JP3102949B2 - Heat resistant material for solid rocket - Google Patents
Heat resistant material for solid rocketInfo
- Publication number
- JP3102949B2 JP3102949B2 JP04107282A JP10728292A JP3102949B2 JP 3102949 B2 JP3102949 B2 JP 3102949B2 JP 04107282 A JP04107282 A JP 04107282A JP 10728292 A JP10728292 A JP 10728292A JP 3102949 B2 JP3102949 B2 JP 3102949B2
- Authority
- JP
- Japan
- Prior art keywords
- heat
- resistant material
- fiber
- solid rocket
- asbestos
- 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.)
- Expired - Lifetime
Links
- 239000007787 solid Substances 0.000 title claims description 7
- 239000003779 heat-resistant material Substances 0.000 title description 8
- 239000000835 fiber Substances 0.000 claims description 19
- 229920001971 elastomer Polymers 0.000 claims description 9
- 239000005060 rubber Substances 0.000 claims description 9
- 239000000203 mixture Substances 0.000 claims description 8
- VTHJTEIRLNZDEV-UHFFFAOYSA-L magnesium dihydroxide Chemical compound [OH-].[OH-].[Mg+2] VTHJTEIRLNZDEV-UHFFFAOYSA-L 0.000 claims description 6
- 239000000347 magnesium hydroxide Substances 0.000 claims description 6
- 229910001862 magnesium hydroxide Inorganic materials 0.000 claims description 6
- 229920003002 synthetic resin Polymers 0.000 claims description 6
- 239000000057 synthetic resin Substances 0.000 claims description 6
- 239000011159 matrix material Substances 0.000 claims description 5
- 239000011777 magnesium Substances 0.000 claims description 2
- 239000012763 reinforcing filler Substances 0.000 claims description 2
- 238000002156 mixing Methods 0.000 claims 1
- 239000011819 refractory material Substances 0.000 claims 1
- 239000010425 asbestos Substances 0.000 description 12
- 229910052895 riebeckite Inorganic materials 0.000 description 12
- 230000000052 comparative effect Effects 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 5
- 230000003628 erosive effect Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 239000000945 filler Substances 0.000 description 3
- 244000043261 Hevea brasiliensis Species 0.000 description 2
- VEXZGXHMUGYJMC-UHFFFAOYSA-N Hydrochloric acid Chemical compound Cl VEXZGXHMUGYJMC-UHFFFAOYSA-N 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000002557 mineral fiber Substances 0.000 description 2
- 229920003052 natural elastomer Polymers 0.000 description 2
- 229920001194 natural rubber Polymers 0.000 description 2
- 229920003051 synthetic elastomer Polymers 0.000 description 2
- 239000005061 synthetic rubber Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229920000181 Ethylene propylene rubber Polymers 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 229910004298 SiO 2 Inorganic materials 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000002542 deteriorative effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 238000004898 kneading Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000010525 oxidative degradation reaction Methods 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 229920001225 polyester resin Polymers 0.000 description 1
- 239000004645 polyester resin Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000012744 reinforcing agent Substances 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Landscapes
- Compositions Of Macromolecular Compounds (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は耐熱性及び断熱性に優れ
た固体ロケットの耐熱材料に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a heat resistant material for a solid rocket having excellent heat resistance and heat insulation.
【０００２】[0002]
【従来の技術】固体ロケットは火薬である固体推進薬を
燃焼室で高圧力で燃焼させ、ノズルから高温燃焼ガスを
噴出させて推進力を得ている。２０００℃を越す燃焼ガ
スと接触する燃焼室内壁は強力な耐熱材料で被覆する必
要があり、耐熱性，断熱性に優れ、強度も強いアスベス
ト繊維を補強及び充填剤としたゴム又は合成樹脂複合剤
が用いられていた。2. Description of the Related Art A solid rocket burns a solid propellant, which is an explosive, at a high pressure in a combustion chamber and ejects a high-temperature combustion gas from a nozzle to obtain propulsion. The interior of the combustion chamber that comes into contact with combustion gas exceeding 2000 ° C must be coated with a strong heat-resistant material, and has excellent heat resistance and heat insulation properties, and a rubber or synthetic resin composite with asbestos fiber as a reinforcement and filler that has high strength. Was used.
