1299017 九、發明說明： 【發明所屬之技術領域】 本發明係關於一種複合材料管件之製造方法 種纏帶式錐形複合材料管件之模壓製造方法。 曰 【先前技術】 複合材料由兩種以上的材料所組成，其主要強度來自於 =材:例如礙纖維與石夕纖維等，這些加強材由例如環氧樹脂或 酚轉脂等基材結合成為-整體。複合材料係一種可設材 料，視不同的應用，可搭配使用不同的加強材和基材如， 以碳纖維作為加搭配魏樹脂做朗複合㈣ 性能，被大量應用於航空、交通工業與運動器材；玻璃 配f賴脂的複合材料隔熱性好，是優良的^ =斷熱或魏或喊兼具雜能，其巾搭配祕細旨j 可耐受2G()(rc高溫的碳齡職布之複合·， 显 之機械及耐燒性能，已成為此技術領域之域洲/;、= 或燒姓時間較短的情況，則多使用祕樹脂基材搭配^ ，維或雜狀複合觀。前輯維強輯脂複& 維型態’常用的有短纖模造^ 7般而言，當複合材料構件的結構強度要求不高且/或主 ^功能為隔熱而不直接受燃氣沖刷，或燃燒時間不長 考^使驗纖模造材料，以熱壓模和熱壓機加熱加 程单純，可製造複雜的形狀，合格率高，且人 j 11構強，求較高，或燒贿件嚴苛時， 滿足而求，此時必須使用連續纖維的製程，因為纖 方式與纖，排列方向是辟結構性能和燒^性J *素:纖維連續越長、排列越規則，材料财燒餘 妗1299017 IX. Description of the Invention: [Technical Field] The present invention relates to a method of manufacturing a composite pipe member, and a method for manufacturing a tape-type tapered composite pipe member.曰[Prior Art] The composite material consists of two or more materials, the main strength of which is derived from = material: for example, fiber and stone fiber, etc., these reinforcing materials are combined by a substrate such as epoxy resin or phenol transesterification. -overall. The composite material is a configurable material. Depending on the application, it can be used with different reinforcing materials and substrates. For example, carbon fiber is used as a blending with Wei resin to make a composite (IV) performance. It is widely used in aviation, transportation industry and sports equipment; Glass with f lyophilic composite material has good heat insulation, it is excellent ^ = heat or Wei or shouting with mixed energy, its towel with secret details can be tolerated 2G () (rc high temperature carbon age cloth The composite, the mechanical and fire-resistant properties have become the domain of this technology field;;, or the burning time is shorter, the use of the secret resin substrate with ^, dimensional or heterogeneous composite view. The former series of Weiqiang series of fat complex & dimension type 'commonly used short fiber mold manufacturing ^ 7 general, when the structural strength of composite members is not high and / or the main function is insulated and not directly affected by gas Scouring, or burning time is not long test ^ to make fiber-optic molding materials, hot stamping and hot press heating plus simple, can create complex shapes, high pass rate, and strong, better, or bribe When the parts are severe, they are satisfied, and the process of continuous fiber must be used at this time. Mode fiber and the fiber arrangement direction is the provision of structural and burn ^ J * Su: continuous fibers longer, more regular arrangement, Choi burning material than Nya
構強度愈好，但製作困難度也隨之提高。典型的長纖維錐形J 1299017 件，如美國 NASA 文獻 PD-ED-1218「APPlication ofAblative Composites to Nozzles for Reusable Sol id Rocket Motors 所述之火箭發動機喷嘴擴張段複合材料絕熱構件，為使纖維排 列符合特定肢需求，係以纏帶法製造，步驟是使用纏帶機， 將裁成帶狀的纖維織布強化高分子樹脂預浸材料，以盘軸心平 行(稱為平行纏帶法）或夾一角度(稱為傾斜纏帶法）的方式，纏 ，於模心相。傾_帶法需細45。職職材料編織帶， 成本較南，因此在絕熱件之設計纖維角度可以接受的情況下， 使用平行纏帶法較為經濟4論平行纏帶法或傾斜纏帶法 維排列方向與軸心的夾角都不大（一般不超過45。），以模壓 =易建立成麵力’因此讀使賴力錢液驗，利用流 ，立側向壓力’其必須按真空餘序，將離賴、吸膠綿及直 二裒包裝前述纏帶胚料及模心（陽模法），置於壓力釜内，抽& =並加?加溫趣，料翁模顧㈣複，整麵帶壓力g 如第―圖流程所示。此外’纏帶胚料崎模法成型的成品 易產生皺摺，而經常造成膠質集中、裂縫等瑕疵。皺摺的 $與成品厚度以及尺寸有關’成品曲率半録小，皺摺便會 。皺舰重到-定減’便造成局部低密度而可能發^ ^問題。影響皺概重程度的因素好 繞參數和壓力魏奴溫賴力條料，且^=^相3 聯’所以皺摺嚴重程度與發生的位置有相當峨 = 〇 AIAA-89 2418 ^ Development and Certification of The Space Shuttle Redesigned Solid Rocket Motor Nozzle」亦指出，平扞缠册 ΐΐΐ原料品質甚為敏感。此外，触還會造成局部缺料，I 避免產品缺料，必須增加胚料厚度，以預留足夠的加工量，這 影ΐ品?