TWI230222B - Insulator forming method and device thereof for a rocket motor casing - Google Patents
Insulator forming method and device thereof for a rocket motor casing Download PDFInfo
- Publication number
- TWI230222B TWI230222B TW92132808A TW92132808A TWI230222B TW I230222 B TWI230222 B TW I230222B TW 92132808 A TW92132808 A TW 92132808A TW 92132808 A TW92132808 A TW 92132808A TW I230222 B TWI230222 B TW I230222B
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- Taiwan
- Prior art keywords
- steel shell
- thermal insulation
- lining
- insulation lining
- rocket
- Prior art date
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- 238000000034 method Methods 0.000 title claims abstract description 44
- 239000012212 insulator Substances 0.000 title abstract 8
- 238000005086 pumping Methods 0.000 claims abstract description 5
- 229910000831 Steel Inorganic materials 0.000 claims description 104
- 239000010959 steel Substances 0.000 claims description 104
- 238000009413 insulation Methods 0.000 claims description 83
- 238000009434 installation Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 238000000605 extraction Methods 0.000 claims 1
- 239000011148 porous material Substances 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 abstract description 4
- 238000009423 ventilation Methods 0.000 abstract 1
- UQMRAFJOBWOFNS-UHFFFAOYSA-N butyl 2-(2,4-dichlorophenoxy)acetate Chemical compound CCCCOC(=O)COC1=CC=C(Cl)C=C1Cl UQMRAFJOBWOFNS-UHFFFAOYSA-N 0.000 description 20
- 238000004519 manufacturing process Methods 0.000 description 6
- 230000008878 coupling Effects 0.000 description 5
- 238000010168 coupling process Methods 0.000 description 5
- 238000005859 coupling reaction Methods 0.000 description 5
- 239000010410 layer Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 241001674048 Phthiraptera Species 0.000 description 1
- 239000004743 Polypropylene Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 238000005187 foaming Methods 0.000 description 1
- 239000003721 gunpowder Substances 0.000 description 1
- 229910052738 indium Inorganic materials 0.000 description 1
- APFVFJFRJDLVQX-UHFFFAOYSA-N indium atom Chemical group [In] APFVFJFRJDLVQX-UHFFFAOYSA-N 0.000 description 1
- 150000002576 ketones Chemical class 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003960 organic solvent Substances 0.000 description 1
- -1 polypropylene Polymers 0.000 description 1
- 229920001155 polypropylene Polymers 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000011265 semifinished product Substances 0.000 description 1
- 210000002784 stomach Anatomy 0.000 description 1
- 238000004073 vulcanization Methods 0.000 description 1
Landscapes
- Laminated Bodies (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
Description
1230222 五、發明說明（1) 【發明所屬 本發明係 置，特別是 襯能緊密的 【先前技術 在火箭發 需結合一絕 製成。在火 構件及火藥 、，以提升 一般而言 工貼製法、 就手工貼 酮之黏著劑 内壁，最後 易於實行， 間極易產生 存在氣泡， 手工貼製法 酮溶劑亦有 就模壓法 接著將預製 模具由絕熱 該鋼殼之内 之技術領域】 關於一種火箭鋼殼之絕熱内襯成形方法及其穿 關於利用氣袋加壓及抽真空方式，使一絕熱^ 結合於一鋼殼内之成形方法及其裝置。 ] 動機之製造上，火箭發動機之鋼殼内壁通常必 熱内襯。該絕熱内襯係由數個耐熱橡膠層堆疊 箭發射時，該絕熱内襯係用以避免該鋼殼内之 受到該鋼殼外壁與空氣摩擦產生之高熱^影 火箭的安全性及穩定性。 y ’習用火箭鋼殼之絕熱内襯成形方法係包含手 模壓法及内纏繞法。 製法而言，其首先係在一鋼殼之内壁噴塗含丁 ，再接著利用手工將一絕熱内襯貼在火箭鮮之 加熱使絕熱内概硫化硬化。雖然該手工貼&法 但其施工品質不穩定，鋼殼内壁及絕熱内襯之 脫膠及間隙之缺陷，且絕熱内襯之疊層間容易 因而常影響結合可靠度及結構強度。再者，該 亦不利於對口徑小的鋼殼進行加工，且使用丁 污染環境及不符合環保製程規定的疑慮。 而言’其首先係將黏著劑塗於一鋼殼之内壁， 成型之一絕熱内襯置入該鋼殼内，並利用一内 内襯内施壓，以便使該絕熱内襯能緊密結合於 壁’以利進行加熱硫化之硬化步驟。雖然該模1230222 V. Description of the invention (1) [The invention belongs to the system of the invention, in particular, the liner can be tight. In the fire member and gunpowder, in order to improve the general paste method, the inner wall of the ketone adhesive is manually applied, and it is easy to implement in the end, and air bubbles are easy to be produced. [Technical Field of Insulating the Steel Shell] [Technical Field] A method for forming an adiabatic lining of a rocket steel shell, and a method for forming an adiabatic ^ combined with a steel shell using airbag pressure and vacuum methods, and Its device. ] In the manufacture of the motive, the inner wall of the steel shell of the rocket engine must usually be lined with heat. When the heat-insulating lining is fired by a stack of several heat-resistant rubber layers, the heat-insulating lining is used to avoid the heat and the rocket's safety and stability in the steel shell, which is caused by the friction between the outer wall of the steel shell and the air. The method for forming a heat-resistant lining of a conventional rocket steel shell includes a hand compression method and an inner winding method. In terms of the manufacturing method, it is first sprayed with Ding on the inner wall of a steel shell, and then a thermal insulation lining is manually affixed to the fresh rocket to heat and harden the thermal insulation. Although the manual paste & method, its construction quality is unstable, the debonding and gap defects of the inner wall of the steel shell and the thermal insulation lining, and the stacking of the thermal insulation lining is easy to affect the reliability and structural strength. In addition, this is not conducive to the processing of small-caliber steel shells, and the use of D pollution concerns the environment and does not comply with environmental protection process regulations. In terms of 'it first applies an adhesive to the inner wall of a steel shell, a shaped heat-insulating liner is placed in the steel shell, and pressure is applied using an inner liner so that the heat-insulating liner can be tightly bonded to The wall 'facilitates the hardening step of heat vulcanization. Although the model
