CN103954340B - Jacking type aircraft weighting breakout box - Google Patents
Jacking type aircraft weighting breakout box Download PDFInfo
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- CN103954340B CN103954340B CN201410171088.3A CN201410171088A CN103954340B CN 103954340 B CN103954340 B CN 103954340B CN 201410171088 A CN201410171088 A CN 201410171088A CN 103954340 B CN103954340 B CN 103954340B
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- screw bore
- radial screw
- breakout box
- type aircraft
- jacking type
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Abstract
The invention discloses a kind of jacking type aircraft weighting breakout box, comprise: pedestal, for cylinder or frustum cone structure, thus center, the end is provided with the connecting stud for connecting load transducer thereon, and the center of going to the bottom has the blind hole for being held into wheel shaft screw jack upper push-rod head; And this pedestal side circumference is all equipped with multiple radial screw bore; Gusset plate, is configured with multiple, has a plain film and vertical with this plain film and have the vertical sheet of via hole, thus when via hole and radial screw bore are coaxially assembled, plain film is fitted and extends to the lower edge of push rod cup and the constraint that forms push rod cup with going to the bottom; And bolt, assemble with mating of radial screw bore for via hole.Can effectively prevent load transducer from coming off from wheel shaft screw jack according to the present invention.
Description
Technical field
The present invention relates to a kind of breakout box, for the switching of wheel shaft screw jack and load transducer in jacking type aircraft weighting.
Background technology
In order to ensure the safety that aircraft flies aloft, the weight of aircraft and center of gravity need to control effectively.It is exactly the main path determining aircraft weight center of gravity to aircraft routine weighing.
The form of aircraft weighting has multiple, and wheel shaft jacking type aircraft weighting method is one wherein.Its implementation is: place load transducer at each wheel shaft fulcrum of aircraft, by aircraft jack-up, the weight data sum of each sensor is aircraft gross weight; The weight center of gravity of aircraft is drawn again by formulae discovery.
Above-mentioned weighting manner needs by wheel shaft screw jack and load transducer.Need to carry out assembling between the two to use.Once assemble the insecure or deflection that exerts a force in aircraft jacking process, sensor may be thrown off from lifting jack, and cause lifting jack top to hinder aircraft, maintenance cost is very large.There is this type of event in certain airline external.
Summary of the invention
Therefore, the object of the present invention is to provide a kind of jacking type aircraft weighting breakout box that can effectively prevent load transducer from coming off from wheel shaft screw jack.
The present invention is by the following technical solutions:
A kind of jacking type aircraft weighting breakout box, comprising:
Pedestal, be cylinder or frustum cone structure, thus center, the end is provided with the connecting stud for connecting load transducer thereon, the center of going to the bottom has the blind hole for being held into wheel shaft screw jack upper push-rod head; And this pedestal side circumference is all equipped with multiple radial screw bore;
Gusset plate, is configured with multiple, has a plain film and vertical with this plain film and have the vertical sheet of via hole, thus when via hole and radial screw bore are coaxially assembled, plain film is fitted and extends to the lower edge of push rod cup and the constraint that forms push rod cup with going to the bottom; And
Bolt, assembles with mating of radial screw bore for via hole.
Particularly, the quantity of radial screw bore is the twice of gusset plate quantity, thus, matched by interval for the radial screw bore of assembling gusset plate;
Remaining radial screw bore penetrates into described blind hole, thus is furnished with puller bolt in the radial screw bore of this remainder, for holding out against the side at push rod cup.
Particularly, the quantity of described radial screw bore is six.
Particularly, described puller bolt is stud.
Particularly, the counterbore being formed with the vertical plate shape of coupling of the radial screw bore of gusset plate is equipped with.
Particularly, described counterbore is square or rectangle counterbore.
Particularly, described bolt is stud, coordinates this stud, is also provided with nut.
According to the present invention, as can be seen from said structure, the connecting stud arranged by pedestal coupling and blind hole, for the connection of load transducer and being held into of wheel shaft screw jack push rod cup, then the constraint to push rod cup is formed by gusset plate, thus formed and connect reliably, enhance the fastness that wheel shaft screw jack and sensor assemble.
Accompanying drawing explanation
Fig. 1 is the decomposition texture schematic diagram according to a kind of jacking type aircraft weighting breakout box of the present invention.
Fig. 2 is that jacking type aircraft weighting breakout box uses the corresponding decomposing state schematic diagram of assembling.
Fig. 3 is jacking type aircraft weighting breakout box using state schematic diagram.
In figure: 1. pedestal, 2. gusset plate, 3. stud, 4. nut, 5. connecting stud, 6. locating slot, 7. via hole, 8. vertical sheet, 9. threaded hole, 10. threaded hole, 11. jacking type aircraft weighting breakout boxs, 12. load transducers, 13. wheel shaft screw jacks, 14. connecting thread holes, 15. push rod cups.
