CN109987541A - Aircraft intelligent electric machinery jacking apparatus - Google Patents
Aircraft intelligent electric machinery jacking apparatus Download PDFInfo
- Publication number
- CN109987541A CN109987541A CN201910215954.7A CN201910215954A CN109987541A CN 109987541 A CN109987541 A CN 109987541A CN 201910215954 A CN201910215954 A CN 201910215954A CN 109987541 A CN109987541 A CN 109987541A
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- jacking apparatus
- head
- fuselage
- jacking
- sensor
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- 230000000007 visual effect Effects 0.000 claims abstract description 11
- 238000012790 confirmation Methods 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 abstract description 2
- 230000002093 peripheral effect Effects 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 20
- 230000009184 walking Effects 0.000 description 14
- 239000003638 chemical reducing agent Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 230000007423 decrease Effects 0.000 description 4
- 238000012423 maintenance Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000001514 detection method Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 229910052744 lithium Inorganic materials 0.000 description 3
- 239000005955 Ferric phosphate Substances 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 229940032958 ferric phosphate Drugs 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- WBJZTOZJJYAKHQ-UHFFFAOYSA-K iron(3+) phosphate Chemical compound [Fe+3].[O-]P([O-])([O-])=O WBJZTOZJJYAKHQ-UHFFFAOYSA-K 0.000 description 2
- 229910000399 iron(III) phosphate Inorganic materials 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000005303 weighing Methods 0.000 description 2
- 230000010165 autogamy Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F17/00—Safety devices, e.g. for limiting or indicating lifting force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66F—HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD
- B66F3/00—Devices, e.g. jacks, adapted for uninterrupted lifting of loads
- B66F3/46—Combinations of several jacks with means for interrelating lifting or lowering movements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C3/00—Measuring distances in line of sight; Optical rangefinders
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L1/00—Measuring force or stress, in general
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
- G01S17/88—Lidar systems specially adapted for specific applications
- G01S17/93—Lidar systems specially adapted for specific applications for anti-collision purposes
Abstract
Aircraft intelligent electric machinery jacking apparatus, including head jacking apparatus and two fuselage jacking apparatus.Head CCD visual sensor is arranged at the bottom of head jacking apparatus.Fuselage CCD visual sensor is arranged at the bottom of each fuselage jacking apparatus.Head jacking apparatus and fuselage jacking apparatus are respectively I and II jacking apparatus.Head jacking apparatus has head laser range sensor, head horizontal inclinometer, head pressure sensor and head laser obstacle avoidance sensor.Each fuselage jacking apparatus also has multiple sensors above-mentioned.It can be achieved intelligentized motor machine jacking aircraft, and can be according to needing to adjust aspect.Electronic it can be moved to designated position; there is the horizontal measurement function of cooperateing with the laser tracker of ground peripheral hardware and carry out aircraft; there are overload protection and sound-light alarm prompt facility by pressure sensor; there is emergency stop and enters position confirmation function; be reduced lateral load function, at the same be equipped with corresponding plug can realize between each equipment it is quick connection and separate.
Description
Technical field
The invention belongs to aircraft support equipment technical fields, more particularly to aircraft intelligent electric machinery jacking apparatus.
Background technique
Airplane lifting-up device is the indispensable equipment of aircraft support equipment.Airplane ground support equipment ensures flight peace in army
Entirely, it completes to play very important effect in training combat duty, to work such as maintenance, maintenance, the dismounting for realizing aircraft floor
With indispensable role.And type, the quantity of airplane lifting-up device are various at present, it is many not to maintenance support work belt
Just, the needs of aircraft equipment development are not suitable with.Existing airplane lifting-up device is mostly hand-hydraulic jacking system, easy oil leakage, Yi Fa
Raw hydraulic system fault, personnel's operation, which is compared, to cumber, and the time is long, low efficiency.With the progress of aviation industry, aircraft is protected
Hinder the function of equipment, performance indicator requires all in the continuous improvement.It needs to research and develop the aircraft for being more suitable for modern weapons equipment Development
Support Equipment.
Summary of the invention
The object of the present invention is to provide aircraft intelligent electric machinery jacking apparatus, structure advanced and reasonable design meets more
The jacking of kind aircraft model, it is easy to operate practical, improve aircraft repair and maintenance efficiency.
The technical solution adopted is that:
Aircraft intelligent electric machinery jacking apparatus, including head jacking apparatus and two fuselage jacking apparatus.
Technical points are:
Head CCD visual sensor is equipped in the bottom of head jacking apparatus.
Fuselage CCD visual sensor is equipped in the bottom of each fuselage jacking apparatus.
