CN104986327B - Damping device - Google Patents
Damping device Download PDFInfo
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- CN104986327B CN104986327B CN201510338592.2A CN201510338592A CN104986327B CN 104986327 B CN104986327 B CN 104986327B CN 201510338592 A CN201510338592 A CN 201510338592A CN 104986327 B CN104986327 B CN 104986327B
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- outer tube
- cross bar
- connecting rod
- inner tube
- chute
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Abstract
nullThe present invention provides a kind of damping device，Including fixed plate，Fixed plate side is provided with inner tube，The lower end of inner tube is fixed with wheel assemblies，Wherein，Inner tube is arranged over vertical pole，Outer tube sleeve is contained in outside vertical pole and inner tube，And vertical pole and inner tube can slide up and down by outer tube relatively，Outer tube is provided with the first chute，First chute has along the axially extended narrow grain of outer tube and along the circumferentially extending sipes of outer tube，Sipes is positioned at the lower end of narrow slot，First cross bar passes inner tube and the first chute，First cross bar can slide in the first chute，It is additionally provided with on the perisporium of outer tube along axially extended second chute of outer tube，Vertical pole is provided with the second cross bar，Second cross bar is through the second chute and stretches out outer tube，The perisporium of outer tube is provided with the connecting rod radially extended along outer tube，The connecting rod of foot-operated assembly is fixed in connecting rod，Bungee jumping rope sling is in connecting rod and the second cross bar.The present invention can realize the releasing of undercarriage and the linkage of rudder neatly and be connected, and improves the comfort level of aircraft.
Description
Technical field
The present invention relates to technical field of mechanical equipment, a kind of can apply aboard and can be as the damping device of the undercarriage of aircraft.
Background technology
The fuselage of existing aircraft is provided with rotor, duct or propeller equal power device, and is provided with undercarriage in the front portion of fuselage, and the afterbody at fuselage is provided with rudder.Generally, undercarriage is provided with one piece of PLASTIC LAMINATED, and aircraft front fork is fixed on PLASTIC LAMINATED, is fixed with wheel assemblies in the lower section of front fork.In order to realize turning to of aircraft, foot-operated assembly it is provided with in control cabinl pulpit, foot-operated assembly has multiple foot-operated, and foot-operated assembly is additionally provided with and the connecting rod of foot-operated linkage, one end of connecting rod is fixed on foot-operated assembly, and the other end through PLASTIC LAMINATED and is connected with front fork, when foot-operated being operated, connecting rod seesaws and drives front fork to rotate, and thus drives wheel assemblies to rotate.
Thering is provided centripetal force to aircraft during in order to turn on the ground, usual and afterbody the rudder of undercarriage links, and i.e. rides assembly and is connected to rudder also by connecting rod, and when foot-operated being operated, rudder will rotate under the drive of connecting rod.Therefore, foot-operated when being operated, undercarriage synchronizes to turn to rudder, and namely wheel assemblies and rudder are to link.
If aircraft is when ground turns to, the synchronous axial system of undercarriage and rudder can increase turning to of centripetal force when turning to of aircraft, beneficially aircraft.But turning to during aircraft flight aloft, undercarriage and rudder rotate in the lump, require that driver provides bigger steering force, it is easily caused driver fatigue, and the rotation of undercarriage easily causes the vibrations of aircraft, reduce flight stability and the comfort level of aircraft.
Rotating owing to often having only to rudder when aircraft aloft turns to, whether the rotation of undercarriage has no effect on that aircraft is skyborne to be turned to, and therefore there is a need to design a kind of novel undercarriage so that undercarriage will not link with rudder when aircraft aloft turns to.
Additionally, due to impulse force is relatively big during aircraft landing, bigger vibrations may be produced in a flash land, also influence whether the comfort level of aircraft.
