CN206394909U - It is a kind of to automatically adjust the aircraft jack for eliminating side force - Google Patents
It is a kind of to automatically adjust the aircraft jack for eliminating side force Download PDFInfo
- Publication number
- CN206394909U CN206394909U CN201621389330.5U CN201621389330U CN206394909U CN 206394909 U CN206394909 U CN 206394909U CN 201621389330 U CN201621389330 U CN 201621389330U CN 206394909 U CN206394909 U CN 206394909U
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- jacking cylinder
- bottom plate
- servo
- force
- servo jacking
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Abstract
The utility model is related to a kind of aircraft jack for automatically adjusting and eliminating side force, it includes bottom plate, two grades of servo jacking cylinders, upper servo jacking cylinder hexagon connector, lower servo jacking cylinder hexagon connector, two anti-fall nuts, force-measuring sensing device assembly, top dome screw rod, and connecting bottom board and upper, three branches of structure identical of lower servo jacking cylinder hexagon connector, three branches circumference uniform distribution on bottom plate and upper servo jacking cylinder hexagon connector, the branch includes servomotor, decelerator, two bearing blocks, screw mandrel, two guide rails, two sliding blocks, slide attachment plate, screw, two ball pivot seats, two the first ball pivots, two struts of drawing money on credit, two short support bars, two the second ball pivots, two the 3rd ball pivots, two revolute pairs.The present invention is simple to operate, saves manpower, eliminates the side force detected, and can change the pose of aircraft using the method for " 3 points " supports.
Description
Technical field
The present invention relates to a kind of aircraft weight and gravity center measurement device, particularly a kind of aircraft jack.
Background technology
In airplane design, experiment, maintenance and flight of aircraft etc., the determination of the weight of aircraft and the position of center of gravity is non-
It is often important, it is especially important especially in its security.With the continuous improvement of aircraft flight speed and height, corresponding aircraft
Center of gravity safe range is also being reduced, therefore the requirement to the measuring system degree of accuracy of aircraft weight center of gravity is also accordingly improved.
It is flat with weighing that the weight of existing survey aircraft and the location method of center of gravity include jack, weighing platform, jack
A variety of methods such as platform combination, wherein jack type measuring method is widely used, and jack type measuring principle is to survey
Force snesor be arranged on jack head, using " 3 points " support methods, by theoretical calculation draw aircraft weight and
Center of gravity.If detecting the information of weight and center of gravity of the aircraft under certain pose, it is desirable to which measurement apparatus, which can not only be crossed, to be known
The support reaction of " 3 points ", and require that measurement apparatus is capable of the pose of coordinated movement of various economic factors change aircraft, but due to aircraft wing stress
Flexible deformation and the adjustment of aspect so that sensor is directly affected the measurement accuracy of system by side force.It is main at present
Installation is rearranged by personnel's experience, it is impossible to realize measurement automate, rapid and precision.Therefore with regard to how to have automatically
The side force that effect is eliminated in measurement process turns into a great problem.
Publication No. CN202508823 U Chinese patent proposes a kind of extendible aircraft jack, the structural volume
Small, simple compact, operation is reliable convenient, stores that floor space is small, solves the problem of transition.But the structure can not be measured and flown
Stressing conditions at the machine strong point, can not also eliminate side force.Chinese patent CN204038956U proposes a kind of mechanical winged
The heavily loaded drive mechanism of the Quick drive mechanism of fast servo mechanism and carrying sleeve is separated by machine jack, the jack,
Fast servo mechanism is enabled quickly to reach target location so that the rise time of the Mechanical type airplane jack can be big
Amplitude shortens.Although the Mechanical type airplane jack can reduce side force, it can not measure and the stress at the aircraft strong point
Situation effectively eliminates side force automatically.Publication No. CN105152067A Chinese patent proposes a kind of main jack of aircraft
Adjusting means, the device can realize that the Level tune and height of the main jack of aircraft are adjusted, simple to operate, can using safety
Lean on.But the device does not have force cell, it is impossible to which effective detection simultaneously eliminates side force.
The content of the invention
It is an object of the invention to provide a kind of aircraft simple to operate, saving manpower for automatically adjusting elimination side force
Jack.
