CN205241146U - Jacking formula airborne vehicle weighing -appliance adapter - Google Patents
Jacking formula airborne vehicle weighing -appliance adapter Download PDFInfo
- Publication number
- CN205241146U CN205241146U CN201521091578.9U CN201521091578U CN205241146U CN 205241146 U CN205241146 U CN 205241146U CN 201521091578 U CN201521091578 U CN 201521091578U CN 205241146 U CN205241146 U CN 205241146U
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- CN
- China
- Prior art keywords
- jack
- pedestal
- screw
- flange
- lead screw
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The utility model provides a jacking formula airborne vehicle weighing -appliance adapter, including the shaft jack, the vertical jack lead screw that sets up on the shaft jack and setting up in the roof on jack lead screw top, include still that two and half bushes and bottom opening are tubular structure's base, the relative lock of two and half bushes forms a cylinder structure, the internal diameter of half bush and the external diameter phase -match of jack lead screw, the external diameter of half bush matches with the external diameter homogeneous phase of the internal diameter of base and roof, the base upper end is provided with the thread head that is used for connecting the load transducer, two and half bush locks are the back outside the jack lead screw, the base cartridge is on two and half bushes and through the fastener fastening. The hole and the jack lead screw of two and half bushes contact, the hole of base and the contact of the outer wall of two and half bushes, and the connection position becomes the face contact by the point contact of traditional equipment, and consequently the situation that the jack is deviate from to the aircraft can not take place for it when measuring at the load transducer, has improved the measuring reliability.
Description
Technical field
The utility model relates to a kind of jacking type aircraft weight device adapter.
Background technology
The AC-121-68 of Civil Aviation Administration of China requires every 36 months of airborne vehicle operator to weigh to obtain the data of airborne vehicle bare weight and bare weight position of centre of gravity accurately to airborne vehicle, then by control and calculating to airborne passenger-cargo amount, guarantee aircraft in flight course weight and center of gravity in the scope limiting, to ensure flight safety. The form of aircraft weight has multiple, and uses wheel shaft jacking type weight method to be one wherein. Its implementation is: place load transducer at airborne vehicle wheel wheel shaft fulcrum, the rear wheel shaft screw jack that utilizes is by airborne vehicle jack-up, and the weight data sum of each sensor is aircraft gross weight; Again by calculating the weight center of gravity that can draw aircraft.
First above-mentioned weighting manner needs the problem solving is exactly how the load transducer of weighing-appliance to be assembled to wheel shaft screw jack safely. Once because assemble insecure or in aircraft jacking process application of force deflection, sensor may be thrown off from jack, causes jack top to wear aircraft, the maintenance cost of this kind of situation is huge, causes great economic loss to airborne vehicle operator.
Summary of the invention
The utility model is in order to overcome the deficiency of above technology, and a kind of use safety, jacking type aircraft weight device adapter are easily provided.
The utility model overcomes the technical scheme that its technical problem adopts:
A kind of jacking type aircraft weight device adapter, comprise wheel shaft screw jack, vertically be arranged at the jack leading screw on wheel shaft screw jack and be arranged at the top board on jack leading screw top, also comprise that two and half linings and bottom opening are the pedestal of tubular construction, two and half linings relatively fasten and form a cylindrical structure, the external diameter of the internal diameter of described half lining and jack leading screw matches, the external diameter of the external diameter of described half lining and the internal diameter of pedestal and top board all matches, described pedestal upper end is provided with the thread head for connecting load transducer, two and half linings are fastened on the outer rear flank of jack leading screw, pedestal 7 is plugged on two and half linings also fastening by fastener.
Above-mentioned fastener comprises the flange I that is arranged at half lining lower end and the flange II that is arranged at pedestal lower end, in described flange II, be provided with some through holes, in described flange I, correspondence is provided with some screws, and screw is connected and fixed flange II and flange I through being combined in screw after through hole.
In order further to improve the fix tightly soundness between two and half linings, also comprise two symmetrically and level is combined on pedestal side holding screw
The beneficial effects of the utility model are: the endoporus of two and half linings contacts with jack leading screw, the endoporus of pedestal contacts with the outer wall of two and half linings, connecting portion becomes face contact by the some contact of legacy equipment, therefore in load transducer its situation that aircraft can not occur and deviate from jack in the time measuring, improved the reliability of measuring.
Brief description of the drawings
Fig. 1 is perspective view of the present utility model;
Fig. 2 is three-dimensional blast structure chart of the present utility model;
In figure, 1. wheel shaft screw jack 2. jack leading screw 3. top board 4. half lining 5. flange I 6. screw 7. pedestal 8. flange II 9. through hole 10. thread head 11. screw 12. holding screw 13. load transducers.
Detailed description of the invention
Below in conjunction with accompanying drawing 1, accompanying drawing 2, the utility model is described further.
