressurized strut of 3-load; 4-balance arm rotary gemel; 5-load pressurized strut afterbody auricle connects hinge; 6-displacement pressurized strut head auricle connects hinge; 7-displacement pressurized strut afterbody auricle connects hinge; 8-support post; 9-column diagonal brace 10-column firm banking; 11-wing flap or slat; 12-rubberized tape; 13-connects lever, realizes load and distributes.
Embodiment
Below in conjunction with Fig. 1, concrete enforcement of the utility model scheme narrated.
The factors such as space, the support stand shared according to the folding and unfolding of wing flap/slat takes up room, wing flap/slat folding and unfolding angle, column riding position, designs the various building blocks of high-order balance arm following loading mechanism.
High position balance arm following loading mechanism is mainly by high-order balance arm 1; 2-displacement pressurized strut 2; 3-load pressurized strut 3; 4-balance arm rotary gemel 4; Load pressurized strut afterbody auricle connects hinge 5; Displacement pressurized strut head auricle connects hinge 6; Displacement pressurized strut afterbody auricle connects hinge 7; Support post 8; Column diagonal brace 9, column firm banking 10 form; Other is wing flap/slat 11, rubberized tape 12, lever 13.
Hinge is monaural and ears connected mode, and all monaurals adopt monaural ball corner structure.
High-order balance arm 1, displacement pressurized strut 2, load pressurized strut 3, balance arm and the support post 8 etc. of high-order balance arm following loading mechanism are arranged in its working face.Working face is to determine like this: if the movement locus of wing flap/slat load(ing) point (when zero load) is in a vertical plane, using this plane as working face; If load(ing) point movement locus is not in a vertical plane, make vertical of a track meta or basic meta, made working face.
High-order balance arm following loading mechanical work principle: measure wing flap/slat folding and unfolding angle beta by sensor, adopt MTS/MOOG multichannel synchro-loading control system to carry out closed-loop control to displacement pressurized strut and load pressurized strut, control rate is displacement pressurized strut stroke " angle-displacement " spectrum and load pressurized strut load " angle-load " spectrum, and independent variable is wing flap/slat folding and unfolding angle; When the folding and unfolding of wing flap/slat, displacement pressurized strut 2 promotes balance arm 1 and rotates around hinge 4, makes the load line of load pressurized strut 3 realize dynamic load perpendicular to load(ing) point.
In order not take near space wing flap/slat below and low level, be the top that balance arm is placed in wing flap/slat by the moving component of following loading mechanism, and be connected with support post with hinge, promoting balance arm with a displacement pressurized strut rotates, realize with the folding and unfolding of wing flap/slat with motion tracking, load with a load pressurized strut, specifically comprise:
(1) high-order balance arm following loading mechanism framework: high-order balance arm 1, displacement pressurized strut 2, load pressurized strut 3, a balance arm turning joint 4(are arranged in stand column and beam), load pressurized strut afterbody auricle connects hinge 5(and is fixed on balance arm), displacement pressurized strut head auricle connects hinge 6, displacement pressurized strut afterbody auricle connects hinge 7, column 8, diagonal brace 9, column holder 10, other is wing flap/slat 11, rubberized tape 12, lever 13.
(2) high-order balance arm following loading mechanism's framework mounting plane and working face:
The first situation: if load(ing) point movement locus is in a vertical plane, high-order balance arm, displacement pressurized strut, load pressurized strut, balance arm and the support post of high-order balance arm following loading mechanism are arranged in this vertical plane;
The second situation: if load(ing) point movement locus is not in a vertical plane, make vertical of a track meta or basic meta, high-order balance arm, displacement pressurized strut, load pressurized strut, balance arm and the support post of high-order balance arm following loading mechanism are arranged in this meta vertical plane;
Load pressurized strut and displacement pressurized strut two ends auricle are monaural ball angle; Balance arm is connected hinge with column, and balance arm link is monaural ball angle, and column link is ears.
