CN105015796A - Following weight-deducting pulley block system - Google Patents
Following weight-deducting pulley block system Download PDFInfo
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- CN105015796A CN105015796A CN201410177180.0A CN201410177180A CN105015796A CN 105015796 A CN105015796 A CN 105015796A CN 201410177180 A CN201410177180 A CN 201410177180A CN 105015796 A CN105015796 A CN 105015796A
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- pulley
- weight
- block system
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Abstract
The invention belongs to the technique of weight deduction of aircraft structure tests, and particularly relates to a following weight-deducting pulley block system for aircraft structure tests. The following weight-deducting pulley block system provided by the invention is good in structural stability, and can greatly improve the weight deducting precision of the aircraft structure tests. The pulley block system comprises adjustable connectors, a lever, fixed pulleys, a movable pulley, a steel cable and the like, wherein the fixed pulleys comprise a double pulley and a single pulley which are respectively arranged at two ends of the lever; one end of the steel cable is connected with a counterbalancing weight, and the other end of the steel cable goes around the single pulley, the double pulley and the movable pulley sequentially, and then, are fixed on the fixed point of the double pulley; a test piece which needs weight deduction is connected to a position under the movable pulley; the adjustable connectors are connected to the two ends of the lever and fixed at suspension points. The pulley block system is stable in tests, and effectively solves the problem of structural weight deduction in large-deformation tests; the pulley block system can regulate the load proportion of deducted weight to the counterbalancing weight in a steel cable winding manner; the pulley block system is flexible and convenient to mount, and is good in universality and practicability.
Description
Technical field
The invention belongs to aircraft structure test button weight technology, be specifically related to the heavy pulley block system of the servo-actuated button of a kind of aircraft structure test.
Background technology
In aircraft structure test, in order to warranty test load accurate, often require before test loads, by test article and affect test and load weight of equipment accurately and all deduct.Detain in current aircraft structure test and heavily mainly contain two kinds of forms: power control pressurized strut active button weighs and crowbar lever counterbalancing weight buckles weight.Crowbar lever counterbalancing weight is buckled refitting and is put owing to installing simple, adopts more in aircraft structure test.But for large aircraft, wing distortion is very large, when being undertaken buckleing heavy by traditional crowbar lever mode, aircraft distortion is very large on the impact of crowbar lever.Crowbar lever meeting knockdown in test, the precision and stability that impact button is heavy.
Summary of the invention
The object of the invention is: the invention provides a kind of structural stability good, significantly can improve the heavy pulley block system of servo-actuated button of the heavy precision of aircraft structure test button.
Technical scheme of the present invention is: the heavy pulley block system of this servo-actuated button comprises adjustable connecting piece, lever, fixed pulley, movable pulley, cable wire.Wherein, fixed pulley comprises sister block and the single-sheaved block that two are separately positioned on lever two ends, cable wire one end connects counterbalancing weight, the other end is fixed on the attachment point of sister block successively after single-sheaved block, sister block and movable pulley, and under movable pulley, connect the test article needing button heavy, adjustable connecting piece is connected to lever two ends, and is fixed on suspension centre place.
By the attaching parts of one group of general length adjustable, by lever regulate level, and be suspended on ceiling fixed point by 1 suspension centre.
The weight of the counterbalancing weight that the weight of aircaft configuration that assembly pulley one end connects is connected with the other end is certain integer ratio.
Technique effect of the present invention is:
1) in stable condition in test, efficiently solve the heavy problem of structure button of large deformation test;
2) load proportion with counterbalancing weight is weighed by cable wire canoe adjusting button;
3) convenient and flexible installation, commonality and practicality good.
The present invention not only solves the heavy problem of aircraft large deformation position button, also makes the heavy accuracy of button significantly improve.Accompanying drawing explanation
Fig. 1 is the structural representation of the heavy pulley block system of the servo-actuated button of the present invention;
Wherein, the heavy position of 1-aircaft configuration button, 2-movable pulley, 3-cable wire, 4-fixed pulley (sister block), 5-lever, 6-fixed pulley (single-sheaved block), 7-counterbalancing weight, 8-adjustable connecting piece, 9-suspension centre.
Detailed description of the invention
The present invention is described further in conjunction with the accompanying drawings and embodiments:
The heavy pulley block system of this servo-actuated button comprises adjustable connecting piece, lever, fixed pulley, movable pulley, cable wire etc.Lever, by the attaching parts of one group of general length adjustable, horizontally suspends, fixes 1 fixed pulley at lever two ends respectively by this system, is wound around guiding for cable wire.By a running block, heavy for aircaft configuration button position is connected with cable wire, achieves the transmission of button heavy lift.The heavy system major part of button and function as follows:
1) adjustable connecting piece: the attaching parts being one group of general, length adjustable, it is connected to lever two ends, for adjustment (adjusting) lever position level, and is fixed on suspension centre place.