C:\LOOO-5\FIVE (XNTINENTS\PK9339.ptd 第11頁C: \ LOOO-5 \ FIVE (XNTINENTS \ PK9339.ptd p. 11
1230222 五、發明說明（2) 壓法之施工品質略優於該手工 殼之内壁的彎弧處及凹陷處 ^法，但該絕熱内襯在鋼 且仍然無法有效移除絕熱内概之j = 隙之缺陷， 熱内襯在預製成型時，可選 且層間的軋泡。雖然該絕 進行堆疊增層，以預先減少為1用較費時之碾輾貼合方式 唯，此舉不但徒增製程複雜度；2 ::湩層間形成氣泡。 熱内襯之彈性變形能力，因 1又’且相對降低該絕 貼合於該鋼殼之内壁的良率。利於該、"邑熱内襯受壓變形 就内纏繞法而言，其係刺田 内襯依序纏繞於該鋼殼之内I内纏繞，具將條狀之絕熱 ^ 2上。雖然該内纏繞法且右產六 佳結合可靠度及結構強度，作 j统法具有較 置費用極高，目而不利c工步驟禝雜，且機具購 1一 加逮製程及降低製造成本。 ,,之，上述習用火箭鋼殼之絕熱 置皆需進一步改善，因此有必二I法及其表 置以克服上述技術缺點。 x 、、、。5方法气裝 述之缺點，其係將-絕熱内襯 士鋼八又内利用一虱袋加壓膨脹該絕熱内襯，並對該 鋼设及絕熱内襯間抽真空，藉此該絕熱内襯不但可緊密結 合於該鋼殼之内壁，且亦可同時抽除該絕熱内襯之疊層間 的氣泡。因此，本發明確實能提升絕熱内襯之結合可靠度 及結構強度’並同時簡化製程、提高良率，並降低有機溶 劑之用量，以減少污染。 【發明内容】 本發明主要目的係提供一種火箭鋼殼之絕熱内襯成形方 C:\LCXJO-5\FIVE OQNTINEm'SVPKiTO.ptd 第12頁 裝置， 襯緊密 數個縱 完全排 具有增 本發明 下列步 内襯套 氣袋及 進行抽 行抽氣 該氣袋 該絕熱 方式】 讓本發1230222 V. Description of the invention (2) The construction quality of the pressing method is slightly better than the bending and depression of the inner wall of the manual shell, but the thermal insulation lining is in steel and still cannot effectively remove the thermal insulation j = Defects in gaps, thermal interlining during pre-forming, optional and interlayer foaming. Although it is necessary to stack and increase the layer, reducing it to 1 in advance and using a more time-consuming rolling and bonding method. However, this will not only increase the complexity of the process, but also form bubbles between the layers. The elastic deformation capacity of the thermal lining is relatively low, and the yield rate of the absolute fit on the inner wall of the steel shell is relatively reduced. Conducive to this, "Yi's thermal lining is deformed under pressure. As far as the inner winding method is concerned, the thorn field lining is sequentially wound inside the steel shell I, and it has a strip-shaped insulation ^ 2. Although the inner winding method and the six best-in-class methods combine reliability and structural strength, the j-system method has extremely high installation costs, is inconvenient for the purpose, and has complicated process steps. Moreover, the equipment purchase process has increased the manufacturing process and reduced manufacturing costs. As a result, the thermal insulation of the conventional rocket steel shells mentioned above need to be further improved, so it is necessary to use the I method and its configuration to overcome the above technical disadvantages. x,,,. The shortcomings of the 5 method air pack are that the heat-insulating lining Shi Gangba is inflated with a lice bag to swell the heat-insulating lining, and evacuate the steel installation and the heat-insulating lining, thereby the heat-insulating lining The liner can not only be tightly bonded to the inner wall of the steel shell, but also can remove the air bubbles between the stacks of the thermal insulation liner at the same time. Therefore, the present invention can indeed improve the combination reliability and structural strength of the thermal insulation lining, and at the same time simplify the manufacturing process, improve the yield, and reduce the amount of organic solvents to reduce pollution. [Summary of the invention] The main purpose of the present invention is to provide a thermal insulation lining forming square C: \ LCXJO-5 \ FIVE OQNTINEm'SVPKiTO.ptd page 12 device for rocket steel shells. Step inner liner air bag and pumping air bag, the air bag and the adiabatic method] Let the hair
時採用 於一鋼 度及簡 提供一 時採用 其係同 的結合 合可靠 目的係 其係同 的結合 孔有利 有增加 目的係 其係同 的結合 向凸條 除該絕 加絕熱 之火箭 驟·將 設於該 内模具 氣形成 形成真 膨脹擴 内襯， 於 鋼 於排除 絕熱内 提供一 時採用 於一鋼 或縱向 熱内襯 内襯結 再將該鋼 該内模具 熱内襯至 合於該鋼 及抽真 ，而使 功效。 殼之絕 及抽真 ，該絕 襯之疊 度之功 殼之絕 及抽真 ，該絕 縱向凸 壁之間 之功效 成形方 具氣孔 組合體 鋼殼内 殼之内 之内部 該鋼殼 殼之内 五、發明說明（3) 法及其裝置 絕熱内襯緊密 升絕熱内襯結 本發明次要 法及其裝置， 絕熱内襯緊密 個透孔，該透 而使本發明具 本發明另一 法及其 絕熱内 面形成 有利於 本發明 根據 其包含 一絕熱 内襯、 之内部 之間進 壓，使 熱硬化 【實施 為了 氣袋加壓 殼之内壁 化製程之 種火箭鋼 氣袋加壓 殼之内壁 該絕熱内 襯結構強 種火箭鋼 氣袋加壓 殼之内壁 凹槽，該 及鋼殼内 合可靠度 鋼殼之絕熱内襯 一氣袋套設於一 氣袋及内模具之 之組合體置入一 真空； 空；在 撐該絕 使其結 空方式，使一 本發明具有提 熱内襯成形方 空方式，使一 熱内概具有數 層間的氣泡， 效。 