High-order balance arm following loading mechanical work principle: displacement pressurized strut and load pressurized strut are by the control of MTS/MOOG multichannel synchro-loading control system, and control rate is displacement pressurized strut stroke " angle-displacement " spectrum and load pressurized strut load " angle-load " spectrum designing in advance; In wing flap/slat folding and unfolding process, displacement pressurized strut promotes high-order balance arm around hinge through, guarantees that load pressurized strut line of force is vertical with wing flap/slat, and load pressurized strut is simultaneously carried out dynamic load to load(ing) point.
The utility model, can avoid wing flap/slat that the interference problem of stand, the motion of wing flap/slat and following loading mechanism is installed, succinct, manufacture and design easily, cost is low.
Claims (4)
1. high-order balance arm following loading mechanism is tested in aircraft flap/slat folding and unfolding, it is characterized in that, comprise high-order balance arm, displacement pressurized strut, load pressurized strut, support post, wherein, displacement pressurized strut afterbody is hinged on support post, and displacement pressurized strut head and high-order balance arm are hinged, and high-order balance arm upper end and support post hinge, lower end and load pressurized strut afterbody are hinged, load pressurized strut head is connected with wire rope, and wire rope is connected with aerofoil with rubberized tape by lever.
2. high-order balance arm following loading mechanism is tested in aircraft flap/slat according to claim 1 folding and unfolding, it is characterized in that, support post is fixed by column diagonal brace and firm banking.
3. high-order balance arm following loading mechanism is tested in aircraft flap/slat according to claim 1 folding and unfolding, it is characterized in that, when load(ing) point movement locus is in a vertical plane, high-order balance arm, displacement pressurized strut, load pressurized strut, balance arm and the support post of high-order balance arm following loading mechanism are in this vertical plane.
4. high-order balance arm following loading mechanism is tested in aircraft flap/slat according to claim 1 folding and unfolding, it is characterized in that, when load(ing) point movement locus is not in a vertical plane, make vertical of a track meta or basic meta, high-order balance arm, displacement pressurized strut, load pressurized strut, balance arm and the support post of high-order balance arm following loading mechanism are in this meta vertical plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320797416.1U CN203616114U (en) | 2013-12-04 | 2013-12-04 | High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320797416.1U CN203616114U (en) | 2013-12-04 | 2013-12-04 | High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test |
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| Publication Number | Publication Date |
|---|---|
| CN203616114U true CN203616114U (en) | 2014-05-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320797416.1U Expired - Lifetime CN203616114U (en) | 2013-12-04 | 2013-12-04 | High-position swing beam follow-up loading mechanism for aircraft flap/slat retractable test |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| CN104075868A (en) * | 2014-05-30 | 2014-10-01 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
| CN104386265A (en) * | 2014-12-15 | 2015-03-04 | 中国飞机强度研究所 | Actuator cylinder twisting prevention device |
| CN104776910A (en) * | 2015-04-21 | 2015-07-15 | 中国飞机强度研究所 | Device for measuring sound mode of engine pipeline |
| CN104787303A (en) * | 2015-04-02 | 2015-07-22 | 中航飞机股份有限公司西安飞机分公司 | Anti-misoperation flap control device |
| CN104890898A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | High lift device movement performance test method and system, and load spectrum measurement method |
| CN104925270A (en) * | 2015-05-13 | 2015-09-23 | 中国飞机强度研究所 | Method, torsion load testing system, pressure load testing system and adjustment assembly |
| CN104931250A (en) * | 2015-06-29 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | High-lift system whole-aircraft loading dynamic test method |
| CN105021414A (en) * | 2014-04-29 | 2015-11-04 | 中国飞机强度研究所 | Movable wing surface servo loading device |