Embodiment
With reference to Figure of description 2, the push rod 15 of wheel shaft screw jack 13 is for being connected with load transducer 12, and wherein load transducer 12, as Fig. 2 top, its basic structure is cylindrical, with screwed hole of centre, referred to here as connecting thread hole 14.
As shown in Figure 2, its upper end has one section of screw thread to the push rod (piston rod) of wheel shaft screw jack 13, and also having one section of push rod cup in the upper end of thread segment, is socket cap, and diameter is greater than the large footpath of thread segment.
Under this structural condition, load transducer 12 can be poor with the combination stability of wheel shaft screw jack 13, and the bottom surface of load transducer 12 can not obtain effective support.
A kind of jacking type aircraft weighting breakout box as shown in Figure 1, comprising:
Pedestal 1, for cylinder or frustum cone structure, it is column structure in figure, main body is solid of revolution, upper bottom surface can support loads sensor 12, form composition surface and supporting surface, and center, the end is provided with the connecting stud 5 for connecting load transducer 12, coming off of the load transducer 12 avoiding unstability to cause thereon.
The center of going to the bottom of pedestal 1 has the blind hole for being held into wheel shaft screw jack 13 upper push-rod head 15, and this blind hole and push rod cup 15 can leave tolerance clearance, with convenient for assembly, also can adopt friction tight mode.
Pedestal 1 is switching basic components, and adopt stainless steel part, processibility is relatively good, also can adopt ironcasting or Al-alloy parts.
For meeting assembled condition stability inferior, this pedestal side circumference is all equipped with multiple radial screw bore, and threaded hole 9 as shown in Figure 1 and threaded hole 10, be distributed in the surrounding of pedestal 1, and its assembling acting body now in the following areas.
First aspect coordinates with gusset plate 2, the parts of the similar unequal angle shown in Fig. 1, it has one and has a plain film, as the horizontal component of gusset plate in figure 2, and then also have one vertical with this plain film and have the vertical sheet 2 of via hole 7, thus, via hole 7 is for assembling, when coaxially assembling with radial screw bore, plain film is fitted and extends to the lower edge of push rod cup 15 and the constraint that forms push rod cup 15 with going to the bottom, plain film by with the coordinating of pedestal 1 bottom surface, and by the constraint of via hole 7, form stable syndeton.
And then using bolt to connect gusset plate 2, as shown in Figure 1, by bolt, via hole 7 was assembled with mating of radial screw bore, is via hole 7 in figure and the mating of threaded hole 10.
Said structure relates to the problem of first aspect, can meet stability to a certain extent, relies on flat blade portion to prop up the lower to realizing constraint of push rod cup 15.
In further selecting, in other words in second aspect, the quantity of radial screw bore is the twice of gusset plate quantity, as shown in Figure 1, thus, matched by interval for the radial screw bore of assembling gusset plate 2, accordingly it is contemplated that gusset plate 2 is uniformly distributed in pedestal surrounding.
So remaining radial screw bore penetrates into described blind hole, thus be furnished with puller bolt in the radial screw bore of this remainder, for holding out against in the side of push rod cup 15, formation holds, thus makes to form the structure being analogous to interference fit between described blind hole and described push rod cup 15.
By the synergy of aforementioned two aspects, pedestal 1 can be fixed on push rod cup 15 reliably, to unstability, there is better adaptability.
Preferably, the distribution of described radial screw bore on pedestal 1 can adopt Central Symmetry or rotational symmetry configuration, and preferably, the quantity of radial screw bore is six.The threaded hole 10 so connected for gusset plate 2 has 3, every 120 degree one, forms stable three-legged structure.
In order to simplify structure, described puller bolt is stud 3, and hexagonal in bolt head part is formed, one-piece construction size is little.
In order to simplify structure further, be equipped with the counterbore being formed with vertical sheet 8 shape of coupling of the radial screw bore of gusset plate, this structure sheet 8 that more easily opposes forms spacing, thus the stability of structure can be made better.
For the flat blade portion of gusset plate 2, also can at the bottom surface structure groove of pedestal 1, thus can be formed spacing better, form stable structure.
Preferably, described counterbore is square or rectangle counterbore, and more easily form constraint reliably, the counterbore in figure is the counterbore of semi open model, the shape of coupling gusset plate 2.
Preferably, as shown in Figure 1, described bolt is stud 2, coordinates this stud, is also provided with nut 4.
As Figure 1-3, breakout box is made up of gusset plate 2, six external thread studs of pedestal 1, three L shapes of a stainless steel, three nuts 4 on the whole.
Installation step (Fig. 1):
1. first wheel shaft screw jack 13 is positioned on the level ground of aircraft weighting relevant position.
2. regulate wheel shaft screw jack 13 to suitable height.
3. the pedestal 1 of breakout box is positioned over wheel shaft screw jack 13 head end, on the end face of namely push rod cup 15.
4. with hex tool, three places are not needed stud Peripheric locking lifting jack top head end (push rod cup 15) of installing gusset plate.