2) lever: for fixing 2 fixed pulleys, and system is fixed to the suspension centre place of ceiling by adjustable connecting piece.
3) fixed pulley: fixed pulley comprises sister block and the single-sheaved block that two are separately positioned on lever two ends, these 2 fixed pulleys are fixed on lever, for cable wire being directed to the position of needs.
4) movable pulley: connect the test article needing button heavy under movable pulley, and transfer loads to counterbalancing weight point place by cable wire.
5) cable wire: one end connects counterbalancing weight, and the other end is fixed on the attachment point of sister block successively after single-sheaved block, sister block and movable pulley, realizes by canoe the load proportion convergent-divergent leading and detain emphasis and counterbalancing weight point.
This system utilizes assembly pulley principle, forms a set of pulley block system heavy for the servo-actuated button of aircaft configuration, has following innovative point:
1. the weight of the counterbalancing weight that the weight that assembly pulley one end connects aircaft configuration is connected with the other end is certain integer ratio, effectively can be reduced the weight of counterbalancing weight, reduce experimental work amount by adjustment ratio.
2. this pulley block system only has a suspension centre (attachment point), for being fixed on loading frame ceiling place, flexible for installation, convenient, requires low to site condition.
3., in test loading procedure, the heavy lever of button remains horizontality, and counterbalancing weight point is followed the distortion up and down of aircaft configuration and moves up and down, and achieves servo-actuated button heavy.
In a word, the servo-actuated button that this pulley block system achieves aircaft configuration is heavy, in stable condition in test, efficiently solves the heavy problem of structure button of large deformation test; The load proportion with counterbalancing weight is weighed by cable wire canoe adjusting button; Convenient and flexible installation, commonality and practicality good.
Claims (3)
1. the heavy pulley block system of servo-actuated button, is characterized in that, comprise adjustable connecting piece, lever, fixed pulley, movable pulley, cable wire etc.Wherein, fixed pulley comprises sister block and the single-sheaved block that two are separately positioned on lever two ends, cable wire one end connects counterbalancing weight, the other end is fixed on the attachment point of sister block successively after single-sheaved block, sister block and movable pulley, and below movable pulley, connect the test article needing button heavy, adjustable connecting piece is connected to lever two ends, and is fixed on suspension centre place.
2. pulley block system according to claim 1, is characterized in that, by the attaching parts of one group of general length adjustable, by lever regulate level, and is suspended on the ceiling fixed point of loading frame by 1 suspension centre.
3. pulley block system according to claim 2, is characterized in that, the weight of the counterbalancing weight that the weight of aircaft configuration that assembly pulley one end connects is connected with the other end is certain integer ratio.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177180.0A CN105015796A (en) | 2014-04-29 | 2014-04-29 | Following weight-deducting pulley block system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177180.0A CN105015796A (en) | 2014-04-29 | 2014-04-29 | Following weight-deducting pulley block system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105015796A true CN105015796A (en) | 2015-11-04 |
Family
ID=54406188
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410177180.0A Pending CN105015796A (en) | 2014-04-29 | 2014-04-29 | Following weight-deducting pulley block system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105015796A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108956179A (en) * | 2018-07-03 | 2018-12-07 | 上海交通大学 | The vertical following loading device and method of self-balancing |
| CN111498143A (en) * | 2020-05-13 | 2020-08-07 | 中国飞机强度研究所 | Weight deducting device and weight deducting method thereof |
| CN111498139A (en) * | 2020-04-22 | 2020-08-07 | 中国飞机强度研究所 | Buffer type weight-fastening device |
| CN113405902A (en) * | 2021-05-19 | 2021-09-17 | 中航西安飞机工业集团股份有限公司 | Loading lever and loading method for strength test |
-
2014
- 2014-04-29 CN CN201410177180.0A patent/CN105015796A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108956179A (en) * | 2018-07-03 | 2018-12-07 | 上海交通大学 | The vertical following loading device and method of self-balancing |
| CN111498139A (en) * | 2020-04-22 | 2020-08-07 | 中国飞机强度研究所 | Buffer type weight-fastening device |
| CN111498143A (en) * | 2020-05-13 | 2020-08-07 | 中国飞机强度研究所 | Weight deducting device and weight deducting method thereof |
| CN113405902A (en) * | 2021-05-19 | 2021-09-17 | 中航西安飞机工业集团股份有限公司 | Loading lever and loading method for strength test |
| 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 |
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| C06 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20151104 |