CN103616150B - Aircraft air spring lifting bearing - Google Patents
Aircraft air spring lifting bearing Download PDFInfo
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- CN103616150B CN103616150B CN201310652620.9A CN201310652620A CN103616150B CN 103616150 B CN103616150 B CN 103616150B CN 201310652620 A CN201310652620 A CN 201310652620A CN 103616150 B CN103616150 B CN 103616150B
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- air spring
- lifting
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Abstract
The invention belongs to aircraft suspension support technology, be specifically related to a kind of aircraft air spring lifting bearing.Aircraft air spring lifting bearing of the present invention includes Hydraulic Station, hydraulic lifting cylinder, base, and auxiliary supports, air spring mounting base, control valve group, displacement transducer.Described air spring mounting base is circular flange structure, it is arranged on base, for installing air spring, three hydraulic pressure sound fall cylinders and three auxiliary support spaced around air spring setting, and be evenly distributed on air spring mounting base, it addition, hydraulic lifting pressurized strut is provided with control valve group and is connected with Hydraulic Station, displacement transducer is arranged on hydraulic lifting pressurized strut sidewall.Large aircraft air spring Special lifting bearing of the present invention achieves large aircraft 3 synchronization liftings in rest, greatly reduces the risk of aircraft rest, has high safety and reliability.
Description
Technical field
The invention belongs to aircraft suspension support technology, be specifically related to a kind of aircraft air spring liter
Descending branch seat.
Background technology
Rest suspension technology when aircraft suspension support technology is airplane ground test, is used for simulating
Aircraft freedom-free state aloft.Existing aircraft suspension support technology mainly uses band leading screw
Lifting pedestal and fax formula lifting pedestal.And the lifting pedestal of band leading screw is mainly by rotating
Leading screw reaches the purpose of lifting, and shortcoming is: 1) time-consuming, laborious (by manpower rotating wire
Thick stick)；2) inapplicable to large-tonnage aircraft；3) can not 3 synchronization liftings；4) poor stability.
Fax formula lifting pedestal mainly reaches the purpose of lifting by driven by motor rotating threaded shaft, lacks
Point is: inapplicable to large-tonnage aircraft.
Present generation aircraft Ground Vibration Test requires that aircraft is got off the plane can freely rise at suspension rest
Fall, the jacking system that the past develops can not meet the requirement that present generation aircraft suspension is supported, therefore
It is badly in need of a kind of type aircraft rest equipment that disclosure satisfy that present generation aircraft Ground Vibration Test requirement.
Summary of the invention
The object of the invention: provide one can by automatically controlling, 3 synchronization liftings realize flying
The aircraft air spring lifting bearing that machine suspension is supported.
Technical scheme: a kind of aircraft air spring lifting bearing, it includes Hydraulic Station,
Hydraulic lifting cylinder, base, auxiliary supports, air spring mounting base, control valve group, displacement
Sensor, described air spring mounting base is circular flange structure, is arranged on base, uses
In installing air spring, three hydraulic pressure sound fall cylinders and three auxiliary support spaced around air
Spring is arranged, and is evenly distributed on air spring mounting base, it addition, hydraulic lifting start
Cylinder is provided with control valve group and is connected with Hydraulic Station, and displacement transducer is arranged on hydraulic lifting and makees
Dynamic cylinder sidewall.
Described base lower end is provided with reinforcement.
Described three hydraulic lifting pressurized struts are all connected to industrial computer by respective control valve group, with
Realize base synchronization lifting.
Described auxiliary is supported for three silks stood upside down and shoulders, and is connected with base with bolt, and uses motor
Drive.
The technique effect of the present invention: compared with prior art, large aircraft air spring of the present invention
Special lifting bearing achieves large aircraft 3 synchronization liftings in rest, greatly reduces and flies
The risk of machine rest, has high safety and reliability.Improve large aircraft simultaneously
Rest efficiency, makes the time used by rest aircraft shorten more than one times, and operation is very flexible,
Convenient, play liter weight big.Fully meet support requirement during large aircraft Ground Vibration Test,
There is in aircraft development bigger using value.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft air spring lifting bearing of the present invention；
Wherein, 1 hydraulic lifting cylinder be, 2 for air spring mounting base, 3 bases, 4 auxiliary
Support, 5 be control valve group, 6 be displacement transducer, 7 Hydraulic Stations.
Detailed description of the invention
Below in conjunction with embodiment and accompanying drawing, the present invention is described further:
Aircraft air spring lifting bearing of the present invention includes Hydraulic Station, hydraulic lifting cylinder, base,
Auxiliary supports, air spring mounting base, control valve group, displacement transducer.
Described air spring mounting base is circular flange structure, is arranged on base, is used for pacifying
Dress air spring, three hydraulic pressure sound fall cylinders and three auxiliary support spaced around air spring
Arrange, and be evenly distributed on air spring mounting base, it addition, hydraulic lifting pressurized strut is equal
Being provided with control valve group and be connected with Hydraulic Station, displacement transducer is arranged on hydraulic lifting pressurized strut
Sidewall.
Described base lower end is provided with reinforcement in order to increase air spring lifting support
Intensity, it is ensured that requirement of strength during large-tonnage aircraft rest.
Described three hydraulic lifting pressurized struts are all connected to industrial computer by respective control valve group, enter
Row Synchronization Control, to realize base synchronization lifting.