熱内襯成形方 空方式，使一 熱内襯之外表 條或縱向凹槽 的空氣，而使It can be used at one degree of rigidity and can be used at the same time to provide reliable coupling. The coupling hole of the coupling is advantageous for the purpose of increasing the coupling of the coupling to the convex strip except the adiabatic rocket. When the inner mold gas is formed, a true expansion and expansion lining is formed. When the steel is excluded from the heat insulation, a steel or longitudinal thermal lining lining is used. True, and make the effect. The insulation of the shell, the insulation of the overlap of the insulation lining, the function of the insulation between the longitudinal convex walls, the inner side of the steel shell, and the interior of the steel shell. Inner V. Description of the invention (3) Method and device The heat-insulating lining is tightly raised. The heat-insulating lining is a secondary method of the present invention and the device thereof. The formation of its heat-insulating inner surface is beneficial to the present invention, according to which the inner pressure of the heat-insulating lining is contained, and the heat is hardened. The inner wall groove of the heat-insulating lining structure strong-type rocket steel air bag pressurized shell, the steel shell and the reliability of the steel shell, the heat-insulating inner lining of the steel shell, an air bag sleeved in a combination of an air bag and an inner mold are placed in a Vacuum; empty; in order to support the method to make it empty, so that the present invention has a heating lining forming square hollow method, so that there can be several layers of air bubbles in a heat, effective. The hot lining is formed in a hollow way, so that a hot lining
。 L 法及其裝置’ 内模具上；將 上；將該絕熱 ;將該内模具 壁及絕熱内襯 進行充氣加 之内壁；及加 壁上。 明之上述和其他目的、特徵、和優點能更明. The L method and its device 'are applied to the inner mold; the upper surface; the heat insulation; the inner mold wall and the heat insulation lining are inflated plus the inner wall; and the wall is added. The above and other objectives, features, and advantages will become clearer
C:\L〇〇〇-5\FIVE OONriNENTS\PK9339.ptd 第13頁 1230222 五、發明說明（4) ' — 確被了解’下文將特舉本發明較佳實施例，並配合所附圖 式，作詳細說明如下。 第1圖揭示本發明火箭鋼殼之絕熱内襯成形方法之流程 方塊圖；第2圖揭示本發明火箭鋼殼之絕熱内襯成形裝置 之分解剖視圖；第2Α圖揭示本發明第2圖之局部放大圖； 第3圖揭示本發明火箭鋼殼之絕熱内襯成形裝置之組合剖 視圖’第4圖揭示本發明火箭鋼殼之絕熱内襯成形裝置之 另一組合剖視圖；第5Α圖揭示本發明沿第4圖之5-5線之組 合剖視圖；第5Β圖揭示本發明沿第4圖之5-5線之另一組合 剖視圖；第6圖揭示本發明火箭鋼殼之絕熱内襯成形裝置 在内模具内部進行抽真空之組合剖視圖；第7圖揭示本發 明火箭鋼殼之絕熱内襯成形裝置將氣袋進行加壓並將鋼殼 及絕熱内襯之間進行抽真空之組合剖視圖；第7Α圖揭示本 發明第7圖之局部放大圖；第8圖揭示本發明火箭鋼殼1絕 熱内襯成形裝置使絕熱内襯擴張緊貼於鋼殼之組合剖視 圖；第9 Α圖揭示本發明沿第8圖之9 - 9線之組合剖視圖；第 9 B圖揭示本發明沿第8圖之9 - 9線之另一組合剖視圖；第1 〇 圖揭示本發明火箭鋼殼之絕熱内襯成形裝置將絕熱内襯加 熱硬化後結合於銦殼之組合剖視圖；第11 A圖揭示本發明 沿第1 0圖之1 1 - 11線之組合剖視圖；第11 B圖揭示本發明沿 第1 0圖之11 - 1 1線之另一組合剖視圖；第11 C圖揭示本發明 第10圖之局部放大圖。 請參照第1至3圖所示，本發明火箭鋼殼之絕熱内襯成形 方法之第一步驟係將一氣袋20套設於一具氣孔内模具1〇C: \ L〇〇〇〇-5 \ FIVE OONriNENTS \ PK9339.ptd Page 13 1230222 V. Description of the invention (4) '-It is understood' The following describes the preferred embodiment of the present invention, in conjunction with the accompanying drawings As detailed below. FIG. 1 illustrates a block flow diagram of a method for forming a thermal insulation lining of a rocket steel shell of the present invention; FIG. 2 illustrates a anatomical view of a thermal insulation lining forming device of the rocket steel shell of the present invention; FIG. Enlarged view; FIG. 3 shows a combined sectional view of a thermal insulation lining forming device for a rocket steel shell of the present invention; FIG. 4 shows another combined sectional view of a thermal insulation lining forming device for a rocket steel shell of the present invention; and FIG. Figure 4 is a combined sectional view taken along line 5-5; Figure 5B shows another combined sectional view taken along line 5-5 of Figure 4; Figure 6 shows the thermal insulation lining forming device of the rocket steel shell of the present invention. Combined sectional view of vacuum evacuation inside the mold; FIG. 7 shows a combined sectional view of the thermal insulation lining forming device of the rocket steel shell of the present invention, which pressurizes the air bag and evacuates between the steel shell and the thermal insulation lining; FIG. A partial enlarged view of FIG. 7 of the present invention is disclosed; FIG. 8 shows a sectional view of the combination of the thermal insulation lining forming device of the rocket steel shell 1 of the present invention with the thermal insulation lining expanded and tightly attached to the steel shell; Figure 9-9 is a combined sectional view; Figure 9B shows another combined sectional view of the invention along line 9-9 of Figure 8; Figure 10 shows that the thermal insulation lining forming device of the rocket steel shell of the invention will Composite sectional view of the liner bonded to the indium shell after heating and hardening; Figure 11A shows the combined sectional view of the present invention along line 1 1-11 of Figure 10; Figure 11B shows the invention according to Figure 11-1 of Figure 10 Another combined sectional view of line 1; FIG. 11C reveals a partially enlarged view of FIG. 10 of the present invention. Please refer to Figs. 1 to 3, the first step of the method for forming the heat-insulating lining of the rocket steel shell of the present invention is to set an air bag 20 in a blow hole mold 1.