Head jacking apparatus is level-one jacking apparatus, and two fuselage jacking apparatus are secondary jacking-up device.
Head laser range sensor is equipped in the handpiece support outer barrel surface of head jacking apparatus.
Fuselage laser range sensor is equipped in the supporting fuselage outer barrel surface of each fuselage jacking apparatus.
Head horizontal inclinometer is equipped in the handpiece support outer barrel surface of head jacking apparatus.
Standard of fuselage inclinator is equipped in the supporting fuselage outer barrel surface of each fuselage jacking apparatus.
There is head pressure sensor in the bottom of head jacking apparatus.
Fuselage pressure sensor is equipped in the bottom of each fuselage jacking apparatus.
Head laser obstacle avoidance sensor is set in the bottom of head jacking apparatus.
Fuselage laser obstacle avoidance sensor is all provided in the bottom of each fuselage jacking apparatus.
The advantage is that:
The present apparatus can realize intelligentized motor machine jacking aircraft, and can be adjusted as needed to aspect.Have
The function what designated position jacks up aircraft is taken office in electronic movement, winged with cooperateing with use to carry out with the laser tracker of ground peripheral hardware
The horizontal measurement function of machine, having has overload protection and sound-light alarm prompt facility by pressure sensor, has emergency stop and enters
Position confirmation function, have the function of reduce lateral load, while be equipped with corresponding plug can realize between each equipment it is quick connect and
Separation.The side of bus communication is used between the master controller and master controller of the control system, master controller and other units
Formula is communicated.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the present invention with aircraft cooperation position.
Fig. 2 is single unit system schematic diagram of the present invention.
Fig. 3 is head jacking apparatus structure chart in the present invention.
Fig. 4 is the lifting body cross-sectional view of head jacking apparatus in the present invention.
Fig. 5 is head omni-directional wheel vehicle with walking machine composition in the present invention.
Fig. 6 is head lower margin (levelling mechanism and Weighing module) structure chart of head jacking apparatus in the present invention.
Head jacking apparatus (preceding jacking apparatus) 1, fuselage jacking apparatus (main jacking apparatus) 2, head jacking apparatus are automatically controlled
Case 3, fuselage jacking apparatus electric cabinet 4, hand-held remote control unit 5(are wired), head tripod supporting mechanism 6, head lifting body
7, head omni-directional wheel walking mechanism 8, head lower margin 9(head levelling mechanism), head detachable battery packet 10, head manually handle
Take turns 11, head horizontal inclinometer 12, head laser obstacle avoidance sensor 13, head CCD visual sensor 14, handpiece support outer cylinder
15, head jacking cylinder 16, head rotating lead screw 17, head come directly towards 18, head with jacking motor 19, laser tracker 20, head
Foot manual lever 21, fuselage come directly towards 22, head laser range sensor 23, head pressure sensor 24.
Specific embodiment
Aircraft intelligent electric machinery jacking apparatus, including head jacking apparatus 1 and two fuselage jacking apparatus 2.
Head jacking apparatus 1 is level-one jacking apparatus, and two fuselage jacking apparatus 2 can be secondary jacking-up device.
It is known technology (jack).
1 primary structure of head jacking apparatus is as follows: head jacking apparatus 1 includes being vertically provided at head tripod support machine
The head lifting body 7 of structure 6, the head omnidirectional wheel carrier of 6 bottom of head tripod supporting mechanism three are respectively arranged with three heads
Omni-directional wheel walking mechanism 8,6 bottom of head tripod supporting mechanism are additionally provided with three head lower margins 9.Head jacking apparatus electric cabinet
3 are arranged in head tripod supporting mechanism 6 lower support portion, while lower support portion is additionally provided in head tripod supporting mechanism 6
Head detachable battery packet 10.
Head CCD visual sensor 14 is equipped on the chassis of a head lower margin 9.
It is equipped with head laser range sensor 23 on 15 surface of handpiece support outer cylinder of head lifting body 7, for measuring
The head of head lifting body 7 comes directly towards 18 positions.
Head horizontal inclinometer 12 is equipped on 15 surface of handpiece support outer cylinder of head lifting body 7.
Head pressure sensor 24 is equipped on the chassis of each head lower margin 9.
Head laser obstacle avoidance sensor 13 is equipped on the chassis of each head lower margin 9.
Head CCD visual sensor 14, head horizontal inclinometer 12, head laser range sensor 23, head pressure pass
Sensor 24 and head laser obstacle avoidance sensor 13 are correspondingly connected with the master controller (PLC) in head jacking apparatus electric cabinet 3.