The present invention includes bottom plate, two grades of servo jacking cylinders, upper servo jacking cylinder hexagon connector, lower servo jacking cylinders six
Side shape connector, two anti-fall nuts, force-measuring sensing device assembly, top dome screw rod and connecting bottom board and upper and lower servo jacking cylinder
Three branches of structure identical of hexagon connector, wherein bottom plate have universal wheel and leveling lower margin, described upper and lower two
Servo jacking cylinder hexagon connector is equipped with six hinge ears, and six two, hinge ears are one group and are evenly arranged in upper and lower servo top
Rise on the outside of hexagon cylinder connector, six hinge ears are centrosymmetric, and every group of hinge ear is concentric；Three branches are in bottom plate and upper
Circumference uniform distribution on servo jacking cylinder hexagon connector, the branch include servomotor, decelerator, two bearing blocks, screw mandrel,
It is two guide rails, two sliding blocks, slide attachment plate, screw, two ball pivot seats, two the first ball pivots, two struts of drawing money on credit, two short
Support bar, two the second ball pivots, two the 3rd ball pivots, two revolute pairs, two guide rails are parallel to each other and are fixed on bottom plate, every
It is equipped between sliding block, two sliding blocks and is connected by slide attachment plate on guide rail, on the bottom plate at the two ends in the middle of two guide rails
A bearing block is respectively equipped with, one end of leading screw is connected with the bearing block close to bottom plate center, and its other end passes through another axle
Bearing and the output end of decelerator are connected, and leading screw and guide rail parallel, screw are connected on slide attachment plate and pass through ladder with leading screw
Shape is threadedly coupled；Decelerator is fixed on bottom plate, and servomotor is connected by flange with decelerator, the output end and silk of decelerator
One end connection of bar；Both sides above slide attachment plate are respectively provided with ball pivot seat, and two strut one end of drawing money on credit are respectively by the
One ball pivot is connected with ball pivot seat, and its other end is connected by the hinge ear of the second ball pivot and upper servo jacking cylinder hexagon connector respectively
Connect, one end of two short support bars is connected by revolute pair with strut bottom of drawing money on credit respectively, and its other end passes through the 3rd ball respectively
Cut with scissors and be located at the hinge ear connection of the lower servo jacking cylinder hexagon connector in bottom plate central through hole；Two servo tops up and down
Rise cylinder hexagon connector to be respectively fixedly connected in servo jacking cylinder upper and lower ends, two anti-fall nuts revolve and with outer trapezoidal respectively
In the first order of screw thread, the servo jacking cylinder extension bar of the second level, force-measuring sensing device assembly is embedded in two grades of servo jacking cylinders
The second level is stretched out in boom end, and top dome screw rod is connected by the screw thread of bottom with the screwed hole of centre of force cell.
Described force-measuring sensing device assembly can be replaced by three-dimensional force sensor, can also by with bimoment sensor and
The force-measuring sensing device assembly of force snesor composition is replaced.
It is of the invention to be had the following advantages that compared with existing correlation technique：
1st, force-measuring sensing device assembly sensitive can know the vertical force and horizontal side force situation suffered by top dome screw rod.
2nd, driven by three servomotors, servo jacking cylinder can be made to realize the two-dimensional movement of plane, so as to disappear
Except the side force detected, and the pose of aircraft can be changed using the method for " 3 points " supports.
3rd, using the parallel institution with redundant drive, the rigidity of structure and bearing capacity can be increased.
Brief description of the drawings
Fig. 1 is the three-dimensional simplified schematic diagram of the present invention.
Fig. 2 is the front view simplified schematic diagram of the present invention.
Fig. 3 is the partially schematic sketch of the branch of the present invention.
In figure：1st, bottom plate；2nd, screw；3rd, guide rail；4th, slide attachment plate；5th, the first ball pivot；6th, the 3rd ball pivot；7th, sliding block；
8th, ball pivot seat；9th, bearing block；10th, servomotor；11st, decelerator；12nd, screw mandrel；13rd, draw money on credit strut；14th, short support bar；15th, turn
Dynamic pair；16th, the second ball pivot；17th, anti-fall nut；18th, force-measuring sensing device assembly；19th, heading screw rod；20th, upper servo jacking cylinder six
Side shape connector；21st, servo jacking cylinder；22nd, lower servo jacking cylinder hexagon connector；23rd, leveling lower margin；24th, universal wheel.
Embodiment
In the aircraft jack schematic diagram for automatically adjusting elimination side force shown in Fig. 1, Fig. 2 and Fig. 3, under bottom plate 1
Provided with three universal wheels 24 and three leveling lower margins 23, upper servo jacking cylinder hexagon connector 20 and the lower side of servo jacking cylinder six
Shape connector 22 is equipped with six hinge ears, and six two, hinge ears are one group and are evenly arranged in upper and lower servo jacking hexagon cylinder company
On the outside of fitting, six hinge ears are centrosymmetric, and every group of hinge ear is concentric；Three structure identical branches are in bottom plate and upper servo top
Two guide rails 3 in circumference uniform distribution on liter cylinder hexagon connector, each branch, which are parallel to each other, to be fixed on bottom plate, every guide rail
On be equipped between sliding block 7, two sliding blocks and connected by slide attachment plate 4, on the bottom plate at the two ends in the middle of two guide rails point
Not She You a bearing block 9, one end of leading screw 12 be connected with close to the bearing block at bottom plate center, and its other end is through another axle
Bearing is connected with the output end of decelerator 11, leading screw and guide rail parallel, and screw 2 is connected on slide attachment plate and passed through with leading screw
Trapezoidal thread is connected；Decelerator is fixed on bottom plate, and servomotor 10 is connected by flange with decelerator, the output end of decelerator
It is connected with one end of screw mandrel；Both sides above slide attachment plate are respectively provided with a ball pivot seat 8, two one end of strut 13 difference of drawing money on credit
It is connected by the first ball pivot 5 with ball pivot seat, its other end is connected by the second ball pivot 16 with upper servo jacking cylinder hexagon respectively
The hinge ear connection of part, one end of two short support bar 14 is connected by revolute pair 15 with strut bottom of drawing money on credit respectively, its other end
The hinge ear of the lower servo jacking cylinder hexagon connector by the 3rd ball pivot 6 with being located in bottom plate central through hole is connected respectively；Institute
Two servo jacking cylinder hexagon connectors are respectively fixedly connected in the upper and lower ends of servo jacking cylinder 21 above and below stating, two anti-fall nuts 17
Revolve respectively and on the servo jacking cylinder extension bar of the first order with outer trapezoidal thread, the second level, force-measuring sensing device assembly 18
It is embedded in the second level of two grades of servo jacking cylinders to stretch out in boom end, screw thread and force cell that top dome screw rod 19 passes through bottom
Screwed hole of centre be connected.