Summary of the invention
The main object of the present invention is to provide and a kind of enables aircraft to reduce flight vibrations when landing and can more preferably protect the damping device of aircraft.
nullIn order to realize above-mentioned main purpose，The damping device that the present invention provides includes fixed plate，Fixed plate side is provided with inner tube，The lower end of inner tube is fixed with wheel assemblies，Wherein，Inner tube is arranged over vertical pole，Outer tube sleeve is contained in outside vertical pole and inner tube，Outer tube is fixed in fixed plate，Inner tube and vertical pole can slide up and down by outer tube relatively，Outer tube is provided with the first chute，First chute has along the axially extended narrow grain of outer tube and along the circumferentially extending sipes of outer tube，Sipes is positioned at the lower end of narrow slot，First cross bar passes inner tube and the first chute，First cross bar can slide in the first chute，It is additionally provided with on the perisporium of outer tube along axially extended second chute of outer tube，Vertical pole is provided with the second cross bar，Second cross bar is through the second chute and stretches out outer tube，The perisporium of outer tube is provided with the connecting rod radially extended along outer tube，The connecting rod of foot-operated assembly is fixed in connecting rod，Bungee jumping rope sling is in connecting rod and the second cross bar.
From such scheme, aircraft is when ground turns to, and outer tube moves downward relative to inner tube under the effect of aircraft weight, and the first cross bar slides in the narrow slot of the first chute.When foot-operated assembly is operated, connecting rod drives the connecting rod on outer tube to rotate, and thus drives inner tube to rotate, and wheel assemblies is also with outer tube synchronous axial system.Now, rudder rotates under the effect of foot-operated assembly, therefore aircraft undercarriage and rudder synchronous axial system when ground turns to.
When aircraft aloft turns to, inner tube moves downward relative to outer tube under gravity, namely outer tube moves upward relative to inner tube, in now the first cross bar slips into the sipes of the first chute, due to circumferentially extending, when foot-operated assembly is operated and drives outer tube to rotate along outer tube of sipes, first cross bar slides in sipes, therefore inner tube rotates relative to outer tube, and namely inner tube is not followed by outer tube rotation, and wheel assemblies does not rotates.So, when aircraft aloft turns to, wheel assemblies and rudder will not synchronous axial system, thus vibrations avoiding aircraft to cause when aloft turning to, improve the comfortableness of aircraft.
One preferred scheme is, the lower end of outer tube is fixed on the first fixation kit, and the first fixation kit is fixed in fixed plate, and the first cross bar is bearing on the first fixation kit.
As can be seen here, outer tube is fixed in fixed plate by the first fixture, it can be ensured that outer tube is fixing, so that it is guaranteed that outer tube is securely fixed in fixed plate with fixed plate.Further, the first cross bar is bearing on the first fixation kit, it is to avoid the first cross bar comes off from outer tube, inner tube.
Further scheme is that the upper end of outer tube is fixed on the second fixation kit, and the second fixation kit is fixed in fixed plate.
Visible, the two ends up and down of outer tube are fixed in fixed plate by the first fixation kit and the second fixation kit respectively, it can be ensured that outer tube is securely fixed in fixed plate.
Further scheme is that the two ends of connecting rod lay respectively at the axial both sides of outer tube, and bungee jumping rope sling is contained in the two ends of connecting rod.
As can be seen here, in the connecting rod outside bungee jumping rope sling is contained in outer tube both sides, it can be ensured that the connection of bungee jumping rope is relatively reliable.
Further scheme is to be connected by screw between connecting rod and connecting rod, bungee jumping rope sling at screw near the side of outer tube.
Visible, bungee jumping rope is limited by screw, and such design can avoid bungee jumping rope to come off from the two ends of connecting rod.
Accompanying drawing explanation
Fig. 1 is the structure chart that the embodiment of the present invention is connected with foot-operated assembly.
Fig. 2 is the structure chart at another visual angle that the embodiment of the present invention is connected with foot-operated assembly.
Fig. 3 is the STRUCTURE DECOMPOSITION figure of the embodiment of the present invention.
Fig. 4 is the STRUCTURE DECOMPOSITION figure of inner tube in the embodiment of the present invention, outer tube and vertical pole.
Fig. 5 is the embodiment of the present invention structure chart when ground.
Fig. 6 is the partial structurtes enlarged drawing of Fig. 5.
Fig. 7 is that the embodiment of the present invention on ground and rides structure chart when stepping on.
Fig. 8 is the partial structurtes enlarged drawing of Fig. 7.
Fig. 9 be the embodiment of the present invention aloft time structure chart.
Figure 10 is the partial structurtes enlarged drawing of Fig. 9.
Figure 11 is that the embodiment of the present invention aloft and rides structure chart when stepping on.
Figure 12 is the partial structurtes enlarged drawing of Figure 11.