The servo motor of head omni-directional wheel walking mechanism 8, the servo motor of head lower margin 9 and head jacking motor 19 are jacked with head
Master controller in device electric cabinet 3 is correspondingly connected with.
Each fuselage jacking apparatus 2 includes the fuselage lifting body for being vertically provided at fuselage tripod supporting mechanism, machine
The fuselage omnidirectional wheel carrier of body tripod supporting mechanism bottom three is respectively arranged with three fuselage omni-directional wheel walking mechanisms, three foot of fuselage
Frame supporting mechanism bottom is additionally provided with three fuselage lower margins.Fuselage jacking apparatus electric cabinet 4 is arranged in fuselage tripod supporting mechanism
In lower support portion, while lower support portion is additionally provided with fuselage detachable battery packet in fuselage tripod supporting mechanism.
The chassis of a fuselage lower margin in each fuselage jacking apparatus 2 is equipped with fuselage CCD visual sensor.
The supporting fuselage outer barrel surface of each fuselage lifting body is equipped with fuselage laser range sensor.
Standard of fuselage inclinator is equipped in the supporting fuselage outer barrel surface of each fuselage lifting body.
Fuselage pressure sensor is equipped on the chassis of each fuselage lower margin of each fuselage jacking apparatus 2.
Fuselage laser obstacle avoidance sensor is equipped on the chassis of each fuselage lower margin of each fuselage jacking apparatus 2.
Fuselage CCD visual sensor, standard of fuselage inclinator, fuselage laser ranging on each fuselage jacking apparatus 2 pass
The fuselage jacking apparatus of sensor, fuselage pressure sensor and fuselage laser obstacle avoidance sensor with the fuselage jacking apparatus 2 at place
Master controller (PLC) in electric cabinet 4 is correspondingly connected with, while lower support portion is also equipped in each fuselage tripod supporting mechanism
Fuselage detachable battery packet.
Head jacking apparatus electric cabinet 3 and two fuselage jacking apparatus electric cabinets 4 are correspondingly connected with, and can be communicated with each other.
Head detachable battery packet 10 is watched to three omni-directional wheels of head jacking apparatus electric cabinet 3 and head jacking apparatus
Take the power supplies such as motor, the servo motor of lower margin and head jacking motor 19.
Three omni-directional wheel, lower margins of the fuselage detachable battery packet to fuselage jacking apparatus electric cabinet 4 and fuselage jacking apparatus 2
The power supply such as motor is jacked with fuselage.
Whole omni-directional wheel walking mechanisms and lower margin are commercially available known product.
Multiple pressure sensors measure jacking apparatus to the active force of aircraft, and multiple pressure sensors also can determine whether to act on
Power whether unbalance loading.
Walking mechanism: the walking chassis of three motor machine jacking apparatus is designed to tripod structure, it is ensured that device exists
It is not collided with undercarriage in use process.Walking function, the installation direction of three omni-directional wheels are completed using three omni-directional wheels
It is mutually 120 ° of angles.Each omni-directional wheel is controlled respectively by the servo motor of omni-directional wheel and generates different revolving speeds, can make to walk
Chassis is mobile to any direction, and is able to achieve the rotation of 360 ° of original place.Jacking apparatus can electronic movement what specific bit top set taken office
Play aircraft.Design and operation 0~2km/h of speed, and be continuously adjusted, each omni-directional wheel has braking parking function.
The servomotor, gear reducer of omni-directional wheel, conical gear commutator, omni-directional wheel have independent transmission shaft
All it is fixed on omnidirectional's wheel carrier.When the engagement of omni-directional wheel clutch, lower margin clutch disconnect, servo motor and speed reducer
Drive omni-directional wheel rotation that chassis is made to walk.After chassis reaches specified position, omni-directional wheel clutch is disconnected, and lower margin clutch connects
It closes, servo motor and speed reducer drive and drive the lifting of lower margin lead screw by conical gear commutator, fix lower margin on the ground
And the levelness on chassis is adjusted according to horizontal inclinometer.Lower margin can also by head lower margin manual lever 21 or fuselage
Foot manual lever manually controls the lifting of lower margin.
Three jacking apparatus walkings are responsible for there are also driving unit and lifting task provides driving force, and lifting part is by high-precision
Close lead screw and servo motor are constituted.Servo-system is the positioning and high-precision lifting task in jacking apparatus realization walking process
Provide guarantee.Servo-system selects commercially available international top-brand to be specifically applied to the servo-system of standard movement control, is conducive to mention
Machinery equipment performance is risen, development cost is reduced.