5. respectively the gusset plate 2 of three L shapes is positioned in the groove of pedestal 1, and with remaining three studs locking wheel shaft screw jack top head end, hook up to lifting jack head end (push rod cup 15) lower limb so simultaneously.
6. lock three gusset plates 2 respectively with three nuts.
7. last, by the stud of load transducer by connector base top, screw and be fixed on pedestal.
Before Fig. 2 gives assembling, the relative position of wheel shaft screw jack, breakout box and load transducer.
Signal after Fig. 3 gives and assembled.
Claims (7)
1. a jacking type aircraft weighting breakout box, is characterized in that, comprising:
Pedestal (1) is cylinder or frustum cone structure, thus center, the end is provided with the connecting stud (5) for connecting load transducer (12) thereon, and the center of going to the bottom has the blind hole for being held into wheel shaft screw jack (13) upper push-rod head (15); And this pedestal side circumference is all equipped with multiple radial screw bore;
Gusset plate (2), be configured with multiple, there is a plain film and vertical with this plain film and have the vertical sheet (8) of via hole (7), thus, when via hole (7) and radial screw bore are coaxially assembled, plain film and pedestal are gone to the bottom and are fitted and extend to the lower edge of push rod cup (15) and the constraint that forms push rod cup (15); And
Bolt, assembles with mating of radial screw bore for via hole.
2. jacking type aircraft weighting breakout box according to claim 1, is characterized in that, the quantity of radial screw bore is the twice of gusset plate quantity, thus, matched by interval for the radial screw bore of assembling gusset plate;
Remaining radial screw bore penetrates into described blind hole, thus is furnished with puller bolt in the radial screw bore of this remainder, for holding out against the side in push rod cup (15).
3. jacking type aircraft weighting breakout box according to claim 2, is characterized in that, the quantity of described radial screw bore is six.
4. jacking type aircraft weighting breakout box according to claim 2, is characterized in that, described puller bolt is stud (3).
5. according to the arbitrary described jacking type aircraft weighting breakout box of Claims 1-4, it is characterized in that, the radial screw bore being equipped with gusset plate forms the counterbore of vertical sheet (8) shape of coupling.
6. jacking type aircraft weighting breakout box according to claim 5, is characterized in that, described counterbore is square or rectangle counterbore.
7. jacking type aircraft weighting breakout box according to claim 1, is characterized in that, described bolt is stud (3), coordinates this stud, is also provided with nut (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410171088.3A CN103954340B (en) | 2014-04-28 | 2014-04-28 | Jacking type aircraft weighting breakout box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410171088.3A CN103954340B (en) | 2014-04-28 | 2014-04-28 | Jacking type aircraft weighting breakout box |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103954340A CN103954340A (en) | 2014-07-30 |
| CN103954340B true CN103954340B (en) | 2015-09-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410171088.3A Expired - Fee Related CN103954340B (en) | 2014-04-28 | 2014-04-28 | Jacking type aircraft weighting breakout box |
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| Country | Link |
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| CN (1) | CN103954340B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989807B (en) * | 2017-06-09 | 2023-04-11 | 中航通飞华南飞机工业有限公司 | Aircraft weighing system |
| CN111177964B (en) * | 2019-12-25 | 2023-04-14 | 中国航空工业集团公司西安飞机设计研究所 | Balance adjusting method and equipment for jacking state of airplane |
| US20220228904A1 (en) * | 2021-01-15 | 2022-07-21 | Gulfstream Aerospace Corporation | Aircraft lifting devices with coupling adapters between jacks and load cells |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3191706A (en) * | 1960-09-06 | 1965-06-29 | Douglas Aircraft Co Inc | Pneumatic support |
| JPS547806Y2 (en) * | 1972-08-12 | 1979-04-11 | ||
| CN2713448Y (en) * | 2004-03-04 | 2005-07-27 | 甘肃省科学院传感技术研究所 | Weight and gravity center measurement device for plane |
| CN103376193A (en) * | 2012-04-17 | 2013-10-30 | 波音公司 | System and method for ground vibration testing and weight and balance measurement |
| CN203785765U (en) * | 2014-04-28 | 2014-08-20 | 山东太古飞机工程有限公司 | Jack-up airplane weighing adaptor |
-
2014
- 2014-04-28 CN CN201410171088.3A patent/CN103954340B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3191706A (en) * | 1960-09-06 | 1965-06-29 | Douglas Aircraft Co Inc | Pneumatic support |
| JPS547806Y2 (en) * | 1972-08-12 | 1979-04-11 | ||
| CN2713448Y (en) * | 2004-03-04 | 2005-07-27 | 甘肃省科学院传感技术研究所 | Weight and gravity center measurement device for plane |
| CN103376193A (en) * | 2012-04-17 | 2013-10-30 | 波音公司 | System and method for ground vibration testing and weight and balance measurement |
| CN203785765U (en) * | 2014-04-28 | 2014-08-20 | 山东太古飞机工程有限公司 | Jack-up airplane weighing adaptor |
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| Publication number | Publication date |
|---|---|
| CN103954340A (en) | 2014-07-30 |
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