【０００３】[0003]
【発明が解決しようとする課題】しかし、アスベストは
アスベスト繊維が飛散して、環境を悪化させる恐れがあ
り、近年公害問題を生じ、代替品の開発が望まれてい
た。However, asbestos has a risk of asbestos fibers scattering and deteriorating the environment. In recent years, asbestos has caused pollution problems, and there has been a demand for the development of alternatives.
【０００４】[0004]
【課題を解決するための手段】本発明者は、アスベスト
に代わる補強及び充填剤となり得る性能を有する天然鉱
物繊維を調査した結果、化学組成がｎＭｇ(ＯＨ)2・ｍ
Ｆｅ2Ｏ3 ・ｌＳｉＯ2である水酸化マグネシウム繊維が
アスベスト繊維と異なり、酸に溶解するので廃品処理も
容易であり公害を起こすこともなく、又炭素繊維と異な
り酸化劣化を起こさず熱伝導率も低いので断熱性に優れ
ていることを見出し、本発明に至ったものである。The inventors of the present invention have investigated natural mineral fibers having a performance as a reinforcing agent and a filler in place of asbestos. As a result, the chemical composition of the natural mineral fibers is nMg (OH) 2 · m.
Unlike asbestos fiber, magnesium hydroxide fiber, which is Fe 2 O 3 .lSiO 2 , dissolves in acid, so it is easy to dispose of waste and does not cause pollution. Unlike carbon fiber, it does not cause oxidative degradation and thermal conductivity. Therefore, it was found that the heat insulating property was excellent, and the present invention was achieved.
【０００５】即ち本発明は、ゴム又は合成樹脂からなる
マトリックスの耐熱及び補強充填剤として、繊維の長さ
１mm以上のｎＭｇ（ＯＨ） 2 ・ｍＦｅ 2 Ｏ 3 ・ｌＳｉＯ
2 （式中、ｎは８０〜９０％、ｍは６〜８％、ｌは０．
５〜５％を示す。）からなる水酸化マグネシウム繊維を
５〜６０重量％配合した組成物を用いたことを特徴とす
る固体ロケットの耐熱材料に係わるものである。That is, the present invention comprises a rubber or a synthetic resin.
Fiber length as matrix heat and reinforcing filler
1mm or morenMg (OH) Two ・ MFe Two O Three ・ LSiO
Two (In the formula, n is 80 to 90%, m is 6 to 8%, and l is 0 to 0%.)
Indicates 5-5%. Consisting ofMagnesium hydroxide fiber
Characterized in that a composition containing 5 to 60% by weight is used.
Related to heat-resistant materials for solid rockets.
【０００６】本発明に使用する水酸化マグネシウム繊維
は、組成中Ｍｇ(ＯＨ)2 は８０〜９０％，Ｆｅ2Ｏ3 は
６〜８％，ＳｉＯ2 は０.5〜５％，であり塩酸に溶解す
る。繊維長は長いもので３０mmであり単繊維の直径は
０.1μｍ〜１０μｍが大半を占めている。水酸化マグネ
シウム繊維は、アスベスト繊維と異なり、平板状の結晶
構造を有する。また、引張強さは１０００ＭＰａを示
し、アスベスト繊維より劣るがガラス繊維並の強度を有
する。[0006] magnesium hydroxide fibers used in the present invention, the composition in Mg (OH) 2 is 80-90% Fe 2 O 3 is 6-8% SiO 2 is from 0.5 to 5% hydrochloric acid Dissolve in The fiber length is long, 30 mm, and the diameter of the single fiber is mostly 0.1 μm to 10 μm. Magnesium hydroxide fiber has a flat crystal structure unlike asbestos fiber. Also, the tensile strength is 1000 MPa, which is inferior to asbestos fiber, but has the same strength as glass fiber.