Jacking system: since the impulse stroke of head jacking apparatus 1 is smaller with respect to minimum altitude, it can satisfy level-one silk
The range demands of thick stick transmission lifting.Therefore, space allows the lifting of head jacking apparatus 1 to use level-one lead screw transmission, lower part machine
Head 17 rotate driving lower part screw of rotating threaded shaft and head jacking cylinder 16 are vertically moved up or down.Head hand control wheel can be manually operated
11 or fuselage top is driven 18 to move up and down by head jacking motor 19.
Since the impulse stroke of fuselage jacking apparatus 2 is bigger with respect to minimum altitude, single-stage lead screw cannot be met the requirements.Cause
The lifting of fuselage jacking apparatus 2 is designed to second level lead screw transmission by this.The primary structure of this fuselage jacking apparatus 2 is known skill
Art: fuselage jacks motor reducer and drives the rotation of lower part lead screw, goes up and down lower part screw along lower part lead screw.Lower part screw is in
Between sleeve connection it is integral, limiting intermediate sleeve and lower part screw with key on shell makes it not rotate.Free-sliding spline axis can
To slide up and down, lower part lead screw drives upper spindle rotation by free-sliding spline axis, because of intermediate sleeve screw and intermediate sleeve
It is fixed together and does not rotate, so upper spindle can also generate lifting.It is installed between fuselage top 22 and upper spindle
Thrust bearing guarantees not rotate when fuselage top 22 is contacted with aircraft.Speed reducer tool there are two input shaft, grasp manually by fuselage
Vertical pole is manually entered axis with speed reducer by ratchet mechanism, clutch and is connected, and the lifting of jacking apparatus be manually operated can also.
Fuselage manual joystick can disassemble when not in use.
Three jacking apparatus have the function of precise synchronization jacking, decline, and 0~120mm/min of lifting speed is continuously adjusted.
It is horizontal
The power supply of power unit detachable battery packet: motor machine jacking apparatus provides electric energy power supply, ferric phosphate using lithium storage battery
Lithium battery has the characteristics that capacity is big, light-weight, the service life is long, environmentally friendly, and cruising ability is not less than 2h.Three jacking apparatus are respectively taken
One ferric phosphate lithium cell packet of band, while the battery pack allows to be removed interim access 220V/380V electrical source of power, battery pack
The fixed latching device for using fast demountable of installation.It can quickly be unloaded when battery capacity deficiency and change electricity abundance
Battery work.Battery pack uses AC220V/380V charger, is suitable for common power source charges.Equipment is directly connected to electricity
Source can carry out quick charge, without connecting charger.Motor machine jacking apparatus has power conductor seat simultaneously, can be directly accessed
AC220V power outlet, drive motor tool jacking apparatus work normally.Each battery pack is carried out by respective battery management system
Charge and discharge control improves the utilization rate of battery, prevents from overcharging and discharge, can be timely in the case where short circuit occurs for battery
Cutting output prevents from causing fire.
Man-machine unit: the touch screen of hand-held remote controller 5 and its touch screen and three electric cabinets, hand-held remote controller 5 is to push up
It rises the control of device walking process and manually controlling for lifting, each touch screen can be in show three jacking apparatus
Work state information and running parameter setting.
It reduces lateral load: being equipped with horizontal inclinometer on each jacking apparatus, every three lower margins pass through lower margin servo
Motor automatically adjusts levelness, reduces jacking apparatus lateral load, guarantees that three jacking apparatus are same by laser range sensor
Step jacks and decline function, and pressure sensor is housed on chassis.Jacking apparatus be can measure to the active force of aircraft and judged whether
Unbalance loading can realize reduction lateral force by above-mentioned measure.
Detection unit is by nine laser obstacle avoidance sensors, three laser range sensors, three horizontal inclinometers, nine pressure
Sensor Weighing module and CCD vision system (finding top nest) are constituted, and are completed the protection in jacking apparatus walking process, are gone up and down
The tasks such as positioning, pose adjustment, state-detection in journey.
Head top 18 is for corresponding to the head top nest of airframe lower part, and two fuselage tops 22 are for corresponding to aircraft machine
The fuselage top nest of body lower part.
Every set jacking apparatus master controller is installed among corresponding jacking apparatus, and it is respective that each master controller is responsible for control
The jacking and decline of corresponding jacking apparatus, any jacking apparatus can individually control lifting, can also to three jacking apparatus or
Two of them jacking apparatus controls lifting simultaneously, and can be adjusted as needed to aspect, according to laser tracker 20
Data control the jacking of three jacking apparatus and decline or aspect be adjusted as needed.