Figure 13 is the embodiment of the present invention structure chart at buffer stage.
Figure 14 is the partial structurtes enlarged drawing of Figure 13.
Below in conjunction with drawings and Examples, the invention will be further described.
Detailed description of the invention
The damping device of the present invention may be mounted on aircraft, and is arranged on the front portion of aircraft as undercarriage, and is connected with foot-operated assembly, and foot-operated assembly is also connected with the rudder being positioned at airplane tail group.
Seeing Fig. 1 and Fig. 2, the undercarriage of aircraft includes one piece of fixed plate 10, fixed plate 10 namely PLASTIC LAMINATED, is arranged on the fore-body of aircraft.The lower section of fixed plate 10 is provided with inner tube 11, and the lower end of inner tube 11 is provided with front fork 12, and wheel assemblies 13 is arranged on front fork 12.
Inner tube 11, wheel assemblies 13 are positioned at the side of fixed plate 10, opposite side in fixed plate 10 is provided with foot-operated assembly 40, foot-operated assembly 40 has four foot-operated 41, two of which is ridden 41 composition first group and is ridden, link with a connecting rod 42, two other is ridden 41 composition second group and rides, and links with another root connecting rod 43.When first group of foot-operated any one is operated, drivening rod 42 travels forward, and when second group of foot-operated any one is operated, drivening rod 43 travels forward.
See Fig. 3 and Fig. 4, inner tube 11 be arranged over vertical pole 16, the collar 15 glue is bonded at the top of inner tube 11, and the position of the collar 15 is slightly below the top of inner tube 11, and the collar 15 is between inner tube 11 and outer tube 20, its effect is subject to the relative motion friction of outer tube 20 and inner tube 11.Be provided with through hole 19 at the middle part of inner tube 11, through hole 19 runs through inner tube 11.The upper end of inner tube 11 is provided with a through hole 14, and the lower end of vertical pole 16 is inserted in through hole 14.The lower end of vertical pole 16 is provided with pad 18, and pad 18 is bearing in the top of inner tube 14.Further, vertical pole 16 is provided with the second cross bar 17, and the second cross bar 17 is perpendicular to the axial of vertical pole 16.
Outer tube 20 is sleeved on outside inner tube 11 and vertical pole 16, and in the present embodiment, the length of outer tube 20 is less than the length of inner tube 11, and therefore outer tube 20 is sleeved on the top of inner tube 11.Further, inner tube 11 and vertical pole 16 can slide up and down relative to outer tube 20.On the perisporium of lower end, the first chute 21 it is provided with at outer tube 20, see Fig. 6, first chute 21 includes narrow slot 22 and sipes 23, narrow slot 22 is axially extending along outer tube 20, sipes 23 is circumferentially extending along outer tube 20, and sipes 23 is positioned at the lower end of narrow slot 22 and connects with narrow slot 22, therefore, narrow slot 22 and sipes 23 form the groove of an inverted T shape.
As seen from Figure 3, it is provided with the first fixation kit in the lower end of fixed plate 10, first fixation kit includes fixture 36 and fixture 37, fixture 36, fixture 37 lay respectively at the both sides of the lower end of outer tube 20, and the first fixation kit is fixed in fixed plate 10, and the first fixation kit is fixed with outer tube 20 and is connected.
First fixation kit is supported with the first cross bar 38, first cross bar 38 passes through hole 19 and first chute 21 of inner tube 11, and the first cross bar 38 can slide in the first chute 21, and the i.e. first cross bar 38 can slip in narrow slot 22, it is also possible to slips in sipes 23.When the first cross bar 38 is in sipes 23, can in sipes 23 circumferentially rotating along outer tube 20, therefore, inner tube 11 the most just can rotate relative to outer tube 20 in the circumferential.
As seen from Figure 4, the upper end of outer tube 20 is provided with the second chute 24, axially extending along outer tube 20 of the second chute 24, and the second chute 24 is positioned at the top of the first chute 21.Second cross bar 17 of vertical pole 16 through the second chute 24 and can slide up and down in the second chute 24, and therefore vertical pole 16 can slide up and down relative to outer tube 20.Preferably, the two ends of the second cross bar 17 be each passed through outer tube 20 and be positioned at outer tube 20 axial both sides outside, therefore the two ends of the second cross bar 17 are positioned at the outside of outer tube 20.It can be seen from figure 3 that the second cross bar 17 be respectively arranged at two ends with axle cap 25.