【０００７】本発明に用いる水酸化マグネシウム繊維の
長さは１mm以上でなければならない。繊維長がより短い
粉状のものは焼食速度が大幅に増大するので好ましくな
い。又、繊維の充填量は５乃至６０重量％であることを
要する。５重量％以下では耐熱性能力が期待できず、一
方６０重量％以上では未硬化配合物の粘度、硬さが上昇
し正常な加工操作が出来ず、均質な圧延シートが得られ
ない。[0007] The length of the magnesium hydroxide fiber used in the present invention must be 1 mm or more. A powder having a shorter fiber length is not preferred because the erosion rate is greatly increased. Further, the filling amount of the fibers is required to be 5 to 60% by weight. If it is less than 5% by weight, the heat resistance cannot be expected, while if it is more than 60% by weight, the viscosity and hardness of the uncured compound increase, so that normal working operations cannot be performed and a homogeneous rolled sheet cannot be obtained.
【０００８】マトリックスとして使用されるゴム及び合
成樹脂としては従来公知の天然ゴム、合成ゴム及びフェ
ノール樹脂，ポリエステル樹脂，エポキシ樹脂等の合成
樹脂を使用し得る。As the rubber and synthetic resin used as the matrix, conventionally known natural rubbers, synthetic rubbers and synthetic resins such as phenolic resins, polyester resins and epoxy resins can be used.
【０００９】[0009]
【実施例】以下本発明を実施例及び比較例について説明
するが、本発明はこれらの実施例に限定されるものでは
ない。表１に示す配合組成で本発明の実施例及び従来の
アスベスト配合の比較例のロケットモーター用耐熱ゴム
材料を作製した。配合組成物を混練ロール温度６０℃で
常法に従い３０分間混練した。混練を終了したゴム組成
物を厚さ４mmに圧延した後、１５０℃の熱プレスで３０
分間プレス硬化を行った。硬化終了したゴム板はＪＩＳ
ーＫー６３０１に従い機械的性質を調べた。その結果を
表２に示す。EXAMPLES The present invention will be described below with reference to examples and comparative examples, but the present invention is not limited to these examples. With the composition shown in Table 1, heat-resistant rubber materials for rocket motors of Examples of the present invention and Comparative Examples of conventional asbestos formulations were produced. The compounded composition was kneaded at a kneading roll temperature of 60 ° C. for 30 minutes according to a conventional method. After the kneaded rubber composition is rolled to a thickness of 4 mm, it is heated at 150 ° C. by a hot press to obtain
Press hardening was performed for minutes. The cured rubber plate is JIS
Mechanical properties were examined according to -K-6301. Table 2 shows the results.
【００１０】[0010]
【表１】 [Table 1]
【００１１】＊数字は重量％を示す。* Numbers indicate% by weight.
【００１２】＊＊繊維の長さ：１mm〜３０mm** Fiber length: 1 mm to 30 mm
【００１３】[0013]
【表２】 [Table 2]
【００１４】＊Ｐａ（パスカル）：圧力単位 Ｎ／ｍ2 表２から実施例のものは比較例より引張強さがやや劣る
が、伸びは約４倍も大きく優れた機械的特性を示すこと
がわかる。* Pa (Pascal): pressure unit N / m 2 According to Table 2, the tensile strength of the example is slightly lower than that of the comparative example, but the elongation is about four times larger and exhibits excellent mechanical properties. Recognize.
【００１５】上記の様にして得られた硬化ゴム板からな
る耐熱材料シートの耐熱性及び燃焼抑制力を公知の固体
ロケット燃焼試験によって評価を行った。即ち入口部の
口径８cm，長さ９cmのコーン状ロケットノズルの内面に
接着剤で貼付し耐熱試験用の試料に供した。その結果を
図１に示す。The heat resistance and the combustion suppressing power of the heat resistant material sheet made of the cured rubber plate obtained as described above were evaluated by a known solid rocket combustion test. That is, an adhesive was applied to the inner surface of a cone-shaped rocket nozzle having a diameter of 8 cm and a length of 9 cm at the inlet portion, and used as a sample for a heat resistance test. The result is shown in FIG.
【００１６】図１において横軸は試料表面の燃焼ガス流
速をマッハ数で示し、縦軸はその流速における試験後に
測定した試料の焼食速度を示し、各曲線は実施例及び比
較例で得られる耐熱シートについて、燃焼ガス流速の各
マッハ数域における試料の燃焼速度を示す。In FIG. 1, the horizontal axis indicates the combustion gas flow rate on the sample surface in Mach number, the vertical axis indicates the erosion rate of the sample measured after the test at that flow rate, and each curve is obtained in Examples and Comparative Examples. For the heat-resistant sheet, the burning speed of the sample in each Mach number region of the burning gas flow velocity is shown.
【００１７】図１から本発明による耐熱材料は、従来か
ら使用されているアスベスト繊維を充填剤とした比較例
試料と比べて、低マッハ数（低ガス流速）域では焼食速
度が低く優れているが、高マッハ数（高ガス流速）域で
は焼食速度がやや大きくなっていることがわる。FIG. 1 shows that the heat-resistant material according to the present invention has a lower erosion rate in a low Mach number (low gas flow rate) range as compared with a comparative sample using asbestos fiber as a filler, which has been conventionally used. However, in the high Mach number (high gas flow rate) range, the erosion rate is slightly higher.
【００１８】本実験例ではマトリックスゴムとしてエチ
レンプロピレンゴムを使用したが他の合成ゴムや天然ゴ
ム又は合成樹脂であっても良い。又マトリックス原料が
液状の場合は注形型を用いた注形法で試料を作製する
か、又はコーン状ロケットノズルの内壁に直接塗布を繰
り返し所定の厚さにしても良い。In this experimental example, ethylene propylene rubber was used as the matrix rubber, but other synthetic rubber, natural rubber or synthetic resin may be used. When the matrix material is liquid, a sample may be prepared by a casting method using a casting mold, or a predetermined thickness may be obtained by directly coating the inner wall of the cone-shaped rocket nozzle.
【００１９】[0019]
【発明の効果】本発明による固体ロケットの耐熱材料は
従来のアスベスト入り耐熱材料と比較して低ガス流速で
は耐焼損性に優れており、機械的性質は破断時の伸びが
大幅に向上している。又、公害を生じさせないためにア
スベスト代替品として十二分に使用することが可能であ
る。The heat-resistant material of the solid rocket according to the present invention is superior in burn-out resistance at a low gas flow rate as compared with the conventional heat-resistant material containing asbestos, and the mechanical properties show that the elongation at break is greatly improved. I have. In addition, it can be more than enough to be used as an asbestos substitute to prevent pollution.
【図１】実施例と比較例の燃焼試験の結果を示す図であ
る。FIG. 1 is a diagram showing the results of combustion tests of an example and a comparative example.
───────────────────────────────────────────────────── フロントページの続き (58)調査した分野(Int.Cl.7，ＤＢ名) F02K 9/34 C08K 7/08 ──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. 7 , DB name) F02K 9/34 C08K 7/08
Claims (1)
の耐熱及び補強充填剤として、繊維の長さ１mm以上のｎ
Ｍｇ（ＯＨ） 2 ・ｍＦｅ 2 Ｏ 3 ・ｌＳｉＯ 2 （式中、ｎは８
０〜９０％、ｍは６〜８％、ｌは０．５〜５％を示
す。）からなる水酸化マグネシウム繊維を５〜６０重量
％配合した組成物を用いたことを特徴とする固体ロケッ
トの耐熱材料。1. As a heat-resistant and reinforcing filler for a matrix made of rubber or synthetic resin, n having a fiber length of 1 mm or more is used.
Mg (OH) 2 .mFe 2 O 3 .lSiO 2 (where n is 8
0 to 90%, m is 6 to 8%, l is 0.5 to 5%
You. Refractory material of solid rocket, characterized in that the magnesium hydroxide fiber comprising) with the composition obtained by blending 5 to 60 wt%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP04107282A JP3102949B2 (en) | 1992-04-27 | 1992-04-27 | Heat resistant material for solid rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP04107282A JP3102949B2 (en) | 1992-04-27 | 1992-04-27 | Heat resistant material for solid rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH05302546A JPH05302546A (en) | 1993-11-16 |
| JP3102949B2 true JP3102949B2 (en) | 2000-10-23 |
Family
ID=14455132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP04107282A Expired - Lifetime JP3102949B2 (en) | 1992-04-27 | 1992-04-27 | Heat resistant material for solid rocket |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3102949B2 (en) |
-
1992
- 1992-04-27 JP JP04107282A patent/JP3102949B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH05302546A (en) | 1993-11-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104629374B (en) | A kind of silicon rubber base heat insulation composite material of resistance to ablation and preparation method thereof | |
| CN110054992B (en) | A kind of ablation-resistant lightweight silicone rubber thermal insulation coating | |
| US5661198A (en) | Ablator compositions | |
| JPS58154743A (en) | Elastomeric composition reinforced with alumamide polymer and powder filler for use as rocket engine insulation | |
| EP1198500A1 (en) | Rocket motor insulation containing hydrophobic particles | |
| CN112225998B (en) | Ablation-resistant thermal insulation material with excellent mechanical property for high-energy propellant and preparation method thereof | |
| CN109232848B (en) | DDI lining layer for solid rocket engine medicine loading and application method thereof | |
| US4332631A (en) | Castable silicone based magnesium fueled propellant | |
| CN105566919A (en) | Carbon cloth and heat-vulcanized silicone rubber based ablation-resistant composite material and preparation method thereof | |
| CN115368822B (en) | Porcelain Gao Wenwei-shaped silicon rubber protective material and preparation method thereof | |
| CN109486201B (en) | Self-crosslinking type silicon-boron-containing high polymer-based ablation-resistant heat-insulating material and preparation method thereof | |
| Sureshkumar et al. | Studies on the properties of EPDM–CSE blend containing HTPB for case‐bonded solid rocket motor insulation | |
| US11306683B2 (en) | Precursor compositions for an insulation and insulated rocket motors | |
| JP3102949B2 (en) | Heat resistant material for solid rocket | |
| BR112021003627A2 (en) | barrier coating resin formulations, barrier coatings formed from the barrier coating resin formulations, articles comprising the barrier coatings, rocket engines comprising the barrier coatings, and related methods". | |
| JPS6319474B2 (en) | ||
| CN102863724A (en) | Halogen-free non-phosphorus poly-n-butyl methacrylate coating material used for propellant casting and coating and preparation method for coating material | |
| CN117551351A (en) | An efficient fireproof silicone rubber compound and its preparation method and application | |
| US3459701A (en) | Ceramic filled plastic system | |
| US3562304A (en) | Ablative composition of matter | |
| CN109608712A (en) | One kind is flammable insulation layer formula and its manufacturing method | |
| JP3144429B2 (en) | Insulation for rocket motor | |
| JPH0713148B2 (en) | Solid Rocket Propellant Restrictor | |
| JP2006096800A (en) | Insulation material | |
| Kitinirunkul et al. | Effect of Antimony Trioxide and Carbon Black on the Mechanical Properties and Ablation Properties of Liner Insulation in Rocket Motors |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| S531 | Written request for registration of change of domicile |
Free format text: JAPANESE INTERMEDIATE CODE: R313532 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20070825 Year of fee payment: 7 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080825 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080825 Year of fee payment: 8 |
|
| S531 | Written request for registration of change of domicile |
Free format text: JAPANESE INTERMEDIATE CODE: R313531 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080825 Year of fee payment: 8 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090825 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090825 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100825 Year of fee payment: 10 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110825 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110825 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120825 Year of fee payment: 12 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120825 Year of fee payment: 12 |
|
| S533 | Written request for registration of change of name |
Free format text: JAPANESE INTERMEDIATE CODE: R313533 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120825 Year of fee payment: 12 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| EXPY | Cancellation because of completion of term | ||
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120825 Year of fee payment: 12 |