C:\LOGO-5\FIVE aKTINENTS\PK9339.ptd 第14頁 1230222 五、發明說明（5) 上。該内模具1 0係由金屬製成之圓柱形中空筒體，例如 銘。該内模具1 0之形狀係相似於火箭發動機之一鋼殼4〇之 内壁形狀，但其外徑係小於該鋼殼4〇之内徑。該内模具工〇 設有數個氣孔11、一定位座12、一定位桿13、一蓋板丨^、 至少一第一氣流通道15、至少一第二氣流通道16。該氣孔 11開設在該内模具1 0之外表面上。該定位座丨2形成在該内 模具10之第一端〔封閉端〕。該定位桿13係可滑動的插設 於該定位座1 2内。該蓋板1 4可封閉結合於該内模具丨〇之第 二端〔開放端〕。該第一氣流通道15可對該内模具1〇進行 抽氣或加壓。該第二氣流通道15亦可供氣體進行流通。該 氣袋20係由塑膠材料製成，例如pp聚丙烯塑膠。該氣袋2〇 具有柔軟度、韌性、耐熱性及耐壓性，其厚度較佳為 0·05_，並可耐17(TC之高溫。該氣袋2〇之形狀相似於該 鋼殼40之内壁形狀，但其外徑較佳大於該鋼殼4〇之内 如此該氣袋20具有可膨脹擴張之裕度，並可套設於該^模 具10上。該氣袋20之第一端〔封閉端〕設有一定位唇緣 21。該定位唇緣21之開口可供該定位桿13穿過，及該定位 唇緣2 1可在後續步驟中適當封閉結合於該定位桿丨3之桿頭 上。該氣袋2 0之第二端〔開放端〕則可在後續步驟中適當 封閉結合於該内模具10之蓋板14。 請參照第1、2、2A及3圖所示，本發明火箭鋼殼之絕熱 内襯成形方法之第二步驟係將一絕熱内襯3 〇套設於該氣袋 2 0及内模具1 0之組合體上。該絕熱内襯3 〇之形狀相似於該 鋼殼40之内壁形狀，其外徑係約等於該鋼殼4〇之内徑，及C: \ LOGO-5 \ FIVE aKTINENTS \ PK9339.ptd Page 14 1230222 V. Description of the invention (5). The inner mold 10 is a cylindrical hollow cylinder made of metal, such as an inscription. The shape of the inner mold 10 is similar to the shape of the inner wall of a steel shell 40 of a rocket engine, but its outer diameter is smaller than the inner diameter of the steel shell 40. The inner mold worker is provided with a plurality of air holes 11, a positioning base 12, a positioning rod 13, a cover plate, at least one first airflow channel 15, and at least one second airflow channel 16. The air hole 11 is opened on the outer surface of the inner mold 10. The positioning base 2 is formed at the first end [closed end] of the inner mold 10. The positioning rod 13 is slidably inserted into the positioning base 12. The cover plate 14 can close the second end [open end] bonded to the inner mold. The first air flow path 15 can evacuate or pressurize the inner mold 10. The second air flow channel 15 is also used for gas circulation. The airbag 20 is made of a plastic material, such as pp polypropylene plastic. The airbag 20 has softness, toughness, heat resistance and pressure resistance, and its thickness is preferably 0.05 ° and can withstand high temperatures of 17 ° C. The shape of the airbag 20 is similar to that of the steel case 40 The shape of the inner wall, but its outer diameter is preferably larger than that of the steel shell 40 so that the airbag 20 has a margin for expansion and expansion, and can be sleeved on the mold 10. The first end of the airbag 20 [ The closed end] is provided with a positioning lip 21. The opening of the positioning lip 21 can be passed by the positioning rod 13, and the positioning lip 21 can be appropriately closed and combined with the head of the positioning rod 3 in the subsequent steps. The second end [open end] of the airbag 20 can be appropriately closed in the subsequent steps to cover the cover plate 14 combined with the inner mold 10. Please refer to Figures 1, 2, 2A and 3 for the rocket of the present invention. The second step of the method for forming a heat-insulating lining of a steel shell is to set an insulation lining 30 on the combination of the airbag 20 and the inner mold 10. The shape of the insulation lining 30 is similar to that of the steel. The inner wall of the shell 40 has an outer diameter approximately equal to the inner diameter of the steel shell 40, and