Described auxiliary is supported for three silks stood upside down and shoulders, and is connected with base with bolt, and uses motor
Drive.
Hydraulic lifting cylinder 1, quantity is three, uses the mode bolt stood upside down to be connected with base,
Lifting for base provides power, it is achieved that the requirement of adjustable height 400mm.
Air spring mounting base 2, structure is flange, is bolted on base, uses
Air spring is installed；
Base 3, is the agent structure of whole system, and other parts are mainly integrated on base.
Auxiliary support 4, is that three silks stood upside down are shouldered, is connected with base with bolt, and uses motor
Drive, during rest aircraft, play servo-actuated protective effect；
Control valve group 5, quantity is three, is bolted on base, and and Hydraulic Station,
Hydraulic lifting cylinder connects, and Main Function is to control the lifting of each hydraulic lifting cylinder；
Displacement transducer 6, is connected with hydraulic lifting cylinder, measures hydraulic lifting cylinder lifting height in real time
Degree.
Hydraulic Station 7, is connected with base by bolt, provides pressure for hydraulic lifting cylinder.
In system operation, bottom controller is by displacement, the inspection of pressure sensor signal
Survey and realize the hydraulic lifting cylinder leveling of system, lifting tube isolated operation, enter a control, synchronization top
Rise control, synchronize to transfer control, and by bus mode, system operation information is transferred to upper
Machine.Industrial computer receives the signal from bottom controller by bus mode, and system is run shape
State is monitored and shows, sends command adapted thereto simultaneously.
Open industrial computer, start air spring lifting support control system, and start air bullet
Spring bearing, all parts are in preparation state, control three hydraulic actuators and three auxiliary
Support work, auxiliary support is helped to be set to servo-actuated state.System sends instructions three to hydraulic actuator
Individual hydraulic actuator rises 20mm, clicks on and performs, and hydraulic actuator begins to ramp up.Assist simultaneously
Support is followed hydraulic actuator and is protected, and the displacement transducer display on hydraulic actuator rises
Displacement.Base plane rises with hydraulic actuator, when displacement transducer display displacement is 30mm,
Hydraulic actuator and auxiliary are supported to stop rising, and at this moment close air spring lifting support, complete
One-off.
Claims (4)
1. an aircraft air spring lifting bearing, it is characterised in that include Hydraulic Station, hydraulic pressure
Lifting pressurized strut, base, auxiliary supports, air spring mounting base, control valve group, displacement
Sensor, described air spring mounting base is circular flange structure, is arranged on base, uses
In installing air spring, three hydraulic lifting pressurized struts and three auxiliary support spaced cincture
Air spring is arranged, and is evenly distributed on air spring mounting base, it addition, hydraulic lifting
Pressurized strut is provided with control valve group and is connected with Hydraulic Station, and displacement transducer is arranged on hydraulic pressure liter
Fall pressurized strut sidewall.
Aircraft air spring lifting bearing the most according to claim 1, it is characterised in that
Described base lower end is provided with reinforcement.
Aircraft air spring lifting bearing the most according to claim 1, it is characterised in that
Described three hydraulic lifting pressurized struts are all connected to industrial computer by respective control valve group, to realize
Base synchronization lifting.
Aircraft air spring lifting bearing the most according to claim 1, it is characterised in that
Described auxiliary is supported for three leading screws stood upside down, and is connected with base with bolt, and drives with motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310652620.9A CN103616150B (en) | 2013-12-04 | 2013-12-04 | Aircraft air spring lifting bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310652620.9A CN103616150B (en) | 2013-12-04 | 2013-12-04 | Aircraft air spring lifting bearing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103616150A CN103616150A (en) | 2014-03-05 |
| CN103616150B true CN103616150B (en) | 2016-08-17 |
Family
ID=50166856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310652620.9A Active CN103616150B (en) | 2013-12-04 | 2013-12-04 | Aircraft air spring lifting bearing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103616150B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112340056B (en) * | 2020-09-22 | 2022-11-22 | 北京强度环境研究所 | Free boundary simulation support module |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3950374B2 (en) * | 2002-06-25 | 2007-08-01 | 三菱重工業株式会社 | Mobile loading test vehicle |
| CN102269651A (en) * | 2011-07-04 | 2011-12-07 | 中国人民解放军国防科学技术大学 | Maglev bogie fatigue test loading device |
| CN102795572A (en) * | 2011-05-27 | 2012-11-28 | 上海微电子装备有限公司 | Lifter and pneumatic control system thereof |
| CN103407933A (en) * | 2012-09-03 | 2013-11-27 | 希实本株式会社 | Vehicle lifting device with synchronizing function |
-
2013
- 2013-12-04 CN CN201310652620.9A patent/CN103616150B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3950374B2 (en) * | 2002-06-25 | 2007-08-01 | 三菱重工業株式会社 | Mobile loading test vehicle |
| CN102795572A (en) * | 2011-05-27 | 2012-11-28 | 上海微电子装备有限公司 | Lifter and pneumatic control system thereof |
| CN102269651A (en) * | 2011-07-04 | 2011-12-07 | 中国人民解放军国防科学技术大学 | Maglev bogie fatigue test loading device |
| CN103407933A (en) * | 2012-09-03 | 2013-11-27 | 希实本株式会社 | Vehicle lifting device with synchronizing function |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103616150A (en) | 2014-03-05 |
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