Be provided with a connecting rod 28 being perpendicular to outer tube 20 axis at the middle part of outer tube 20, the two ends of connecting rod 28 lay respectively at the both sides of outer tube 20.The two ends of connecting rod 28 are respectively connecting on the connecting rod 42,43 of foot-operated assembly 40, and the two ends of connecting rod 28 are connected with connecting rod 42,43 by screw 27 respectively.Therefore, the side of the equal self-retaining plate 10 of connecting rod 42,43 extends to the opposite side of fixed plate 10 through fixed plate 10, and connecting rod 42,43 can seesaw relative to fixed plate 10.
So, when connecting rod 42 travel forward and connecting rod 43 is corresponding do adverse movement time, connecting rod 28 will turn clockwise under the drive of connecting rod 42,43, thus drives outer tube 20 to turn clockwise.Owing to there is sliding friction between outer tube 20 and fixation kit 37, fixation kit 37 and fixed plate 10 keep fixing.When connecting rod 43 travel forward and connecting rod 42 is corresponding do adverse movement time, connecting rod 28 will rotate counterclockwise, thus drive outer tube 20 to rotate counterclockwise, and such fixation kit 37 and fixed plate 10 keep fixing.
Be provided with the second fixation kit in the upper end of outer tube 20, as seen from Figure 3, the second fixation kit includes fixture 31, bearing 32 and is positioned at the pad 33 below bearing 32, and the upper end of vertical pole 16 can pass pad 33, and the upper end of outer tube 20 is fixed on the second fixation kit.So, the two ends up and down of outer tube 20 are separately fixed on the first fixation kit and the second fixation kit, and the first fixation kit and the second fixation kit are separately fixed in fixed plate 10, can be clamped securely in fixed plate 10 by outer tube 20.
Bungee jumping rope 30 it is additionally provided with outside outer tube 20, bungee jumping rope 30 is made by having resilient material, such as rubber etc., bungee jumping rope 30 is sleeved on the second cross bar 17 and the two ends of connecting rod 28, it can be seen from figure 3 that a part for bungee jumping rope 30 is enclosed within screw 27 in the connecting rod 28 of outer tube 20, a part is sleeved on axle cap 25 on the second cross bar 17 of outer tube 20, by screw 27, axle cap 25, bungee jumping rope 30 is carried out spacing, it is to avoid bungee jumping rope 30 comes off from connecting rod the 28, second cross bar 17.
See Fig. 5 and Fig. 6, aircraft on the ground time, wheel assemblies 13 lands, and inner tube 11 moves upward under the support of wheel assemblies 13.Fixed plate 10 moves downward under the fuselage weight effect of aircraft, and therefore outer tube 20 is also followed fixed plate 10 and moved downward relative to inner tube 11.Now, in the first cross bar 38 slips into the narrow slot 22 of the first chute 21.When foot-operated the 41 of foot-operated assembly 40 are operated, as illustrated in figs. 7 and 8, connecting rod 28 rotates clockwise or counterclockwise under the drive of connecting rod 42,43, and rotation also followed by outer tube 20.Owing to the first cross bar 38 is positioned at narrow slot 22, the first cross bar 22 can not rotate in the circumferential relative to outer tube 20, and therefore the first cross bar 38, inner tube 11 are followed outer tube 20 immediately and rotated, and wheel assemblies 13 also follows rotation.
When being operated due to foot-operated the 41 of foot-operated assembly 40, rotation also followed by the rudder being positioned at airplane tail group, and when therefore aircraft turns on the ground, wheel assemblies 13 and rudder are by synchronous axial system, it is achieved undercarriage and the linkage of rudder.So, bigger centripetal force can be provided by rudder when aircraft turns on the ground, it is ensured that aircraft turns to neatly.
Owing to outer tube 20 moves downward relative to inner tube 11, the second cross bar 17 slides into the lower end of the second chute 24, and bungee jumping rope 30 is not elongated.
During aircraft flight aloft, as shown in Figures 9 and 10, owing to wheel assemblies 13 does not lands, therefore move downward relative to outer tube 20 under the effect of himself gravity, namely outer tube 20 moves upward relative to inner tube 11, and the first cross bar 38 moves downward and slips into along the first chute 21 in sipes 23.