第15頁 1230222 五、發明說明（6) 其内徑稍大於該内模具10之外徑。該絕熱内襯30之第一端 〔封閉端〕具有一頂孔31，及其另一端〔開放端〕形成開 放，以便該絕熱内襯30套設於該氣袋20及内模具10之組合 體上。該絕熱内襯3 0較佳係由具耐熱性之數個橡膠片3 2堆 疊預製成形，且該橡膠片32之堆疊層數及厚度係可依火箭 發動機之鋼殼40規格作適當變化。在該絕熱内襯套設於 該氣袋2 0之前，該絕熱内襯3 〇之外表面較佳預先進行打 孔，以形成數個透孔3 3。在後續步驟中，該透孔3 3可用以 排除各橡膠片32之間所積存的氣泡。本發明較佳係在該絕 熱内襯3 0上每隔1 〇 〇mm利用適當針錐進行穿刺，以形成孔 徑5mm之該透孔33。 請參照第1、3及4圖所示，本發明火箭鋼殼之絕熱内襯 成形方法之第三步驟係將該絕熱内襯3〇、氣袋2〇及内模具 10之組合體置入該鋼殼40内。在組合該絕熱内襯3〇、 2〇及内模具10後，使該定位件13穿過該絕熱内襯3〇之|__^ 31及氣袋20之定位唇緣21的開口，並結合於該内模具1〇之 定位座12内，再利用該定位件13之桿頭封閉該氣袋2〇之定 位唇緣21。接著，將該絕熱内襯30、氣袋2 組合體由該鋼殼4。之-喷嘴口 42〔開放端〕置入；鋼= 内，並利用該定位件13準確的對位結合於該鋼殼4〇之一點 火孔41〔封閉端〕。最後，藉由該蓋板14封閉該氣袋2〇之 第二端〔開放端〕’而使該該絕熱内襯3〇、氣袋2〇及内模 具10之組合體全部密封於該鋼殼40内。 、 請參照第5A及5B圖所示，該絕熱内襯3〇之外周環係可選Page 15 1230222 V. Description of the invention (6) The inner diameter is slightly larger than the outer diameter of the inner mold 10. The first end [closed end] of the thermal insulation lining 30 has a top hole 31 and the other end [open end] forms an opening, so that the thermal insulation lining 30 is set on the combination of the airbag 20 and the inner mold 10 on. The heat-insulating lining 30 is preferably formed by stacking a plurality of heat-resistant rubber sheets 32, and the number of stacked layers and thickness of the rubber sheet 32 can be appropriately changed according to the specifications of the steel shell 40 of the rocket engine. Before the heat-insulating liner is set on the airbag 20, the outer surface of the heat-insulating liner 30 is preferably perforated in advance to form a plurality of through-holes 33. In the subsequent steps, the through holes 33 can be used to eliminate air bubbles accumulated between the rubber pieces 32. In the present invention, it is preferable to puncture the insulating lining 30 with an appropriate needle cone every 100 mm to form the through-holes 33 having a diameter of 5 mm. Please refer to FIGS. 1, 3 and 4. The third step of the method for forming the thermal insulation lining of the rocket steel shell of the present invention is to put the combination of the thermal insulation lining 30, the airbag 20 and the inner mold 10 into the assembly. Inside the steel case 40. After combining the thermal insulation lining 30, 20 and the inner mold 10, the positioning member 13 is passed through the opening of the thermal insulation lining 30 ___ ^ 31 and the positioning lip 21 of the airbag 20, and combined with In the positioning seat 12 of the inner mold 10, the head of the positioning member 13 is used to close the positioning lip 21 of the air bag 20. Next, the heat-insulating liner 30 and the air bag 2 are assembled from the steel shell 4. No.-nozzle port 42 [open end] is placed; steel = inside, and the positioning member 13 is used to accurately align with one of the fire holes 41 [closed end] of the steel shell 40. Finally, the cover 14 closes the second end [open end] 'of the air bag 20, so that the combination of the thermal insulation liner 30, the air bag 20, and the inner mold 10 is completely sealed in the steel shell. Within 40. Please refer to Figures 5A and 5B. The outer ring of the thermal insulation lining 30 is optional.