Described control unit is the control core of entire aircraft intelligent electric jack-up system, is responsible for three jackings of dispatching distribution
The walking of device, lifting task carry out overall monitor to the working condition of system.Each autogamy of the control unit of three jacking apparatus
There is PLC master controller as Body Controller, in executing synchronous lifting/lowering task work, the master controller of head jacking apparatus 1
It can be designated as coordinated scheduling controller, undertake the coordination of tasks of three jacking apparatus adjustable heights, speed, hand-held remote control unit
5 are connect by cable with the master controller of head jacking apparatus 1.
The aircraft intelligent electric machinery jacking apparatus passes through single by power unit, driving unit, man-machine unit, detection
The control system of the compositions such as member and control unit completes everything.By the carrying energy for changing single motor machinery jacking apparatus
Power and minimum altitude and impulse stroke, that is, be suitable for the needs of different type of machines.
Head jacking apparatus 1 and two fuselage jacking apparatus pass through corresponding cable connecting communication, can be by line after the completion of work
Cable is deposited in head jacking apparatus electric cabinet 4.
Claims (6)
1. aircraft intelligent electric machinery jacking apparatus, including head jacking apparatus (1) and two fuselage jacking apparatus (2)；It is special
Sign is:
Head CCD visual sensor (14) is equipped in the bottom of head jacking apparatus (1)；
Fuselage CCD visual sensor is equipped in the bottom of each fuselage jacking apparatus (2).
2. aircraft intelligent electric machinery jacking apparatus according to claim 1, it is characterised in that:
Head jacking apparatus (1) is level-one jacking apparatus, and two fuselage jacking apparatus (2) are secondary jacking-up device.
3. aircraft intelligent electric machinery jacking apparatus according to claim 1, it is characterised in that: in head jacking apparatus
(1) handpiece support outer cylinder (15) surface is equipped with head laser range sensor (23)；
Fuselage laser range sensor is equipped in the supporting fuselage outer barrel surface of each fuselage jacking apparatus (2).
4. aircraft intelligent electric machinery jacking apparatus according to claim 1, it is characterised in that: in head jacking apparatus
(1) handpiece support outer cylinder (15) surface is equipped with head horizontal inclinometer (12)；
Standard of fuselage inclinator is equipped in the supporting fuselage outer barrel surface of each fuselage jacking apparatus (2).
5. aircraft intelligent electric machinery jacking apparatus according to claim 1, it is characterised in that: in head jacking apparatus
(1) bottom is equipped with head pressure sensor (24)；
Fuselage pressure sensor is equipped in the bottom of each fuselage jacking apparatus (2).
6. aircraft intelligent electric machinery jacking apparatus according to claim 1, it is characterised in that: in head jacking apparatus
(1) bottom sets head laser obstacle avoidance sensor (13)；
Fuselage laser obstacle avoidance sensor is all provided in the bottom of each fuselage jacking apparatus (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910215954.7A CN109987541A (en) | 2019-03-21 | 2019-03-21 | Aircraft intelligent electric machinery jacking apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910215954.7A CN109987541A (en) | 2019-03-21 | 2019-03-21 | Aircraft intelligent electric machinery jacking apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109987541A true CN109987541A (en) | 2019-07-09 |
Family
ID=67129141
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910215954.7A Withdrawn CN109987541A (en) | 2019-03-21 | 2019-03-21 | Aircraft intelligent electric machinery jacking apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109987541A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111177964A (en) * | 2019-12-25 | 2020-05-19 | 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 |
| CN112194034A (en) * | 2020-08-12 | 2021-01-08 | 广州飞机维修工程有限公司 | Method for integrally jacking airplane |
| CN114235374A (en) * | 2021-12-22 | 2022-03-25 | 上海无线电设备研究所 | Durability test device and method for airplane cabin door mechanism |
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| CN109368529A (en) * | 2018-12-10 | 2019-02-22 | 长沙市天映机械制造有限公司 | A kind of jack device for airframe jacking |
| CN209797364U (en) * | 2019-03-21 | 2019-12-17 | 沈阳飞研航空设备有限公司 | Intelligent electric mechanical jacking device for airplane |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111177964A (en) * | 2019-12-25 | 2020-05-19 | 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 |
| 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 |
| CN112194034A (en) * | 2020-08-12 | 2021-01-08 | 广州飞机维修工程有限公司 | Method for integrally jacking airplane |
| CN112194034B (en) * | 2020-08-12 | 2022-11-22 | 广州飞机维修工程有限公司 | Method for integrally jacking airplane |
| CN114235374A (en) * | 2021-12-22 | 2022-03-25 | 上海无线电设备研究所 | Durability test device and method for airplane cabin door mechanism |
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Application publication date: 20190709 |