CN103808483B - A kind of liter force simulating device - Google Patents
A kind of liter force simulating device Download PDFInfo
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- CN103808483B CN103808483B CN201210453694.5A CN201210453694A CN103808483B CN 103808483 B CN103808483 B CN 103808483B CN 201210453694 A CN201210453694 A CN 201210453694A CN 103808483 B CN103808483 B CN 103808483B
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- storage chamber
- cylinder
- air storage
- built
- simulating device
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- 238000012360 testing method Methods 0.000 abstract description 12
- 238000004088 simulation Methods 0.000 abstract description 11
- 238000000034 method Methods 0.000 abstract description 5
- 238000009434 installation Methods 0.000 abstract description 3
- 230000009514 concussion Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to plane simulation technology, relate to a kind of liter force simulating device being applied to aircraft full machine drop-test.Described liter of force simulating device includes air storage chamber (1), built-in cylinder (2), piston rod (3).Wherein, described built-in cylinder (2) is arranged in air storage chamber (1), piston rod stretches into built-in cylinder (2) inside through air storage chamber (1) and by cylinder blow vent (4), and built-in cylinder (2) one end is connected to air storage chamber (1) outward by epicoele passage (6).The present invention rises force simulating device, uses unitary design method, generally internal force system, it is easy to in-site installation and movement, and lift is constant, and lift outfan and testpieces can realize Hard link, and servo-actuated with testpieces, can significantly improve the precision of lift simulation.
Description
Technical field
The invention belongs to plane simulation technology, relate to a kind of liter being applied to aircraft full machine drop-test
Force simulating device.
Background technology
During aircraft landing, contact to earth moment at main landing gear wheel, effect lift aboard
It is in a basic balance with the weight of aircraft, therefore in aircraft full machine drop-test, needs aircraft
1g lift be simulated, it is therefore an objective to make drop-test process more true, more can reflect that aircraft rises
The stressing conditions of aircaft configuration and energy absorption situation during shake that the frame that falls falls shake or full machine falls.
At present, the liter force simulating device of domestic use is essentially split-type design, the most whole lift mould
Plan system is made up of air storage chamber, breather, piston, and piston is connected by breather with air storage chamber,
Respective installation site is substantially stationary, can be only installed at ground, is not easy to mobile, and full machine falls to shaking examination
Testing field apparatus numerous, ground installing space is limited, is difficult to install.Split type lift simulation dress
Putting generally special equipment, only adapt to certain specific testpieces, purposes is single.Meanwhile, divide
The liter force simulating device of body formula cannot be servo-actuated with body, and is difficult to avoid that again with testpieces effect moment
Impact, cause lift to shake so that lift simulation precision be greatly affected.
Summary of the invention
It is an object of the invention to: provide a kind of and form simple, easy for installation and that simulation precision is high liter
Force simulating device.
The technical scheme is that a kind of liter force simulating device, it includes air storage chamber 1, built-in gas
Cylinder 2, piston rod 3, wherein, described built-in cylinder 2 is arranged in air storage chamber 1, and piston rod passes
Air storage chamber 1 also stretches into built-in cylinder 2 inside, and built-in cylinder 2 one end by cylinder blow vent 4
It is communicated to outside air storage chamber 1 by epicoele passage 6.
Air storage chamber 1 is additionally provided with the inflation inlet 5 being connected with the external world.
Piston rod moves down the shared volume change ratio with air storage chamber volume change less than 4.3%.
It is provided with on piston rod for hardwired slidingtype connecting rod.
Advantages of the present invention: this liter of force simulating device of present invention design, uses unitary design
Method, generally internal force system, the lift of output is only undertaken by piston rod, the intensity to mount point
Requiring low, mount point is only subjected to system gravity, it is easy to install in testing ground and mobile.Simultaneously
Compare built-in cylinder by appropriate design air storage chamber volume in lift simulation process, lose the ratio of volume
Example, can make effect simulation lift aboard be essentially constant.Lift outfan and testpieces can
Realize Hard link, and servo-actuated with testpieces, can significantly improve the precision of lift simulation.
Accompanying drawing explanation
Fig. 1 is that the present invention rises force simulating device schematic diagram,
Wherein, 1: air storage chamber；2: built-in cylinder；3: piston rod；4: cylinder blow vent；5: inflation
Mouthful；6: epicoele passage.
Detailed description of the invention
Below by detailed description of the invention, the present invention will be further described:
Referring to Fig. 1, it is the schematic diagram that the present invention rises force simulating device.Described liter of force simulating device
Including air storage chamber 1, built-in cylinder 2, piston rod 3.Wherein, described built-in cylinder 2 is arranged on storage
In air chamber 1, piston rod stretches in built-in cylinder 2 through air storage chamber 1 and by cylinder blow vent 4
Portion, and built-in cylinder 2 one end is connected to outside air storage chamber 1 by epicoele passage 6, it addition, storage
Air chamber 1 is additionally provided with the inflation inlet 5 being connected with the external world.
The present invention uses built-in upside-down mounting principle, air rammer device and caisson Integral design,
Making system composition simple, it is convenient that testing ground is installed.Meanwhile, the volume of gas storage part compares gas
The volume of dynamic piston portion is sufficiently large, it is ensured that piston pressure is basically unchanged.When drop-test,
Piston rod and aircaft configuration Hard link, and servo-actuated with testpieces, and such system composition form can disappear
Lift output concussion divided by the split type liter of force simulating device used in drop-test so that mould
Intend lift output more steady, can significantly improve drop-test lift simulation precision.