Claims (2)
1. a kind of automatically adjust the aircraft jack for eliminating side force, it is characterised in that：It includes bottom plate, two grades of servo jackings
Cylinder, upper servo jacking cylinder hexagon connector, lower servo jacking cylinder hexagon connector, two anti-fall nuts, force cells
Three branches of structure identical of component, top dome screw rod and connecting bottom board and upper and lower servo jacking cylinder hexagon connector,
Wherein bottom plate has universal wheel and leveling lower margin, and upper and lower two servos jacking cylinder hexagon connector is equipped with six
Ear is cut with scissors, six two, hinge ears are one group and are evenly arranged on the outside of upper and lower servo jacking hexagon cylinder connector, during six hinge ears are in
The heart is symmetrical, and every group of hinge ear is concentric；Three branches circumference uniform distribution on bottom plate and upper servo jacking cylinder hexagon connector,
The branch includes servomotor, decelerator, two bearing blocks, screw mandrel, two guide rails, two sliding blocks, slide attachment plate, silks
Female, two ball pivot seats, two the first ball pivots, two struts of drawing money on credit, two short support bars, two the second ball pivots, two the 3rd balls
Hinge, two revolute pairs, two guide rails are parallel to each other and are fixed on bottom plate, are equipped with every guide rail between sliding block, two sliding blocks
Connected by slide attachment plate, a bearing block, one end of leading screw are respectively equipped with the bottom plate at the two ends in the middle of two guide rails
It is connected with the bearing block close to bottom plate center, the output end of its other end through another bearing block and decelerator is connected, leading screw
With guide rail parallel, screw is connected on slide attachment plate and is connected with leading screw by trapezoidal thread；Decelerator is fixed on bottom plate,
Servomotor is connected by flange with decelerator, and the output end of decelerator is connected with screw mandrel one end；Two above slide attachment plate
Side is respectively provided with a ball pivot seat, and two strut one end of drawing money on credit are connected by the first ball pivot with ball pivot seat respectively, its other end difference
It is connected by the second ball pivot with the hinge ear of upper servo jacking cylinder hexagon connector, one end of two short support bars is respectively by turning
Dynamic pair is connected with strut bottom of drawing money on credit, and its other end passes through the 3rd ball pivot and the lower servo top being located in bottom plate central through hole respectively
Rise the hinge ear connection of cylinder hexagon connector；Two servo jacking cylinder hexagon connectors up and down are respectively fixedly connected on servo top
Cylinder upper and lower ends are risen, two anti-fall nuts revolve and the servo jacking cylinder in the first order with outer trapezoidal thread, the second level respectively
On extension bar, force-measuring sensing device assembly is embedded in the second level of two grades of servo jacking cylinders and stretched out in boom end, and top dome screw rod passes through
The screw thread of bottom is connected with the screwed hole of centre of force cell.
2. according to claim 1 automatically adjust the aircraft jack for eliminating side force, it is characterised in that：Described survey
Force sensor module is replaced by three-dimensional force sensor, or the force cell by being constituted with bimoment sensor and force snesor
Component is replaced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621389330.5U CN206394909U (en) | 2016-12-16 | 2016-12-16 | It is a kind of to automatically adjust the aircraft jack for eliminating side force |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621389330.5U CN206394909U (en) | 2016-12-16 | 2016-12-16 | It is a kind of to automatically adjust the aircraft jack for eliminating side force |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206394909U true CN206394909U (en) | 2017-08-11 |
Family
ID=59511136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621389330.5U Expired - Fee Related CN206394909U (en) | 2016-12-16 | 2016-12-16 | It is a kind of to automatically adjust the aircraft jack for eliminating side force |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206394909U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021142557A1 (en) * | 2020-01-19 | 2021-07-22 | 西安方元明科技股份有限公司 | Electric jack and electronic control system thereof |
-
2016
- 2016-12-16 CN CN201621389330.5U patent/CN206394909U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021142557A1 (en) * | 2020-01-19 | 2021-07-22 | 西安方元明科技股份有限公司 | Electric jack and electronic control system thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170811 Termination date: 20211216 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |