JP2001180232A - Tire for aircraft - Google Patents
Tire for aircraftInfo
- Publication number
- JP2001180232A JP2001180232A JP36740399A JP36740399A JP2001180232A JP 2001180232 A JP2001180232 A JP 2001180232A JP 36740399 A JP36740399 A JP 36740399A JP 36740399 A JP36740399 A JP 36740399A JP 2001180232 A JP2001180232 A JP 2001180232A
- Authority
- JP
- Japan
- Prior art keywords
- bead
- tire
- cable
- cover rubber
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
- B29C35/08—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation
- B29C35/0866—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using particle radiation
- B29C2035/0877—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould by wave energy or particle radiation using particle radiation using electron radiation, e.g. beta-rays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2030/00—Pneumatic or solid tyres or parts thereof
- B29L2030/001—Beads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60C—VEHICLE TYRES; TYRE INFLATION; TYRE CHANGING; CONNECTING VALVES TO INFLATABLE ELASTIC BODIES IN GENERAL; DEVICES OR ARRANGEMENTS RELATED TO TYRES
- B60C15/00—Tyre beads, e.g. ply turn-up or overlap
- B60C15/04—Bead cores
- B60C2015/044—Bead cores characterised by a wrapping layer
Landscapes
- Tyre Moulding (AREA)
- Tires In General (AREA)
- Heating, Cooling, Or Curing Plastics Or The Like In General (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は航空機用タイヤに関
するもので、特に高内圧、高荷重で使用される航空機用
タイヤに好適に利用できるものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an aircraft tire, and more particularly to an aircraft tire used under a high internal pressure and a high load.
【０００２】[0002]
【従来の技術】従来の航空機用タイヤは軽量・高強度の
要求が強く補強コードが有機繊維からなる複数のカーカ
スプライ構造とし、ビードワイヤーをストランドタイプ
（四角断面形状）に比較して重量当たりの強度の高い、
図８記載の断面が円形のケーブルビード１を左右一対使
用している。さらに、従来の航空機用タイヤは図７に示
す通り、一対の断面が円形のケーブルビード１の上でタ
イヤ半径方向外側にビードフィラー３を配置してなる。
該円形のケーブルビード１とビードフィラー３を包み込
むようにタイヤ内側から外側に巻き付けられた、少なく
とも１層のターンナッププライ４と、タイヤ外側から内
側に巻き付けられた、少なくとも１層のターンダウンプ
ライ５からなるカーカス層を備えている。2. Description of the Related Art Conventional aircraft tires are strongly demanded for light weight and high strength and have a plurality of carcass ply structures in which reinforcing cords are made of organic fibers, and a bead wire has a smaller weight per weight than a strand type (square cross section). High strength,
8, a pair of left and right cable beads 1 having a circular cross section is used. Further, as shown in FIG. 7, the conventional aircraft tire has a pair of bead fillers 3 arranged radially outward on a cable bead 1 having a circular cross section.
At least one turn-up ply 4 wound from the inside of the tire to the outside so as to enclose the circular cable bead 1 and the bead filler 3, and at least one turn-down ply 5 wound from the outside to the inside of the tire And a carcass layer comprising:
【０００３】上記のような、従来の航空機用タイヤでは
タイヤ加硫時の高温雰囲気における加硫ブラダーの押し
付け圧（図７中のＢ→）と、タイヤ加硫時のリフト（タ
イヤが未加硫時の大きさから加硫後の大きさに膨らむこ
と。）によってターンナッププライ４が（図７中のＰ→
の様に）引き上げられ、ケーブルビードが絞られるよう
にビードカバーゴム２のゴム流れ２ｂを生じ、ビードト
ウ部分のターンナッププライ４とケーブルビード１を分
離するべく設けられたビードカバーゴム２の厚さが図７
中薄肉化したビードトウ側のビードカバーゴムＳのよう
に確保できないといった問題が有った。[0003] As described above, in the conventional aircraft tire, the pressing pressure of the vulcanized bladder in a high temperature atmosphere during tire vulcanization (B → in FIG. 7) and the lift during tire vulcanization (the tire is unvulcanized). The turn-up ply 4 is swelled from the size at the time to the size after vulcanization) (P → in FIG. 7).
The thickness of the bead cover rubber 2 provided to separate the cable bead 1 from the turn-up ply 4 at the bead toe portion and the cable bead 1 from the turn-up ply 4 in the bead toe portion is raised so that the cable bead is squeezed. Figure 7
There was a problem that it was not possible to secure the bead cover rubber S on the bead toe side having a small thickness.
【０００４】さらに耐え難いことには、航空機用タイヤ
は図４のような著しい高荷重での使用に起因して、ター
ンナッププライ４とケーブルビード１との擦れ（以下フ
レッチングと称する。）を図４中の←Ｆ→のように生
じ、ターンナッププライ４がケーブルビードに擦られて
摩滅してしまい、ターンナッププライ４の強度低下が防
止できなかった。[0004] Even more intolerably, aircraft tires suffer from rubbing (hereinafter referred to as fretting) between the turn-up ply 4 and the cable bead 1 due to the use under extremely high loads as shown in FIG. As shown by ← F → in the middle, the turnup ply 4 was rubbed and abraded by the cable bead, and the reduction in the strength of the turnup ply 4 could not be prevented.
【０００５】[0005]
【発明が解決しようとする課題】本発明の目的は、航空
機タイヤのケーブルビード１の廻りに、ビードカバーゴ
ム２の厚さを確保し、カーカスコードのフレッチングに
よる強度低下を防止することに有る。SUMMARY OF THE INVENTION An object of the present invention is to secure the thickness of a bead cover rubber 2 around a cable bead 1 of an aircraft tire, and to prevent a decrease in strength due to fretting of a carcass cord.
【０００６】[0006]
【課題を解決するための手段】本発明によれば、トレッ
ド部の両側に連続するショルダー部から、タイヤ半径方
向内側に延びる一対のサイドウオール部に連なって配置
された、ビード部の構造が、ビードカバーゴムで全体を
包み込んだ丸型断面を有する左右一対のケーブルビード
と、該ケーブルビード廻りでタイヤ内側から外側に巻き
付けられたカーカス層と、該カーカス層のタイヤ半径方
向外側でタイヤ周方向に対して１０度から４５度、また
は０度の角度を有する複数のベルト層を備えた航空機用
タイヤにおいて、前記ビードカバーゴムの少なくとも前
記ケーブルビード側を電子線照射したことを特徴とする
航空機用タイヤが提供される。それによって、前記ビー
ドカバーゴムのケーブルビードワイヤー廻りの不必要な
ゴム流れが抑制されるとともに、ケーブルビードワイヤ
ー間に食い込んでしまう量が少なくて済むのである。According to the present invention, a structure of a bead portion arranged from a shoulder portion continuous on both sides of a tread portion to a pair of sidewall portions extending inward in a tire radial direction is provided. A pair of left and right cable beads having a round cross-section wrapped entirely in bead cover rubber, a carcass layer wound from the inside of the tire to the outside around the cable bead, and a tire circumferential direction outside the carcass layer in the tire radial direction. An aircraft tire provided with a plurality of belt layers having an angle of 10 degrees to 45 degrees or 0 degrees, wherein at least the cable bead side of the bead cover rubber is irradiated with an electron beam. Is provided. As a result, unnecessary flow of the rubber around the cable bead wire of the bead cover rubber is suppressed, and the amount of bite between the cable bead wires can be reduced.
【０００７】さらに別な本発明によれば、前記カーカス
層の補強コードがタイヤ周方向に対して７０度から９０
度の角度を有するとともに、前記ケーブルビードをタイ
ヤ内側から外側に巻き付けられた、少なくとも１層のタ
ーンナッププライと、タイヤ外側から内側に巻き付けら
れた、少なくとも１層のターンダウンプライからなる請
求項１に記載の航空機用タイヤが提供される。それによ
って、カーカス層の剛性が高まり良好なカーカス層の耐
久性能と操縦安定性能が享受できる。According to still another aspect of the present invention, the reinforcing cord of the carcass layer has a reinforcing cord of 70 to 90 degrees with respect to the tire circumferential direction.
2. The tire according to claim 1, comprising at least one turn-up ply having an angle of degree and wherein the cable bead is wound from the inside to the outside of the tire, and at least one turn-down ply wound from the outside to the inside of the tire. 2. An aircraft tire according to claim 1. Thereby, the rigidity of the carcass layer is increased, and the good durability and steering stability of the carcass layer can be enjoyed.
【０００８】さらに別な本発明によれば、前記ビードカ
バーゴムのビードトウ側の厚さをビードヒール側の厚さ
の１．５から５倍としたことを特徴とする航空機用タイ
ヤが提供される。それによって、カーカス補強コードと
ビードワイヤー間の距離を大きく確保できるので前記フ
レッチング現象をさらに有効に防止できる。According to still another aspect of the present invention, there is provided an aircraft tire characterized in that the thickness of the bead cover rubber on the bead toe side is 1.5 to 5 times the thickness on the bead heel side. Thereby, a large distance between the carcass reinforcing cord and the bead wire can be secured, so that the fretting phenomenon can be more effectively prevented.
【０００９】さらに別な本発明によれば、前記ビードカ
バーゴムの前記ケーブルビード側とカーカス層側両者を
電子線照射した航空機用タイヤが提供される。電子線に
よる加硫の効果は微視的に見ると前記ビードカバーゴム
の内部に大きい効果を表わすため、ビードカバーゴム表
面のタック（未加硫ゴムのくっつきやすさ。）を低下さ
せ難くく通常の熱加硫に比較してタック不足による、加
硫時のタイヤの故障を生じ難い利点が有る。According to still another aspect of the present invention, there is provided an aircraft tire in which both the cable bead side and the carcass layer side of the bead cover rubber are irradiated with an electron beam. Since the effect of vulcanization by electron beams is microscopically significant within the bead cover rubber, the tack on the surface of the bead cover rubber (easiness of sticking of unvulcanized rubber) is hardly reduced, and it is usually difficult to reduce the tack. There is an advantage that a failure of the tire at the time of vulcanization is less likely to occur due to insufficient tack compared to the heat vulcanization of the above.
【００１０】また、本発明によれば、トレッド部の両側
に連続するショルダー部から、タイヤ半径方向内側に延
びる一対のサイドウオール部に連なって配置された、ビ
ード部の構造が、ビードカバーゴムで全体を包み込んだ
丸型断面を有する左右一対のケーブルビードと、該ケー
ブルビード廻りでタイヤ内側から外側に巻き付けられた
カーカス層と、該カーカス層のタイヤ半径方向外側でタ
イヤ周方向に対して１０度から４５度、または０度の角
度を有する複数のベルト層を備えた航空機用タイヤにお
いて、前記ビードカバーゴムの少なくとも前記ケーブル
ビード側を加速電圧５００から１０００ｋＶ、照射線量
２５から１００ｋＧｙで電子線照射した航空機用タイヤ
の製造方法が提供される。Further, according to the present invention, the structure of the bead portion, which is arranged from the shoulder portion continuous on both sides of the tread portion to the pair of sidewall portions extending inward in the tire radial direction, is constituted by a bead cover rubber. A pair of left and right cable beads having a round cross-section enclosing the entirety, a carcass layer wound around the cable bead from the inside to the outside of the tire, and 10 degrees from the tire radial direction outside the carcass layer in the tire radial direction. In an aircraft tire provided with a plurality of belt layers having an angle of from 0 to 45 degrees or 0 degrees, at least the cable bead side of the bead cover rubber was irradiated with an electron beam at an acceleration voltage of 500 to 1000 kV and an irradiation dose of 25 to 100 kGy. A method for manufacturing an aircraft tire is provided.
【００１１】[0011]
【発明の実施の形態】以下本発明の実施の形態を図を用
いて説明するが、本発明の範囲はこれらの実施形態に限
定されないことはもちろんである。図１のビードカバー
ゴム２のケーブルビード１側に図２および図３のように
電子線照射をしてあるため、ビードカバーゴム２のケー
ブルビード１廻りの流動性が拘束され、タイヤ加硫時の
高温雰囲気における加硫ブラダーの押し付け圧（図１中
のＢ→）と、加硫時のリフトによってターンナッププラ
イ４が（図１中のＰ→の様に）引き上げられ、ケーブル
ビード１が絞られるようにビードカバーゴム２に働いて
も、本来不必要なゴム流れを生じ難くなる。その結果、
ビードトウ部分のビードカバーゴム２の厚さが確保でき
ないといった問題が効率よく軽減される。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the present invention will be described below with reference to the drawings, but it is needless to say that the scope of the present invention is not limited to these embodiments. Since the bead cover rubber 2 of FIG. 1 is irradiated with an electron beam as shown in FIGS. 2 and 3 on the cable bead 1 side, the fluidity of the bead cover rubber 2 around the cable bead 1 is restricted, and the tire cover rubber 2 is hardened during tire vulcanization. The press-up pressure of the vulcanization bladder in the high temperature atmosphere (B → in FIG. 1) and the lift during vulcanization raise the turn-up ply 4 (like P → in FIG. 1), and the cable bead 1 is squeezed. Even if it acts on the bead cover rubber 2 as described above, it becomes difficult to generate an unnecessary rubber flow. as a result,
The problem that the thickness of the bead cover rubber 2 at the bead toe portion cannot be ensured is efficiently reduced.
【００１２】さらに、図４のような著しい高荷重での使
用に起因してターンナッププライ４とケーブルビード１
とのフレッチング（図４中の←Ｆ→）に対しても、ビー
ドトウ部分のビードカバーゴム２の厚さが十分に確保で
きているため、ターンナッププライ４のフレッチングに
よる強度低下を有効に防止できる。Further, the turn-up ply 4 and the cable bead 1 due to the use under a remarkably high load as shown in FIG.
4 (← F → in FIG. 4), since the thickness of the bead cover rubber 2 at the bead toe portion is sufficiently ensured, it is possible to effectively prevent a decrease in strength of the turn-up ply 4 due to fretting. .
【００１３】さらに、図５のように前記ビードカバーゴ
ム２のビードトウ側の厚さをビードヒール側の厚さの
１．５から５倍としたことによって、大幅にターンナッ
ププライ４とケーブルビード１とを分離可能になり、タ
ーンナッププライ４のフレッチングによる強度低下をよ
り有効に防止できる。１．５倍未満ではフレッチングに
よる強度低下の防止が不十分であり、５倍超ではタイヤ
重量が増加してしまい好ましくない。さらにエアー溜ま
りなどの故障を削減するには１．５倍〜３倍が好ましい
し、徐々にビードカバーゴム２の厚さを変更することが
好ましい。Further, by making the thickness of the bead toe side of the bead cover rubber 2 from 1.5 to 5 times the thickness of the bead heel side as shown in FIG. Can be separated, and a decrease in strength due to fretting of the turn-up ply 4 can be more effectively prevented. If it is less than 1.5 times, it is not enough to prevent the strength from being reduced by fretting, and if it is more than 5 times, the tire weight increases, which is not preferable. In order to further reduce troubles such as air pockets, the thickness is preferably 1.5 to 3 times, and it is preferable to gradually change the thickness of the bead cover rubber 2.
【００１４】さらに、図６のようにビードカバーゴム２
の両側、すなわちケーブルビード側とターンナッププラ
イ側に電子線を照射することで、さらに強固なビードカ
バーゴム２が確保できる。その際、加速電圧５００から
１０００ｋＶ、照射線量２５から１００ｋＧｙとするこ
とが望ましく、加速電圧５００ｋＶおよび照射線量２５
ｋＧｙ未満ではビードカバーゴム２の流動性を押さえる
効果が少なく、また１０００ｋＶおよび１００ｋＧｙ超
では実際の加硫が進行してしまい、加硫故障を生じ易く
なり好ましくない。Further, as shown in FIG.
By irradiating the electron beam to both sides, that is, the cable bead side and the turn-up ply side, a stronger bead cover rubber 2 can be secured. At this time, it is preferable that the acceleration voltage is 500 to 1000 kV and the irradiation dose is 25 to 100 kGy.
If it is less than kGy, the effect of suppressing the fluidity of the bead cover rubber 2 is small, and if it is more than 1000 kV and 100 kGy, actual vulcanization proceeds, and vulcanization failure tends to occur, which is not preferable.
【００１５】[0015]
【実施例】以下、本発明を実施例にもとづき説明する。
未加硫ビードカバーゴムの厚さを２ｍｍ、ケーブルビー
ドの構造は１本の芯線に４層のビードワイヤーを螺旋巻
きした構造で、加速電圧７５０ｋＶ、照射線量５０ｋＧ
ｙ照射として、タイヤサイズ５０×２０．０Ｒ２２ ２
６ＰＲの航空機用タイヤを下表の通り、ビード側のみ電
子線照射した実施例１とビード側とカーカス側両面に照
射した実施例２を試作した。また、実施例３においては
未加硫ビードカバーゴムの厚さを２ｍｍおよび部分的に
４ｍｍとし両面に電子線を照射した。さらに、両側とも
電子線照射しない従来例と、ビードカバーゴムのカーカ
ス側のみ電子線照射した比較例１を、実施例と同様にし
て試作し、評価結果を表1に纏めた。DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below based on embodiments.
The thickness of the uncured bead cover rubber is 2 mm, and the structure of the cable bead is a structure in which four layers of bead wires are spirally wound around one core wire, with an acceleration voltage of 750 kV and an irradiation dose of 50 kG.
For y irradiation, tire size 50 × 20.0R22 2
As shown in the table below, a prototype of Example 1 in which only the bead side was irradiated with the electron beam and Example 2 in which both the bead side and the carcass side were irradiated with the 6PR aircraft tire were prepared. In Example 3, the thickness of the unvulcanized bead cover rubber was 2 mm and partially 4 mm, and both surfaces were irradiated with electron beams. Further, a conventional example in which electron beam irradiation was not performed on both sides and a comparative example 1 in which electron beam irradiation was performed only on the carcass side of the bead cover rubber were prototyped in the same manner as in the example, and the evaluation results are summarized in Table 1.
【表１】 [Table 1]
【００１６】（ビードカバー加硫後ゴム厚さ）タイヤ周
上６ヶ所の径方向ビード部断面を取り、ビードトウ側の
ビードカバーゴム厚さの平均を取った。(Rubber thickness after vulcanization of bead cover) Cross sections of six radial bead portions on the tire circumference were taken, and the average thickness of the bead cover rubber on the bead toe side was taken.
【００１７】（室内ドラム耐久性試験走行後のカーカス
コード強度）試験内圧１７７ｐｓｉ、試験荷重４５２０
０ＬＢＳ、ランディング走行（１８０から４０）ｍｐｈ
×３５秒＋タクシー走行４０ｍｐｈ×９２秒を１サイク
ルとして、１５０サイクル終了後、タイヤ周上２ヶ所か
ら注意深くビードトウ部のターンナップカーカスコード
５本ずつを丁寧にはがし、１０本の破断強度を測定し平
均を取り比較例を１００とした指数で表示した。表中数
値が大きい方が残存強度が大きく、耐フレッチング性能
が良好なことをしめしている。(Carcass cord strength after indoor drum durability test run) Test internal pressure 177 psi, test load 4520
0LBS, Landing (180 to 40) mph
X 35 seconds + taxi traveling 40 mph x 92 seconds as one cycle, and after 150 cycles, carefully remove 5 turn-up carcass cords of bead toe part carefully from two places on the tire circumference and measure the breaking strength of 10 pieces. The average was taken and indicated by an index with the comparative example taken as 100. The larger the value in the table, the higher the residual strength and the better the fretting resistance.
【００１８】以上説明した通り、ビードカバーゴム２の
少なくとも前記ケーブルビード側を電子線照射すること
によって、不要なビードカバーゴム流れが有効に抑制さ
れ極めて過酷な室内ドラム耐久性試験走行後でも十分な
カーカスコード残存強度が維持可能になる事が理解され
る。As described above, by irradiating at least the cable bead side of the bead cover rubber 2 with an electron beam, unnecessary flow of the bead cover rubber is effectively suppressed, and sufficient even after the extremely severe indoor drum durability test run. It is understood that the carcass cord residual strength can be maintained.
【００１９】[0019]
【発明の効果】本発明によれば、航空機タイヤのケーブ
ルビード１の廻り、特にビードトウ側に、ビードカバー
ゴム２の厚さを十分に確保することが可能になり、ター
ンナッププライとケーブルビードのフレッチングによる
ターンナッププライの強度低下を有効に防止することが
できる。According to the present invention, it is possible to sufficiently secure the thickness of the bead cover rubber 2 around the cable bead 1 of the aircraft tire, particularly on the bead toe side, and the turnup ply and the cable bead can be secured. A decrease in the strength of the turn-up ply due to fretting can be effectively prevented.
【図１】本発明に係る航空機タイヤのビード部、部分径
方向断面図である。FIG. 1 is a partial radial sectional view of a bead portion of an aircraft tire according to the present invention.
【図２】本発明に係るビードカバーゴム電子線照射方向
の説明図である。FIG. 2 is an explanatory view of a bead cover rubber electron beam irradiation direction according to the present invention.
【図３】本発明に係るビードカバーゴムをケーブルビー
ドに巻き付ける説明図である。FIG. 3 is an explanatory view of winding a bead cover rubber according to the present invention around a cable bead.
【図４】航空機タイヤのビード部のフレッチング（摩
擦）説明図である。FIG. 4 is an explanatory diagram of fretting (friction) of a bead portion of an aircraft tire.
【図５】本発明に係る他の航空機タイヤのビード部、部
分径方向断面図である。FIG. 5 is a partial radial sectional view of a bead portion of another aircraft tire according to the present invention.
【図６】本発明に係る他のビードカバーゴム電子線照射
方向の説明図である。FIG. 6 is an explanatory diagram of another bead cover rubber electron beam irradiation direction according to the present invention.
【図７】従来の航空機タイヤのビード部、部分径方向断
面図である。FIG. 7 is a partial radial sectional view of a bead portion of a conventional aircraft tire.
【図８】従来の航空機タイヤのビードワイヤー、部分径
方向断面図である。FIG. 8 is a partial radial sectional view of a bead wire of a conventional aircraft tire.
１ ケーブルビード ２ ビードカバーゴム ２ａ 厚肉化したビードカバーゴム ２ｂ ゴム流れを起こしたビードカバーゴム ３ ビードフィラーゴム ４ ターンナッププライ ５ ターンダウンプライ ６ サイドゴム ７ ビードトウ ８ ビードヒール ９ リム Ｂ 加硫ブラダーの押し付け圧 Ｆ フレッチング（擦れ）発生部 Ｇ ビードトウ側のビードカバーゴムの厚さ Ｐ カーカスターンナッププライの引き上げ力 Ｓ 薄肉化したビードトウ側のビードカバーゴム Ｘ 電子線 DESCRIPTION OF SYMBOLS 1 Cable bead 2 Bead cover rubber 2a Thick bead cover rubber 2b Bead cover rubber which caused rubber flow 3 Bead filler rubber 4 Turnup ply 5 Turndown ply 6 Side rubber 7 Bead toe 8 Bead heel 9 Rim B Pressing vulcanized bladder Pressure F Fretting (rubbing) generating part G Thickness of bead cover rubber on bead toe side P Lifting force of carcass turn-up ply S Bead cover rubber on bead toe side thinned X Electron beam
───────────────────────────────────────────────────── フロントページの続き (51)Int.Cl.7 識別記号 ＦＩ テーマコート゛(参考） Ｂ６０Ｃ 9/18 Ｂ６０Ｃ 9/18 Ｈ 15/00 15/00 Ｇ // Ｂ２９Ｋ 21:00 Ｂ２９Ｋ 21:00 105:24 105:24 Ｂ２９Ｌ 30:00 Ｂ２９Ｌ 30:00 ──────────────────────────────────────────────────の Continued on the front page (51) Int.Cl. 7 Identification symbol FI Theme coat ゛ (Reference) B60C 9/18 B60C 9/18 H 15/00 15/00 G // B29K 21:00 B29K 21:00 105 : 24 105: 24 B29L 30:00 B29L 30:00
Claims (5)
部から、タイヤ半径方向内側に延びる一対のサイドウオ
ール部に連なって配置された、ビード部の構造が、ビー
ドカバーゴムで全体を包み込んだ丸型断面を有する左右
一対のケーブルビードと、該ケーブルビード廻りでタイ
ヤ内側から外側に巻き付けられたカーカス層と、該カー
カス層のタイヤ半径方向外側でタイヤ周方向に対して１
０度から４５度、または０度の角度を有する複数のベル
ト層を備えた航空機用タイヤにおいて、前記ビードカバ
ーゴムの少なくとも前記ケーブルビード側を電子線照射
したことを特徴とする航空機用タイヤ。A bead structure, which is arranged continuously from a shoulder portion continuous on both sides of a tread portion to a pair of sidewall portions extending inward in a tire radial direction, the bead portion having a round shape wrapped entirely in a bead cover rubber. A pair of left and right cable beads having a cross section, a carcass layer wound around the cable bead from the inside to the outside of the tire,
An aircraft tire including a plurality of belt layers having an angle of 0 to 45 degrees or 0 degrees, wherein at least the cable bead side of the bead cover rubber is irradiated with an electron beam.
方向に対して７０度から９０度の角度を有するととも
に、前記ケーブルビードをタイヤ内側から外側に巻き付
けられた、少なくとも１層のターンナッププライと、タ
イヤ外側から内側に巻き付けられた、少なくとも１層の
ターンダウンプライからなる請求項１に記載の航空機用
タイヤ。2. A turnup ply of at least one layer, wherein the reinforcing cord of the carcass layer has an angle of 70 to 90 degrees with respect to the tire circumferential direction, and the cable bead is wound from the inside to the outside of the tire. The aircraft tire according to claim 1, comprising at least one turn-down ply wound from the outside to the inside of the tire.
厚さをビードヒール側の厚さの１．５から５倍としたこ
とを特徴とする請求項１または２に記載の航空機用タイ
ヤ。3. The aircraft tire according to claim 1, wherein a thickness of the bead cover rubber on a bead toe side is 1.5 to 5 times a thickness on a bead heel side.
ード側とカーカス層側両者を電子線照射したことを特徴
とする請求項１から３のいずれか１項に記載の航空機用
タイヤ。4. The aircraft tire according to claim 1, wherein both the cable bead side and the carcass layer side of the bead cover rubber are irradiated with an electron beam.
部から、タイヤ半径方向内側に延びる一対のサイドウオ
ール部に連なって配置された、ビード部の構造が、ビー
ドカバーゴムで全体を包み込んだ丸型断面を有する左右
一対のケーブルビードと、該ケーブルビード廻りでタイ
ヤ内側から外側に巻き付けられたカーカス層と、該カー
カス層のタイヤ半径方向外側でタイヤ周方向に対して１
０度から４５度、または０度の角度を有する複数のベル
ト層を備えた航空機用タイヤにおいて、前記ビードカバ
ーゴムの少なくとも前記ケーブルビード側を加速電圧５
００から１０００ｋＶ、照射線量２５から１００ｋＧｙ
で電子線照射したことを特徴とする航空機用タイヤの製
造方法。5. A round bead structure in which the entire bead structure is wrapped around a bead cover rubber, which is arranged continuously from a shoulder portion continuous on both sides of the tread portion to a pair of sidewall portions extending inward in the tire radial direction. A pair of left and right cable beads having a cross section, a carcass layer wound around the cable bead from the inside to the outside of the tire,
In an aircraft tire having a plurality of belt layers having an angle of 0 to 45 degrees or 0 degrees, at least the cable bead side of the bead cover rubber has an acceleration voltage of 5 °.
00 to 1000 kV, irradiation dose 25 to 100 kGy
A method for manufacturing an aircraft tire, comprising irradiating an electron beam with the method.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP36740399A JP4079565B2 (en) | 1999-12-24 | 1999-12-24 | Aircraft tire and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP36740399A JP4079565B2 (en) | 1999-12-24 | 1999-12-24 | Aircraft tire and manufacturing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2001180232A true JP2001180232A (en) | 2001-07-03 |
| JP4079565B2 JP4079565B2 (en) | 2008-04-23 |
Family
ID=18489236
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP36740399A Expired - Fee Related JP4079565B2 (en) | 1999-12-24 | 1999-12-24 | Aircraft tire and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP4079565B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007076549A (en) * | 2005-09-15 | 2007-03-29 | Sumitomo Rubber Ind Ltd | Pneumatic tire |
| JP2008094264A (en) * | 2006-10-12 | 2008-04-24 | Bridgestone Corp | Pneumatic radial tire |
| CN104118280A (en) * | 2014-07-29 | 2014-10-29 | 中橡集团曙光橡胶工业研究设计院 | Aviation tire with durable edge and preparation method of aviation tire |
-
1999
- 1999-12-24 JP JP36740399A patent/JP4079565B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007076549A (en) * | 2005-09-15 | 2007-03-29 | Sumitomo Rubber Ind Ltd | Pneumatic tire |
| JP4482504B2 (en) * | 2005-09-15 | 2010-06-16 | 住友ゴム工業株式会社 | Pneumatic tire |
| JP2008094264A (en) * | 2006-10-12 | 2008-04-24 | Bridgestone Corp | Pneumatic radial tire |
| CN104118280A (en) * | 2014-07-29 | 2014-10-29 | 中橡集团曙光橡胶工业研究设计院 | Aviation tire with durable edge and preparation method of aviation tire |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4079565B2 (en) | 2008-04-23 |
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