The present invention rises the output lift of force simulating device and is provided by the air pressure acting on piston, and leads to
Cross piston rod 3 to be delivered on aircraft, therefore, in the situation that piston area and air storage chamber volume are certain
Under, can improve the size of the pressure change lift of air storage chamber, therefore, system has and well adapts to
Property, the simulation demand of different size lift can be met.
In the case of piston area is certain, ignore the friction and inertia power of system, system defeated
The lift gone out is only relevant with the pressure of system.The initial pressure assuming system is P0Just volume is V0(have
Air storage chamber volume and piston lower portion volumetric composition), during piston movement, the available space of system
Can reduce, it is assumed that stroke ends with system volumetric loss Δ V, now the pressure of system is P1, available appearance
Amass as V0-Δ V, then according to the second law of thermodynamics:
Then
Wherein γ is air polytropic exponent, and Δ V is relevant with piston area A and stroke L, Δ V=A*L.
The imitative lift F=P*A of output, will keep the imitative lift substantially constant of output (such as maximum variable quantity
Less than 5%), this just requires that pressure maximum relative variation is less than 5%, knowable to (2) formula,
Only need to meet volume and relatively change that (piston rod moves down the change of shared volume and becomes with air storage chamber volume
The ratio of change) less than 4.3% can (γ=1.1), then by the piston area of appropriate design cylinder with
And the volume of air storage chamber, output lift substantially invariable design requirement can be met.
Native system primary load bearing parts are piston rod, and the outer cylinder structure of air storage chamber structure and cylinder is subjected only to
Gas intrinsic pressure, therefore, overall system architecture is internal force structure, and the mount point in testing ground is only
Be subjected to the gravity of system, can use the form such as pulley, wind spring realize lift and airplane motion with
Dynamic.
Owing to piston rod is subjected only to pulling force, the not requirement of existence and stability, therefore, piston rod is permissible
It is designed to long, by installing the connecting rod of slidingtype on the piston rod, lift mould can be realized
Intend the Hard link of device and aircraft, thus eliminate the liter in split type liter of force simulating device process of the test
Power concussion problem so that the lift of this device output is more steady.
Claims (3)
1. one kind rises force simulating device, it is characterised in that: include air storage chamber (1), built-in cylinder (2),
Piston rod (3), wherein, described built-in cylinder (2) is arranged in air storage chamber (1), piston rod
Built-in cylinder (2) inside is stretched into through air storage chamber (1) and by cylinder blow vent (4), and interior
Put cylinder (2) one end and be communicated to air storage chamber (1) outward by epicoele passage (6), piston rod to
Volume change shared by lower movement and the ratio of air storage chamber volume change are less than 4.3%.
The most according to claim 1 liter of force simulating device, it is characterised in that: air storage chamber 1 is also
It is provided with the inflation inlet (5) being connected with the external world.
The most according to claim 2 liter of force simulating device, it is characterised in that: pacify on piston rod
Equipped with for hardwired slidingtype connecting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210453694.5A CN103808483B (en) | 2012-11-12 | 2012-11-12 | A kind of liter force simulating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210453694.5A CN103808483B (en) | 2012-11-12 | 2012-11-12 | A kind of liter force simulating device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103808483A CN103808483A (en) | 2014-05-21 |
| CN103808483B true CN103808483B (en) | 2016-08-10 |
Family
ID=50705577
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210453694.5A Active CN103808483B (en) | 2012-11-12 | 2012-11-12 | A kind of liter force simulating device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103808483B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114486138B (en) * | 2021-12-30 | 2024-03-19 | 中国飞机强度研究所 | Device and method for testing vibration comfort of aircraft in full-aircraft state |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4215644A1 (en) * | 1992-05-14 | 1993-11-18 | Greschbach Ind Gmbh & Co | Lifting device for jacking up aircraft |
| FR2837760A1 (en) * | 2002-03-28 | 2003-10-03 | Liftlux Potain Gmbh | MOBILE LIFTING PLATFORM |
| TW566543U (en) * | 2003-04-17 | 2003-12-11 | Chung Shan Inst Of Science | Dropping hammer testing device of landing gear with ascending force simulation |
| CN101000238A (en) * | 2007-01-17 | 2007-07-18 | 北京航空航天大学 | Plane wheel space displacement measuring system of landing gear lowering shock test |
| CN102126563A (en) * | 2011-01-21 | 2011-07-20 | 南京航空航天大学 | Aircraft landing gear drop lifting force simulating device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20100108991A (en) * | 2009-03-31 | 2010-10-08 | 한재도 | Test device and method of aircraft landing gear |
-
2012
- 2012-11-12 CN CN201210453694.5A patent/CN103808483B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4215644A1 (en) * | 1992-05-14 | 1993-11-18 | Greschbach Ind Gmbh & Co | Lifting device for jacking up aircraft |
| FR2837760A1 (en) * | 2002-03-28 | 2003-10-03 | Liftlux Potain Gmbh | MOBILE LIFTING PLATFORM |
| TW566543U (en) * | 2003-04-17 | 2003-12-11 | Chung Shan Inst Of Science | Dropping hammer testing device of landing gear with ascending force simulation |
| CN101000238A (en) * | 2007-01-17 | 2007-07-18 | 北京航空航天大学 | Plane wheel space displacement measuring system of landing gear lowering shock test |
| CN102126563A (en) * | 2011-01-21 | 2011-07-20 | 南京航空航天大学 | Aircraft landing gear drop lifting force simulating device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103808483A (en) | 2014-05-21 |
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