When foot-operated the 41 of foot-operated assembly 40 are operated, connecting rod 42,43 drives connecting rod 28 to rotate clockwise or counterclockwise, thus drives outer tube 20 to rotate.As shown in Figure 11 Yu Figure 12, owing to now the first cross bar 38 is positioned at sipes 23, therefore the first cross bar 38 can in sipes 23 circumferentially rotating along outer tube 20, inner tube 11 also rotates in the circumferential with respect to outer tube 20.Therefore, when outer tube 20 rotates clockwise or counterclockwise under the drive of foot-operated assembly 40, inner tube 11 can't be driven to rotate, wheel assemblies 13 also would not follow rotation.
Owing to foot-operated assembly 40 still links with rudder, therefore when foot-operated the 41 of foot-operated assembly 40 are operated, rudder rotates the most in the predetermined direction.Visible, aircraft aloft turns to, wheel assemblies 13 not being rotated by foot-operated assembly 40, and rudder still being rotated by foot-operated assembly 40, it is achieved disconnect the linkage between wheel assemblies 13 and rudder.So, the steering force that driver aloft controls to provide when aircraft turns to is less, it is to avoid driver fatigue.Further, since wheel assemblies 13 does not rotate, the phenomenon of the aircraft vibrations caused because wheel assemblies 13 rotates can be avoided, improve the comfort level of Aircraft Air flight.
Meanwhile, bungee jumping rope 30 is enclosed within connecting rod 28 and the second cross bar 17, forces the second cross bar 17 to slide into the bottom of the second chute 24, and bungee jumping rope 30 is not elongated.
At aircraft landing buffer stage, as shown in figures 13 and 14, wheel assemblies 13 is supported by ground, but aircraft forces outer tube 20 to move downward relative to inner tube 11 and vertical pole 16 under the effect of own wt and impulse force.Owing to the impulse force of aircraft is relatively big, the distance forcing outer tube 20 slide downward is longer, and the upper end of vertical pole 16 passes the second fixation kit, and the second cross bar 17 slides into the upper end of the second chute 24, and now bungee jumping rope 30 is elongated.
And, inner tube 11 moves upward relative to outer tube 20, first cross bar 38 will slide in the narrow slot 22 of the first chute 21, therefore foot-operated the 41 of assembly 40 is ridden when being operated, inner tube 11 is followed outer tube 20 and is rotated, thus drive wheel assemblies 13 to rotate, thus realize the linkage of wheel assemblies 13 and rudder, facilitate the steering operation of aircraft.
Visible, in the aircraft landing stage, outer tube 20 can be relative to inner tube 11 motion the most on a large scale, impulsive force during aircraft landing can be buffered, when making aircraft landing more steady, avoiding causing aircraft bigger impact, therefore the undercarriage of aircraft constitutes a damping device, improves the comfort level of aircraft further.
Certainly, above-described embodiment is only the detailed description of the invention of the present invention, can also have more change in actual application, and such as outer tube is only fixed in fixed plate by one group of fixation kit, and now fixed plate can be arranged on the middle part of outer tube；Or, use the bungee jumping rope of more than two to realize the buffering of impulsive force of landing phases, such change has no effect on the enforcement of the present invention.
Finally it is emphasized that; the present invention is to provide a kind of easy Multifuctional shock-absorbing device; also can be used in the general standard machinery field in addition to aviation field; as applied on automobile the damping device as automobile; the invention is not restricted to above-mentioned embodiment, the changes such as the change of position are set such as inner tube and the change of outer tube shape, the first chute and the second chute and also should include within the scope of the invention as claimed.
Claims (10)
1. damping device, including
Fixed plate, described fixed plate side is provided with inner tube, and the lower end of said inner tube is fixed with wheel assemblies；
Its characteristic is:
Said inner tube is arranged over vertical pole, and outer tube sleeve is contained in outside described vertical pole and said inner tube, and described outer tube is fixed in described fixed plate, and said inner tube and described vertical pole can slide up and down relative to described outer tube；
Described outer tube is provided with the first chute, described first chute has along the axially extended narrow grain of described outer tube and along the circumferentially extending sipes of described outer tube, described sipes is positioned at the lower end of described narrow slot, first cross bar passes said inner tube and described first chute, and described first cross bar can slide in described first chute；
Being additionally provided with along axially extended second chute of described outer tube on the perisporium of described outer tube, described vertical pole is provided with the second cross bar, and described second cross bar is through described second chute and stretches out described outer tube；
The perisporium of described outer tube is provided with the connecting rod radially extended along described outer tube, and the connecting rod of foot-operated assembly is fixed in described connecting rod, and bungee jumping rope sling is in described connecting rod and described second cross bar.