A kind of jacking type aircraft weight device adapter, comprise wheel shaft screw jack 1, be vertically arranged at the jack leading screw 2 on wheel shaft screw jack 1 and be arranged at the top board 3 on jack leading screw 2 tops, also comprise that two and half linings 4 and bottom opening are the pedestal 7 of tubular construction, two and half linings 4 relatively fasten and form a cylindrical structure, the external diameter of the internal diameter of half lining 4 and jack leading screw 2 matches, the external diameter of the internal diameter of the external diameter of half lining 4 and pedestal 7 and top board 3 all matches, and pedestal 7 upper ends are provided with the thread head 10 for connecting load transducer 13. When use, wheel shaft screw jack 1 is positioned over to the level ground of aircraft weighting relevant position and jack leading screw 2 that its hydraulic pressure is stretched out is down to minimum. Two and half linings 4 are fastened on jack leading screw 2 outsides, now the upper end of two and half linings 4 is positioned at the lower end of top board 3, therefore two and half linings 4 form a complete cylinder with top board 3, and pedestal 7 is plugged on two and half linings 4 and top board 3 also fastening by fastener. Because the endoporus of two and half linings 4 contacts with jack leading screw 2, the endoporus of pedestal 7 contacts with the outer wall of two and half linings 4, connecting portion becomes face contact by the some contact of legacy equipment, therefore in load transducer 13 its situation that aircraft can not occur and deviate from jack in the time measuring, improved the reliability of measuring.
Fastener can be following structure, it comprises the flange II 8 that is arranged at the flange I 5 of half lining 4 lower ends and is arranged at pedestal 7 lower ends, in flange II 8, be provided with some through holes 9, in flange I 5, correspondence is provided with some screws 6, screw 11 is connected and fixed flange II 8 and flange I 5 through being combined on after through hole 9 in screw 6, therefore realized being connected and fixed of pedestal 7 and two and half linings 4, simple in structure, easy for installation. Further, can also comprise two symmetrically and level is combined on pedestal 7 side holding screws 12, two holding screws 12 of both sides can fixedly secure two and half linings 4 respectively, have further improved steadiness.
Claims (3)
1. a jacking type aircraft weight device adapter, comprise wheel shaft screw jack (1), vertically be arranged at the jack leading screw (2) on wheel shaft screw jack (1) and be arranged at the top board (3) on jack leading screw (2) top, it is characterized in that: also comprise that two and half linings (4) and bottom opening are the pedestal (7) of tubular construction, two and half linings (4) relatively fasten and form a cylindrical structure, the external diameter of the internal diameter of described half lining (4) and jack leading screw (2) matches, the external diameter of the internal diameter of the external diameter of described half lining (4) and pedestal (7) and top board (3) all matches, described pedestal (7) upper end is provided with the thread head (10) for connecting load transducer (13), two and half linings (4) are fastened on the outer rear flank of jack leading screw (2), pedestal (7) is plugged in that two and half linings (4) are gone up and to pass through fastener fastening.
2. jacking type aircraft weight device adapter according to claim 1, it is characterized in that: described fastener comprises the flange II (8) that is arranged at the flange I (5) of half lining (4) lower end and is arranged at pedestal (7) lower end, in described flange II (8), be provided with some through holes (9), the upper correspondence of described flange I (5) is provided with some screws (6), and screw (11) is connected and fixed flange II (8) and flange I (5) through being combined on after through hole (9) in screw (6).
3. jacking type aircraft weight device adapter according to claim 1 and 2, is characterized in that: also comprise two symmetrically and level is combined on pedestal (7) side holding screw (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521091578.9U CN205241146U (en) | 2015-12-25 | 2015-12-25 | Jacking formula airborne vehicle weighing -appliance adapter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521091578.9U CN205241146U (en) | 2015-12-25 | 2015-12-25 | Jacking formula airborne vehicle weighing -appliance adapter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205241146U true CN205241146U (en) | 2016-05-18 |
Family
ID=55940225
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521091578.9U Expired - Fee Related CN205241146U (en) | 2015-12-25 | 2015-12-25 | Jacking formula airborne vehicle weighing -appliance adapter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205241146U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989807A (en) * | 2017-06-09 | 2017-07-28 | 中航通飞华南飞机工业有限公司 | A kind of aircraft weighting system |
| CN107738223A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing |
-
2015
- 2015-12-25 CN CN201521091578.9U patent/CN205241146U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106989807A (en) * | 2017-06-09 | 2017-07-28 | 中航通飞华南飞机工业有限公司 | A kind of aircraft weighting system |
| CN107738223A (en) * | 2017-11-13 | 2018-02-27 | 山东太古飞机工程有限公司 | The dismounting auxiliary mould of aircraft engine first order stator blade radome fairing |
| CN107738223B (en) * | 2017-11-13 | 2023-11-10 | 山东太古飞机工程有限公司 | Auxiliary assembly and disassembly tool for fairing of first-stage stator blade of aircraft engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160518 Termination date: 20211225 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |