CN102874403A - Airplane wheel system with combination of rigid solid tires and buffer support - Google Patents
Airplane wheel system with combination of rigid solid tires and buffer support Download PDFInfo
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- CN102874403A CN102874403A CN2012104142623A CN201210414262A CN102874403A CN 102874403 A CN102874403 A CN 102874403A CN 2012104142623 A CN2012104142623 A CN 2012104142623A CN 201210414262 A CN201210414262 A CN 201210414262A CN 102874403 A CN102874403 A CN 102874403A
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Abstract
The invention provides an airplane wheel system with a combination of rigid solid tires and a buffer support, mainly consisting of two major parts, i.e., a non-inflated rigid solid tire part and a buffer support part, wherein the buffer support part mainly consists of an upper post, a lower post, an air spring, an end cover plate, an aluminum alloy flange, side supporting posts and the like; the anti-wear and anti-puncture performances of aircraft tires are separated from the performances of vibration buffer and impact energy absorption; the air spring plays a role in mainly absorbing the impact energy; since the tires have the non-inflation performance, the anti-puncture and anti-wear performances are improved remarkably; therefore, when an airplane lands or slides from high altitude, the non-inflated rigid tires only need to bear high speed friction between the tires themselves and the ground; the posts provided with the air spring can exert functions of main buffering and vibration lightening; through the volume expansion, the energy is absorbed or released; and therefore, the comfortable effect of vibration absorption is achieved.
Description
Technical field
The present invention relates to a kind of type aircraft train, particularly relate to a kind of aircraft train that has rigidity band tyre and buffering holder combination, it makes aircraft in lifting and slides in the process and can significantly improve comfort property.
Background technology
The current tire that is using in air transportation is Pneumatic tire, namely use pressurized air to come support tire to bear certain load, although this has improved passenger's traveling comfort greatly, but Pneumatic tire also exists significant limitation, because it will possess higher resistance to abrasion, and under high pressure, high temperature, the inferior very harsh condition of high-speed working condition, carry out work, this can make, and air leakage, tire shoulder place Crack failure occur in Pneumatic tire easily, the major accident problem such as blow out, and cause the generation of a series of bad accidents; Present undercarriage is most of in addition uses the oil gas shock strut to absorb, consume damping and the Impact energy when sliding, and its structure is not only comparatively complicated, and owing to be filled with liquid etc. in its inner chamber, exist may leakage of oil etc. the generation of accident.
Patent CN 101850844A has proposed a kind of undercarriage, this structure comprises rotating shaft, pressurized strut and energy disperser, in pressurized strut, be set with piston rod, be provided with sleeve in the rotating shaft, this sleeve is fixedly connected on the fuselage, this invention realizes that by movement and the control of lock control devices countershaft of piston rod in pressurized strut alighting gear moves in three dimensional space, guarantee that alighting gear can walk around the bulge on the fuselage, smoothly folding and unfolding.
Patent CN1093066C has invented a kind of aircraft nose-gear system, this Aircraft landing gear system comprises landing gear assembly and alighting gear rotary shaft pin connector, this joint comprises inboard nose gear nacelle element and the outside nose gear nacelle element of the relative both sides of airplane frame nose gear nacelle plate, is connected inboard axle sleeve in the hole of correspondence with outside nose gear nacelle panel element and is connected the rotary shaft pin with outside axle sleeve and connects and be installed in described inboard front deck element.
International monopoly CN101687545A discloses a kind of bumper for undercarriage, it has two parts that can slide after mutually installing, and be limited to one and be filled with in the internal capacity of liquids and gases, it is separated part and is divided at least two chambers, separator has a cutoff port at least, make gas when alighting gear launches, transfer to another chamber from a chamber, thereby the mechanical energy that the rapid flow of hydraulic fluid by cutoff port falls aircraft when bumper compresses is converted into thermal energy consumption and dissipates, play damping effect, to improve the aircraft whereabouts traveling comfort of moment.
Because aircraft tyre is after sliding or slide fast through long distance, temperature can significantly raise, this can increase its sensivity and cause aircraft take off or landing mission in the generation of fault, in the US7172000B2 patent, related to a kind of crown reinforced layer structure with the tire shoulder layer that is applicable to aircraft tyre, this not only can reduce well because the crack causes the risk that tire decomposes, and can heat rejection and removal, this tire shoulder layer at least one edge with crown reinforced layer on the inner edge of axial direction is adjacent, and axially external margin is lower than the bracing ply that is adjacent at meridian direction.
In order to make tire can bear heavier load and larger inflation pressure, company of Michelin has proposed a meridian aircraft tyre crown enhancement layer structure among the disclosed patent US6601626B2 in 2003, this crown reinforced layer comprises at least high-modulus reinforcement unit of one deck circumferential orientation, the two-layer high-modulus that free end arranged is strengthened the fabricate block that unit and two-layer and circumferential direction are the low modulus blended layer of 0 ° of-35 ° of angle orientation, more than each layer be aramid fiber material, wherein low modulus blended layer 300 and 301 separately width be 95mm and 85mm, 130mm less than tread width L, enhancement Layer 310,311 gross thickness is 3mm, and the width of enhancement Layer 32 is 190mm.
U.S. Patent application US2006/113016 discloses a kind of non-inflatable tyre, is called Tweel, and it is formed by connecting by four parts, comprises wheel, spoke, around the enhancing endless belt of spoke and the rubber tread of kiss the earth.
In above-mentioned multiple Aircraft landing gear system and aircraft tyre train, the Pneumatic tire that it adopts the alighting gear of different structure and different structure and material to design, although can consume to a certain extent and absorb aircraft is descending and is sliding problems such as bump in the process, but there is a series of accident potential problem in Pneumatic tire itself, for example blow out, the crack, tire shoulder damage etc., Landing Gear System is also comparatively complicated, manufacturing overhead cost is higher, and because its complexity must be brought the risk of a series of failure problems, such as hydraulic fluid leak in the shock strut etc.
Summary of the invention
The object of the present invention is to provide a kind of type aircraft train, its use has the on-inflatable rigidity tire of resistance to abrasion, and between the upper lower supporting rod of aircraft train, adopt the air bellow structure to absorb to consume it in landing and slide the collision impact that produces in the process etc., not only can improve its service life, greatly reduce the accident risk incidence, and it is simple in structure, low cost of manufacture, and can reach the comfortable effect of damping.
For achieving the above object, a kind of aircraft train with rigidity band tyre and buffering holder combination is proposed, it mainly rushes the support two large divisions and forms by on-inflatable rigidity tire is gentle, the buffering stand part is mainly by upper supporting column, lower supporting rod, air bellow, end casing, aluminium alloy flange, the compositions such as side stay pillar, upper supporting column and lower supporting rod mainly play the effect of the load support aircraft weight that withstands shocks, air bellow then plays damping vibration, the effect of absorbing impact energy, wherein two ends, the lower supporting rod bottom cooperation that is connected with on-inflatable rigidity tire, the lower supporting rod top end joins by aluminium alloy flange structure and air bellow end casing, and fastening by special bolt, same upper supporting column bottom joins by aluminium alloy flange structure and air bellow end casing, and fastening by special bolt, support pillar in the left and right sides contacts with the upper supporting column cooperation by the connection of rotary shaft pin in addition, in order to support alighting gear from left and right directions.On-inflatable rigidity tire part then is comprised of wheel rim and band tyre, band tyre can be injection molded by thermoplastic elastomer, such as the polyurethane elastomer plastic cement, it had both had certain mechanical strength and good elasticity, and resistance to cold is outstanding, durometer level is wide, can satisfy well to contact needed basic physical and mechanical properties with ground.
According to the present invention, this type aircraft train is separated the anti-wear-resisting anti-puncture performance of aircraft tyre with buffering vibration absorbing impact energy performance, air bellow plays main absorbing impact energy effect, and tire is because its on-inflatable performance, greatly improved its anti-puncture and resistance to abrasion, so when aircraft lands from the high-altitude or slides, on-inflatable rigidity tire only need bear the high-speed friction between itself and ground, the pillar that air bellow is housed then can play main buffering and alleviate the function of vibrations, its by own vol stretch absorb and release energy, thereby reach the comfortable effect of damping.
Type aircraft train of the present invention is not only simple in structure, saves cost, and it has better anti-wear and anti-puncture, effectively prolongs the service life of tire, and then can greatly reduce the incidence of accident in the aircraft takeoffs and landings process.
From following to according to the present invention preferably but the description of not exclusive embodiment, can further understand better advantages and features of the invention, the accompanying drawing that this description provides with reference to non-limiting example, specification sheets of the present invention also should be read with reference to accompanying drawing.
Description of drawings
Fig. 1 has the aircraft wheel architecture scheme drawing of rigidity band tyre and buffering holder combination for invention is a kind of.
Fig. 2 shows a kind of side direction view with aircraft train of rigidity band tyre and buffering holder combination of the present invention.
Fig. 3 is a kind of on-inflatable rigidity tire with aircraft train of rigidity band tyre and buffering holder combination of the present invention.
Fig. 4 plays the air bellow of cushion characteristic in a kind of aircraft train with rigidity band tyre and buffering holder combination.
Respectively mark as follows among the figure:
1-on-inflatable rigidity tire; The 2-lower supporting rod; The 3-air bellow; The 4-aluminium alloy flange; The 5-upper supporting column; 6-side stay pillar; The 7-end casing; The 8-special bolt.
The specific embodiment
Below in conjunction with exemplary embodiment a kind of type aircraft train with on-inflatable rigidity band tyre and buffering stand of the present invention is set forth.
As depicted in figs. 1 and 2, a kind of aircraft train with rigidity band tyre and buffering holder combination of the present invention, it has the on-inflatable rigidity tire 1 of resistance to abrasion, and between the lower supporting rod 2 of aircraft train, upper supporting column 5, adopt air bellow 3 structures to absorb to consume it in landing and slide the collision impact that produces in the process etc., not only can improve its service life, greatly reduce the accident risk incidence, and it be simple in structure, low cost of manufacture, and can reach the comfortable effect of damping.
The invention provides a kind of aircraft train with rigidity band tyre and buffering holder combination, it mainly is comprised of on-inflatable rigidity tire 1 and buffering stand two large divisions, the buffering stand part is mainly by upper supporting column 5, lower supporting rod 2, air bellow 3, end casing 7, aluminium alloy flange 4, side stay pillar 6 compositions such as grade, upper supporting column 5 and lower supporting rod 2 mainly play the effect of the load support aircraft weight that withstands shocks, 3 of air bellows play damping vibration, the effect of absorbing impact energy, wherein two ends, the lower supporting rod 2 bottom cooperation that is connected with on-inflatable rigidity tire 1, lower supporting rod 2 top ends join by aluminium alloy flange 4 and air bellow end casing 7, and fastening by special bolt 8, same upper supporting column 5 bottoms join by aluminium alloy flange 4 and air bellow end casing 7, and fastening by special bolt 8, left and right sides side stay pillar 6 contacts with upper supporting column 5 cooperations by the connection of rotary shaft pin in addition, in order to support alighting gear from left and right directions.
On-inflatable rigidity tire 1 part then is comprised of wheel rim and band tyre, as shown in Figure 3, band tyre can be injection molded by thermoplastic elastomer, such as the polyurethane elastomer plastic cement, it had both had certain mechanical strength and good elasticity, and resistance to cold is outstanding, and durometer level is wide, can satisfy well to contact needed basic physical and mechanical properties with ground.
According to the present invention, this type aircraft train is separated the anti-wear-resisting anti-puncture performance of aircraft tyre with buffering vibration absorbing impact energy performance, air bellow 3(is as shown in Figure 4) play main absorbing impact energy effect, and on-inflatable rigid wheel tire 1 is because its performance that need not to inflate, greatly improved its anti-puncture and resistance to abrasion, so when aircraft lands from the high-altitude or slides, 1 need of on-inflatable rigidity tire bear the high-speed friction between itself and ground, 3 of air bellows can play main buffering and alleviate the effect of vibrations, its by own vol stretch absorb and release energy, thereby reach the comfortable effect of damping.
Type aircraft train of the present invention is not only simple in structure, saves cost, and it has better anti-wear and anti-puncture, effectively prolongs the service life of tire, and then can greatly reduce the incidence of accident in the aircraft takeoffs and landings process.
Claims (3)
1. one kind has rigidity band tyre and the aircraft train that cushions holder combination, it is characterized in that: mainly rush the support two large divisions and form by on-inflatable rigidity tire is gentle, the buffering stand part is mainly by upper supporting column, lower supporting rod, air bellow, end casing, aluminium alloy flange, the compositions such as side stay pillar, upper supporting column and lower supporting rod mainly play the effect of the load support aircraft weight that withstands shocks, air bellow then plays damping vibration, the effect of absorbing impact energy, wherein two ends, the lower supporting rod bottom cooperation that is connected with on-inflatable rigidity tire, the lower supporting rod top end joins by aluminium alloy flange structure and air bellow end casing, and fastening by special bolt, same upper supporting column bottom joins by aluminium alloy flange structure and air bellow end casing, and fastening by special bolt, support pillar in the left and right sides contacts with the upper supporting column cooperation by the connection of rotary shaft pin in addition, in order to support alighting gear from left and right directions; On-inflatable rigidity tire part then is comprised of wheel rim and band tyre.
According to claim 1 a kind of have the rigidity band tyre and the buffering holder combination the aircraft train, it is characterized in that: band tyre is injection molded by thermoplastic elastomer.
According to claim 2 a kind of have the rigidity band tyre and the buffering holder combination the aircraft train, it is characterized in that: described thermoplastic elastomer is the polyurethane elastomer plastic cement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104142623A CN102874403A (en) | 2012-10-25 | 2012-10-25 | Airplane wheel system with combination of rigid solid tires and buffer support |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104142623A CN102874403A (en) | 2012-10-25 | 2012-10-25 | Airplane wheel system with combination of rigid solid tires and buffer support |
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| CN102874403A true CN102874403A (en) | 2013-01-16 |
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| CN2012104142623A Pending CN102874403A (en) | 2012-10-25 | 2012-10-25 | Airplane wheel system with combination of rigid solid tires and buffer support |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN104816591A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Injection molding type air-inflation-free unmanned aerial vehicle wheel on metal rim |
| CN104816592A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Injection type non-pneumatic wheel on metal rim for two-wheel electrical motorcycle |
| CN104816590A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Inflation-free automobile wheel injection-molded on metal rim |
| CN104816593A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Non-pneumatic artillery vehicle wheel formed by injection molding on metal rim |
| CN104816589A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Air inflation-free field-in motor vehicle wheel with injection molding on metal rim |
| CN104960662A (en) * | 2015-06-01 | 2015-10-07 | 深圳市大疆创新科技有限公司 | Landing gear and unmanned aerial vehicle using the same |
| CN108639340A (en) * | 2018-04-12 | 2018-10-12 | 清远市巨劲科技有限公司 | One kind can pre- antiwear unmanned plane |
| CN113443130A (en) * | 2021-06-30 | 2021-09-28 | 高鸿飞 | Front shock-absorbing undercarriage device for airplane |
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| RU2258848C2 (en) * | 2003-06-30 | 2005-08-20 | Открытое акционерное общество "Авиационный комплекс им. В.С. Ильюшина" | Hydromechanical damper |
| JP2009073209A (en) * | 2007-09-18 | 2009-04-09 | Toyota Motor Corp | Landing device for movement body |
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| KR20110067289A (en) * | 2009-12-14 | 2011-06-22 | 한국항공우주연구원 | Helicopter nose landing gear to prevent cockpit intrusion |
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2012
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104192303A (en) * | 2014-09-15 | 2014-12-10 | 沈阳飞机工业（集团）有限公司 | Small nose landing gear for unmanned aerial vehicle |
| CN104192303B (en) * | 2014-09-15 | 2016-06-22 | 沈阳飞机工业（集团）有限公司 | SUAV nose-gear |
| CN104816591A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Injection molding type air-inflation-free unmanned aerial vehicle wheel on metal rim |
| CN104816592A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Injection type non-pneumatic wheel on metal rim for two-wheel electrical motorcycle |
| CN104816590A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Inflation-free automobile wheel injection-molded on metal rim |
| CN104816593A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Non-pneumatic artillery vehicle wheel formed by injection molding on metal rim |
| CN104816589A (en) * | 2015-03-27 | 2015-08-05 | 余启佳 | Air inflation-free field-in motor vehicle wheel with injection molding on metal rim |
| CN104960662A (en) * | 2015-06-01 | 2015-10-07 | 深圳市大疆创新科技有限公司 | Landing gear and unmanned aerial vehicle using the same |
| CN108482654A (en) * | 2015-06-01 | 2018-09-04 | 深圳市大疆创新科技有限公司 | Undercarriage and the unmanned vehicle for using the undercarriage |
| CN108639340A (en) * | 2018-04-12 | 2018-10-12 | 清远市巨劲科技有限公司 | One kind can pre- antiwear unmanned plane |
| CN113443130A (en) * | 2021-06-30 | 2021-09-28 | 高鸿飞 | Front shock-absorbing undercarriage device for airplane |
| CN113443130B (en) * | 2021-06-30 | 2023-07-07 | 上海捷翔航空技术有限公司 | Front damping landing gear device for airplane |
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Application publication date: 20130116 |