1230222 五、發明說明（7) · 擇預先貼設數個縱向凸條34，或預先切割數個縱向凹槽 · _ 3 5 ’以利後續抽真空時能完全促進排除該絕熱内襯3 〇及鋼 . 殼4 0之内壁之間的空氣。該縱向凸條34之材質與該絕熱内 概30相同’其寬度較佳為5mifl，及厚度較佳為2min。該縱向 凹槽35之深度較佳約2min。該縱向凸條34及縱向凹槽35之 、 作用原理將於下列相關步驟進一步詳細說明。 請參照第1及6圖所示，本發明火箭鋼殼之絕熱内襯成形 — 方法之第四步驟係將該内模具丨〇之内部進行抽氣形成真 空。在§亥絕熱内襯3 〇、氣袋2 〇及内模具1 〇之組合體初步置 入該鋼殼40内之後，若直接進行下列第五步驟之抽真空動 鲁 作’則容易造成靠近該鋼殼4 〇之第二端〔開放端〕的絕熱 内概3 0及氣袋20過早膨脹擴張，而影響排除靠近該鋼殼4〇 之第二端〔開放端〕的内部空氣。因此，本發明較佳傳先 利用一空氣幫浦〔未繪示〕經由該第一氣流通道15對 具10抽氣’以形成5 t〇r Γ之真空，如此可藉由該氣孔丨丨的 吸1吸住該氣袋20，以確保該絕熱内襯3〇及氣袋2〇貼於該 内模具1 0之外表面，以克服上述技術問題。 、明參照第1、7及7 A圖所示，本發明火箭鋼殼之絕熱内襯 成形方法之第五步驟係再將該鋼殼4〇之内壁及絕熱内襯3〇 之間進行抽氣形成真空。在保持該内模具丨〇的真空狀態 馨 下，接著利用該空氣幫浦經由該第二氣流通道1 6，而對該· 鋼殼40之内壁及絕熱内襯3〇之間抽氣，以形成等於〔或稍· 小於〕5t〇rr之真空，以便與該内模具1〇的真空狀態形成 平衡。該真空平衡狀態較佳保持2〇分鐘。藉此，如第了八圖1230222 V. Description of the invention (7) · Choose to lay several longitudinal ridges 34 in advance, or cut several longitudinal grooves in advance · _ 3 5 'to facilitate the exhaustion of the thermal insulation lining completely in the subsequent vacuum 3 〇 and Steel. Air between the inner walls of the shell 40. The material of the longitudinal ridges 34 is the same as that of the heat-insulating interior 30. Its width is preferably 5 mifl, and its thickness is preferably 2 min. The depth of the longitudinal groove 35 is preferably about 2 minutes. The working principle of the longitudinal ridges 34 and the longitudinal grooves 35 will be further explained in the following related steps. Please refer to Figs. 1 and 6, the fourth step of the method for forming the thermal insulation lining of the rocket steel shell of the present invention is to evacuate the inside of the inner mold to form a vacuum. After the combination of § 30 adiabatic inner lining 30, air bag 20 and inner mold 10 is initially placed in the steel shell 40, if the vacuum operation of the fifth step is performed directly, it is easy to cause it to be close to the The adiabatic internal profile 30 of the second end [open end] of the steel shell 40 and the airbag 20 expand and expand prematurely, which affects the exclusion of the internal air near the second end [open end] of the steel shell 40. Therefore, the present invention preferably uses an air pump [not shown] to evacuate 10 pairs of 10 'through the first air flow channel 15 to form a vacuum of 5 t0r Γ, so that the air holes can be passed through the air holes. Suction 1 sucks the airbag 20 to ensure that the heat-insulating liner 30 and airbag 20 are attached to the outer surface of the inner mold 10 to overcome the above technical problems. As shown in Figures 1, 7, and 7A, the fifth step of the method for forming the thermal insulation lining of the rocket steel shell of the present invention is to extract air between the inner wall of the steel shell 40 and the thermal insulation lining 30. A vacuum is formed. While maintaining the vacuum state of the inner mold, the air pump is then used to evacuate between the inner wall of the steel shell 40 and the heat-insulating lining 30 through the second air flow channel 16 to form A vacuum equal to [or slightly less than] 5 to 0rr so as to be in equilibrium with the vacuum state of the inner mold 1O. This vacuum equilibrium state is preferably maintained for 20 minutes. With this, as shown in Figure 8
第17頁Page 17
五、發明說明（8) 所示，在該氣袋20及絕熱内襯30膨脹擴張前，該絕熱内襯 30可先利用該透孔33排除各橡膠片32之間的層間氣泡以 便使該絕熱内襯30的結構變得緊密結實，而提升結構強 度。 請參照第1、8、9A及9B圖所示，本發明火箭鋼殼之絕埶 内襯成形方法之第六步驟係在該内模具1〇之内部進行充•氣 加壓，使該氣袋20膨脹抵撐該絕熱内襯3〇至該鋼殼4〇之内 壁。在保持該鋼殼40及絕熱内襯3〇之間的真空下，經由兮 第-氣流通道15釋放該内模具10之真空，並接著對該内以 具10充氣加壓至3kg/cm2。藉此，由於該氣孔n提供 氣 體’因此該氣袋20開始徑向膨脹擴張，進而向外抵 孔 熱内襯30，使該絕熱内襯30緊密貼附於該鋼殼“之内、。 H ίΛΑ &9B ® ~ ^胃絕熱内_可利用該縱向凸 條34,兩側或縱向凹槽35本身做為臨時性氣流通道，^ 该鋼设4◦及絕熱内襯30之間任一位置的空氣，皆 經由該臨時性的氣流通道加以㈣，以便 二件，並避免兩者之間存在任何間隙，進而確保結 再者，如第8圖所示，本發明之定位桿13亦可 抽真空功能，並使該定位桿13額外結合一空 ' 擇，、備 示〕，如此本發明亦可同時由該鋼殼4〇之第一 / ^繪 端〕進行抽真空動作。 、于閉 請參照第1、8、10、11A、l1B及11C圖所示，本發明 箭鋼殼之絕熱内襯成形方法之第七步驟係力口熱硬化該絕熱5. The invention description (8) shows that before the airbag 20 and the thermal insulation lining 30 expand and expand, the thermal insulation lining 30 can first use the through-holes 33 to eliminate interlayer air bubbles between the rubber sheets 32 in order to make the thermal insulation. The structure of the lining 30 becomes tight and strong, and the structural strength is improved. Please refer to Figs. 1, 8, 9A, and 9B. The sixth step of the method for forming the insulating lining of the rocket steel shell of the present invention is to fill and pressurize the inside of the inner mold 10 to make the air bag. 20 expands against the inner wall of the thermal insulation lining 30 to the steel shell 40. While maintaining the vacuum between the steel shell 40 and the heat-insulating lining 30, the vacuum of the inner mold 10 is released through the first-air flow passage 15, and then the inner mold 10 is pressurized to 3 kg / cm2. As a result, because the air holes n provide gas, the air bag 20 begins to expand and expand radially, and then outwardly contacts the hole thermal lining 30, so that the thermal insulation lining 30 is closely attached to the steel shell "." H ίΛΑ & 9B ® ~ ^ Stomach insulation _ You can use the longitudinal ridges 34, both sides or the longitudinal grooves 35 themselves as temporary airflow channels, ^ The steel is set at any position between 4◦ and the insulation lining 30 The air is simmered through the temporary airflow channel, so that there are two pieces, and there is no gap between the two, so as to ensure knotting. As shown in FIG. 8, the positioning rod 13 of the present invention can also be pumped. Vacuum function, and the positioning rod 13 is additionally combined with an empty option, so that the present invention can simultaneously perform a vacuum pumping action from the first / ^ drawing end of the steel shell 40. For the closed, please refer to As shown in Figures 1, 8, 10, 11A, 11B, and 11C, the seventh step of the method for forming the heat-insulating lining of the arrow steel shell of the present invention is to heat harden the heat-insulation.