Damping device the most according to claim 1, it is characterised in that:
The lower end of described outer tube is fixed on the first fixation kit, and described first fixation kit is fixed in described fixed plate.
Damping device the most according to claim 2, it is characterised in that:
Described first cross bar is bearing on described first fixation kit.
4. according to the damping device described in any one of claims 1 to 3, it is characterised in that:
The upper end of described outer tube is fixed on the second fixation kit, and described second fixation kit is fixed in described fixed plate.
5. according to the damping device described in any one of claims 1 to 3, it is characterised in that:
The two ends of described connecting rod lay respectively at the axial both sides of described outer tube, and described bungee jumping rope sling is contained in the two ends of described connecting rod.
Damping device the most according to claim 5, it is characterised in that:
Be connected by screw between described connecting rod and described connecting rod, described bungee jumping rope sling at described screw near the side of described outer tube.
7. according to the damping device described in any one of claims 1 to 3, it is characterised in that:
The two ends of described second cross bar lay respectively at the axial both sides of described outer tube, and described bungee jumping rope sling is at the two ends of described second cross bar.
Damping device the most according to claim 7, it is characterised in that:
Described second cross bar be respectively arranged at two ends with axle cap, described bungee jumping rope sling at described axle cap near the side of described outer tube.
9. according to the damping device described in any one of claims 1 to 3, it is characterised in that:
Being stained with the collar outside said inner tube, the described collar is between described outer tube and inner tube, and described vertical pole can rotate relative to said inner tube.
Damping device the most according to claim 9, it is characterised in that:
The lower end of described vertical pole is provided with pad, and described pad is connected to the top of said inner tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510338592.2A CN104986327B (en) | 2015-06-17 | 2015-06-17 | Damping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510338592.2A CN104986327B (en) | 2015-06-17 | 2015-06-17 | Damping device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104986327A CN104986327A (en) | 2015-10-21 |
| CN104986327B true CN104986327B (en) | 2016-09-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510338592.2A Active CN104986327B (en) | 2015-06-17 | 2015-06-17 | Damping device |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10591013B2 (en) * | 2017-06-14 | 2020-03-17 | Safran Landing Systems Canada Inc. | Lubrication mechanism design for aircraft landing gear bearings |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08276884A (en) * | 1996-04-26 | 1996-10-22 | Showa:Kk | Front fork of motorcycle |
| CN201405989Y (en) * | 2009-05-23 | 2010-02-17 | 黄庆煊 | Shock-absorbing front fork of bicycle |
| CN203094439U (en) * | 2013-01-10 | 2013-07-31 | 襄阳宏伟航空器有限责任公司 | Shock absorption system for wheel-type dynamic parachute |
| CN103445921A (en) * | 2013-09-23 | 2013-12-18 | 江门市朝扬精密制造有限公司 | Four-wheel independent suspension system of power-driven wheelchairs |
| CN204197279U (en) * | 2014-10-31 | 2015-03-11 | 湖北易瓦特科技有限公司 | A kind of retractable landing gear |
-
2015
- 2015-06-17 CN CN201510338592.2A patent/CN104986327B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08276884A (en) * | 1996-04-26 | 1996-10-22 | Showa:Kk | Front fork of motorcycle |
| CN201405989Y (en) * | 2009-05-23 | 2010-02-17 | 黄庆煊 | Shock-absorbing front fork of bicycle |
| CN203094439U (en) * | 2013-01-10 | 2013-07-31 | 襄阳宏伟航空器有限责任公司 | Shock absorption system for wheel-type dynamic parachute |
| CN103445921A (en) * | 2013-09-23 | 2013-12-18 | 江门市朝扬精密制造有限公司 | Four-wheel independent suspension system of power-driven wheelchairs |
| CN204197279U (en) * | 2014-10-31 | 2015-03-11 | 湖北易瓦特科技有限公司 | A kind of retractable landing gear |
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| CN104986327A (en) | 2015-10-21 |
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