| CN105223006A (en) * | 2015-09-17 | 2016-01-06 | 中国运载火箭技术研究院 | A kind of actuation means of power test run body wing flap antiscour test and test method |
| CN105758629A (en) * | 2014-12-19 | 2016-07-13 | 成都飞机设计研究所 | Servo loading method in aircraft strength test |
| 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 |
| CN108956179A (en) * | 2018-07-03 | 2018-12-07 | 上海交通大学 | The vertical following loading device and method of self-balancing |
| CN110243686A (en) * | 2019-05-22 | 2019-09-17 | 航天科工防御技术研究试验中心 | A kind of loading method of loading device and power |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111572813A (en) * | 2020-05-26 | 2020-08-25 | 中国飞机强度研究所 | Airplane upward loading device |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| 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 |
| CN113602523A (en) * | 2021-07-21 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Loading system for wing load calibration test and using method thereof |
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- 2013-12-04 CN CN201320797416.1U patent/CN203616114U/en not_active Expired - Lifetime
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105021414B (en) * | 2014-04-29 | 2018-03-02 | 中国飞机强度研究所 | Movable wing following loading device |
| CN105021414A (en) * | 2014-04-29 | 2015-11-04 | 中国飞机强度研究所 | Movable wing surface servo loading device |
| CN104075868A (en) * | 2014-05-30 | 2014-10-01 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
| CN104075868B (en) * | 2014-05-30 | 2017-02-22 | 西北工业大学 | Aerodynamic load loading method used for reliability tests on aircraft flap and slat system |
| CN104048874A (en) * | 2014-06-24 | 2014-09-17 | 西北工业大学 | Load follow-up loading system for plane flap reliability test |
| CN104386265A (en) * | 2014-12-15 | 2015-03-04 | 中国飞机强度研究所 | Actuator cylinder twisting prevention device |
| CN105758629A (en) * | 2014-12-19 | 2016-07-13 | 成都飞机设计研究所 | Servo loading method in aircraft strength test |
| CN105758629B (en) * | 2014-12-19 | 2018-04-03 | 成都飞机设计研究所 | A kind of following loading method in aircraft strength test |
| CN104787303A (en) * | 2015-04-02 | 2015-07-22 | 中航飞机股份有限公司西安飞机分公司 | Anti-misoperation flap control device |
| CN104776910A (en) * | 2015-04-21 | 2015-07-15 | 中国飞机强度研究所 | Device for measuring sound mode of engine pipeline |
| CN104925270A (en) * | 2015-05-13 | 2015-09-23 | 中国飞机强度研究所 | Method, torsion load testing system, pressure load testing system and adjustment assembly |
| CN104890898A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | High lift device movement performance test method and system, and load spectrum measurement method |
| CN104931250B (en) * | 2015-06-29 | 2018-04-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full machine loading dynamic test method of high-lift system |
| CN104931250A (en) * | 2015-06-29 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | High-lift system whole-aircraft loading dynamic test method |
| CN105223006B (en) * | 2015-09-17 | 2017-08-29 | 中国运载火箭技术研究院 | The actuation means and test method of a kind of power test run body wing flap antiscour experiment |
| CN105223006A (en) * | 2015-09-17 | 2016-01-06 | 中国运载火箭技术研究院 | A kind of actuation means of power test run body wing flap antiscour test and test 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 |
| CN108956179A (en) * | 2018-07-03 | 2018-12-07 | 上海交通大学 | The vertical following loading device and method of self-balancing |
| CN110243686A (en) * | 2019-05-22 | 2019-09-17 | 航天科工防御技术研究试验中心 | A kind of loading method of loading device and power |
| CN111003208A (en) * | 2019-12-06 | 2020-04-14 | 江西洪都航空工业集团有限责任公司 | Nonlinear force loading test device for airplane speed reduction plate |
| CN111572813A (en) * | 2020-05-26 | 2020-08-25 | 中国飞机强度研究所 | Airplane upward loading device |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
| 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 |
| CN113602523A (en) * | 2021-07-21 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Loading system for wing load calibration test and using method thereof |
| CN113602523B (en) * | 2021-07-21 | 2024-01-12 | 成都飞机工业（集团）有限责任公司 | Loading system for wing load calibration test and application method thereof |
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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 |
Granted publication date: 20140528 |
|
| CX01 | Expiry of patent term |