第18頁 1230222 五、發明說明（9) 内襯，使其結合於該鋼殼40之内壁上。在保持該鋼殼4〇 及絕熱内襯30之間的真空一段時間之後，該絕熱内襯3〇之 财熱橡膠材質因真空而彈性變形填滿該縱向凸條34兩側或 縱向凹槽35本身所形成之間縫，同時該絕熱内襯30之各橡 膠片3 2間亦幾乎不存在任何氣泡〔如第丨丨c圖所示〕。此 時’利用130 °C的高溫對該絕熱内襯30加熱12小時，使該 絕熱=襯30之耐熱橡膠材質硫化，而永久性的硬化成形^ 並緊密的膠黏結合於該鋼殼4〇之内壁上。最後，移除該内 模具10及氣袋20，本發明即可製得該鋼殼4〇及絕熱内^3〇 之結合半成品，以供後續組裝形成完整的火箭發動機。 如上所述，相較於習用火箭鋼殼之絕熱内襯成形方法不 易控制施工品質、容易產生間隙、氣泡或脫膠，而影響結 合可靠度及結構強度等缺點，第丨圖之本發明藉由氣袋 壓及抽真空方式，其確實可使該絕熱内襯30緊密的結 該鋼殼40之内壁，以提升絕熱内襯30之結合可靠度及結 強度，並同時簡化製程及提高良率。 、°Page 18 1230222 V. Description of the invention (9) The inner lining is bonded to the inner wall of the steel shell 40. After maintaining the vacuum between the steel shell 40 and the thermal insulation lining 30 for a period of time, the thermal insulation rubber material of the thermal insulation lining 30 elastically deforms due to the vacuum to fill both sides of the longitudinal ridge 34 or the longitudinal groove 35 The gap formed by itself, and at the same time, there is almost no air bubble between the rubber sheets 32 of the heat-insulating lining 30 [as shown in FIG. 丨 丨 c]. At this time, the heat-insulating lining 30 is heated at a temperature of 130 ° C for 12 hours, so that the heat-insulating = heat-resistant rubber material of the lining 30 is vulcanized, and is permanently hardened ^ and tightly bonded to the steel shell 4. Inside the wall. Finally, the inner mold 10 and the air bag 20 are removed, and the present invention can obtain a combined semi-finished product of the steel shell 40 and the thermal insulation inner 30, for subsequent assembly to form a complete rocket engine. As described above, compared with the conventional method of forming a thermal insulation lining for a conventional rocket steel shell, it is not easy to control the construction quality, it is easy to produce gaps, bubbles, or degumming, which affects the shortcomings such as reliability and structural strength. The invention shown in FIG. The bag pressing and vacuuming methods can indeed make the thermal insulation lining 30 tightly bond the inner wall of the steel shell 40 to improve the bonding reliability and junction strength of the thermal insulation lining 30, and at the same time simplify the manufacturing process and increase the yield. , °
雖然本發明已利用前述較佳實施例詳細揭示，然其並 用以限定本發明，任何熟習此技藝者，在不脫離本^明之 精神和範圍内，當可作各種之更動與修改，因此本發明 保護範圍當視後附之申請專利範圍所界定者為準。Although the present invention has been disclosed in detail using the foregoing preferred embodiments, it is also used to limit the present invention. Any person skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. The scope of protection shall be determined by the scope of the attached patent application.
1230222 _ ---------—-- ----- 圖式簡單制 --- 【圖式簡單說明】 第1圖：本發明火箭鋼毅之絕熱内概成形方法之流程方 塊圖。 第2圖：本發明火箭鋼殼之絕熱内襯成形裝置之分解剖 視圖。 第2A圖：本發明第2圖之局部放大圖。 第3圖：本發明火箭鋼殼之絕熱内襯成形裝置之組合剖 視圖。 第4圖：本發明火箭鋼殼之絕熱内襯成形裝置之另一組 合剖視圖。 第5 A圖：本發明沿第4圖之5 - 5線之組合剖視圖。 第5B圖：本發明沿第4圖之5-5線之另一組合剖視圖。 第6圖：本發明火箭鋼殼之絕熱内襯成形裝置在内模具 内部進^亍抽真空之組合剖視圖。 第7圖：本發明火箭鋼殼之絕熱内襯成形裝置將氣 行加壓並將鋼殼及絕熱内襯之間進行抽真空之組合剖視 圖。 第7A圖：本發明第7圖之局部放大圖。 第8圖：本發明火箭鋼殼之絕熱内襯成形裝置使絕熱内 襯擴張緊貼於鋼殼之組合剖視圖。 第9 A圖：本發明沿第8圖之9 - 9線之組合剖視圖。 第9 B圖：本發明沿第8圖之9〜9線之另一組合剖視圖。 第1 0圖：本發明火箭鋼殼之絕熱内襯成形裝置將絕熱内 概加熱硬化後結合於鋼殼之組合剖視圖。1230222 _ ------------ ----- Simple drawing system --- [Simplified illustration of the drawing] Figure 1: Block diagram of the process of the adiabatic inner forming method of the rocket steel of the present invention . Fig. 2: An exploded view of a thermal insulation lining forming device for a rocket steel shell of the present invention. Fig. 2A is a partially enlarged view of Fig. 2 of the present invention. Fig. 3 is a sectional view of the heat-insulating lining forming device of the rocket steel shell of the present invention. Fig. 4 is a sectional view of another group of the heat-insulating lining forming device for the rocket steel shell of the present invention. Figure 5A: A sectional view of the present invention taken along line 5-5 of Figure 4. Fig. 5B: Another combined sectional view of the present invention taken along line 5-5 of Fig. 4. Fig. 6: A combined sectional view of a vacuum lining forming device for a thermal insulation lining forming device of a rocket steel shell according to the present invention. Fig. 7: The sectional view of the thermal insulation lining forming device of the rocket steel shell of the present invention pressurizes air and evacuates the steel shell and the thermal insulation lining. Fig. 7A: A partially enlarged view of Fig. 7 of the present invention. Fig. 8: The sectional view of the thermal insulation lining forming device for the rocket steel shell of the present invention, which expands the thermal insulation lining to closely adhere to the steel shell. Figure 9A: A sectional view of the present invention taken along line 9-9 of Figure 8. Figure 9B: Another combined sectional view of the present invention along line 9-9 of Figure 8. Fig. 10: The sectional view of the thermal insulation lining forming device of the rocket steel shell of the present invention, which is combined with the steel shell after heating and hardening.
C：\UX».5\FIVE aMINENTS\PK9339.pid 第20頁 1230222__ 圖式簡單說明 第11A圖：本發明沿第1 0圖之11 - 11線之組合剖視圖。 第11B圖：本發明沿第10圖之11-11線之另一組合剖視 圖。 第11C圖：本發明第10圖之局部放大圖。 圖號說明：C: \ UX ».5 \ FIVE aMINENTS \ PK9339.pid Page 20 1230222__ Brief description of the drawings Figure 11A: The present invention is a sectional view taken along line 11-11 of Figure 10. Fig. 11B: Another sectional view of the present invention taken along line 11-11 of Fig. 10; Fig. 11C: A partially enlarged view of Fig. 10 of the present invention. Figure number description:
10 内 模 具 11 氣 孔 12 定 位 座 13 定 位 桿 14 蓋 板 15 第 一 氣 流通道 16 第 二 氣 流通 道20 氣 袋 21 定 位 唇 緣 30 絕 熱 内 襯 31 頂 孔 32 橡 膠 片 33 透 孔 34 縱 向凸條 35 縱 向 凹 槽 40 鋼 殼 41 點 火孔 42 喷 嘴 D10 Inner mold 11 Air hole 12 Positioning seat 13 Positioning rod 14 Cover plate 15 First air flow channel 16 Second air flow channel 20 Air bag 21 Positioning lip 30 Insulation lining 31 Top hole 32 Rubber sheet 33 Through hole 34 Vertical protrusion 35 Vertical Groove 40 Steel case 41 Ignition hole 42 Nozzle D
C:\UOOO-5\FIVE OCKTINENTS\PK9339.ptd 第21頁C: \ UOOO-5 \ FIVE OCKTINENTS \ PK9339.ptd Page 21
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TW92132808A TWI230222B (en) | 2003-11-21 | 2003-11-21 | Insulator forming method and device thereof for a rocket motor casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TW92132808A TWI230222B (en) | 2003-11-21 | 2003-11-21 | Insulator forming method and device thereof for a rocket motor casing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| TWI230222B true TWI230222B (en) | 2005-04-01 |
| TW200517582A TW200517582A (en) | 2005-06-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| TW92132808A TWI230222B (en) | 2003-11-21 | 2003-11-21 | Insulator forming method and device thereof for a rocket motor casing |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104848002A (en) * | 2015-05-15 | 2015-08-19 | 湖北三江航天江河化工科技有限公司 | Control method for heat-insulating layer structural uniformity |
| CN104875470A (en) * | 2015-05-15 | 2015-09-02 | 湖北三江航天江河化工科技有限公司 | Air distribution system for manufacturing engine heat insulation layer and control method of air distribution system |
| TWI511860B (en) * | 2012-12-10 | 2015-12-11 | Nat Inst Chung Shan Science & Technology | Method for forming shell liner and device |
| CN104552692B (en) * | 2013-10-28 | 2017-06-13 | 湖北航天化学技术研究所 | A kind of middle-size and small-size solid propellant rocket internal insulation bulge forming frock |
-
2003
- 2003-11-21 TW TW92132808A patent/TWI230222B/en not_active IP Right Cessation
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI511860B (en) * | 2012-12-10 | 2015-12-11 | Nat Inst Chung Shan Science & Technology | Method for forming shell liner and device |
| CN104552692B (en) * | 2013-10-28 | 2017-06-13 | 湖北航天化学技术研究所 | A kind of middle-size and small-size solid propellant rocket internal insulation bulge forming frock |
| CN104848002A (en) * | 2015-05-15 | 2015-08-19 | 湖北三江航天江河化工科技有限公司 | Control method for heat-insulating layer structural uniformity |
| CN104875470A (en) * | 2015-05-15 | 2015-09-02 | 湖北三江航天江河化工科技有限公司 | Air distribution system for manufacturing engine heat insulation layer and control method of air distribution system |
| CN104848002B (en) * | 2015-05-15 | 2017-03-01 | 湖北三江航天江河化工科技有限公司 | A kind of control method of insulating structure uniformity |
Also Published As
| Publication number | Publication date |
|---|---|
| TW200517582A (en) | 2005-06-01 |
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