與合格率’造I惡性循環，而且浪費材料’ ^長車丨彡叫’增加製造成本。解決皺姻題的方法之 tiff，胚料取出，另置於陰模中成型。但由於將材料 择開為要相㊂大的壓力，-般壓力爸所能提供的細_5〇〇 _ ⑧ 1299017 崎壓爸，提供ι〇〇〇_以上的壓力，而且， ‘pi及ΐί^ί布具備足夠的延紐。但是，使用液壓 釜陰核及斜接f專將大幅增加製作成本。 之最華民國第201585號專利所揭示之「具斜角 件之魏錄」係-歡模餘製造長纖 r大m μ ’可將纖、轉贼_向錄大角度 歐J甘^’、而適合以模壓成型，提供超過2000psi的成型 列ϋΐ之/成品不會發生嚴錄摺，且甚少發生膠質集 件了 該方法不適合製造例如喷嘴擴張段的錐形 模壓方Si ^向_小於45°'時’仍不適合以 造出壓法來成型纏帶胚料，將能以最低成本製 最大==2▼錐形複合材料管件。以模壓法成型纏帶胚料 在於加壓方向與纖維剩方向的夾角太小，這種加 ‘，維排料建立成型壓力。尤其是平行纏帶的情 構方向平行’必須設計複雜賴壓力產生機 ί ί 經詳細分析研究錐形管件_何形狀之 Ϊ罐料的斜度’把軸向施力轉換成側向壓 力G、％、，廛π胚料，再配合適當的溫度控制 σ 的纏帶式錐形管件。 便犯展4冋〇口貝 【發明内容】 之穿之』nr严供一種纏帶式錐形複合材料管件 之氣每方法，其無須使用壓力釜或液壓釜 下吸勝綿、離形膜等真空袋包裝耗材。又備且了名 依據本發明之方法製造纏帶式錐形複合材料管 -般熱壓模細’❿無須設計複_繼力產生機 依據本發明之方法製造纏帶式錐形複合材料° 面不會有皺摺，且纖維排列整齊，符合設計要求。σ 依據本發明之方法製造_式刺彡複合娜 材料浪費域少加工量。 冊目件’可㈣ 7 φ 1299017 為達以上目的，本發明提供之纏帶式錐形複合材料管 製造方法包括以下步驟： 首先，將已裁成-定寬度的帶狀材料纏繞於一錐 h形成-錐形管狀胚料；其次，視需要 胚 後多餘的部分，褪出模心得到—纏帶胚料；然後 置於一特別設計的熱壓模中，以一般模 = 熱加壓成型。其巾，雜顧之設計錢得：斤口接加 ⑴成型加壓時，纏帶胚料斜面比上下端面 立側向壓力後熱壓模才合模； 、田按觸建 (2)ii後’胚料各點有賴的驗量使成品各部翻要求的 【實施方式】 掇壓2::!例1 兒明本發明所述之纏帶式錐形複合材料管件 樹脂預浸布，財，韻維_咖 :度12G±5C下塗佈_樹脂溶液於 = 維场樹脂預浸布，樹脂含量約35-概。1 纖 用分條機將該碳纖維/酚樹 。面線”、員不纖維的排列方向，本例為平; 除線3、4切除前、後多餘的材料ί6 = 出权心後得到如第三圖的纏帶胚料7。 冊b 6，祕 如第三圖所示，將纏帶胚料 再把熱壓模8的上模1G與 :、中， 示出定位銷、頂*板、·继Π: U表達，本圖未 頁出軌、頂夾板、底夾板及其它敎壓 8 1299017 ===齡統。第三_示加壓前， ^nVwi :便面12與上模10之間各留有一餘隙⑴u 向壓縮本移側 與胚料7内面之間具有—致的形狀，如此备 動時’便會使胚料各部有足夠的壓縮量，The better the structural strength, but the difficulty in making it increases. A typical long-fiber tapered J 1299017 piece, such as the rocket engine nozzle expansion section composite insulation member described in the NASA document PD-ED-1218 "APPlication of Ablative Composites to Nozzles for Reusable Sol id Rocket Motors", in order to make the fiber arrangement conform to a specific The limbs are manufactured by the tape wrapping method. The step is to use a tape wrapping machine to cut the fiber-woven fabric into a ribbon-like reinforced polymer prepreg, parallel to the disk axis (called parallel tape winding method) or clip one. The angle (called the slanting tape method) is wrapped in the mold core phase. The tilting tape method needs to be fine 45. The woven tape of the professional material is relatively cost-effective, so in the case where the design fiber angle of the heat insulating member is acceptable. Using the parallel tape method is more economical. The parallel wrapping tape method or the oblique tape wrapping method has a small angle between the alignment direction and the axis (generally no more than 45.), and the molding pressure = easy to establish the surface force 'so read Lai Li Qian liquid test, using the flow, standing lateral pressure 'it must be in accordance with the vacuum residual sequence, the separation of the rag, the absorbent cotton and the straight two 裒 packaging of the aforementioned entangled billet and the core (positive mold method), placed in the autoclave Inside, pump & a Mp; = and add? Add interest, material Weng Gu (four) complex, the entire surface with pressure g as shown in the figure - process. In addition, 'wrapped with the raw material stripe molding method is easy to produce wrinkles, and often caused Concentration of colloids, cracks, etc. The wrinkle is related to the thickness and size of the finished product. 'The curvature of the finished product is half-recorded, and the wrinkles will be fixed. The wrinkle ship will be heavy-decrease--caused to cause local low density and may cause problems. The factors of the degree of wrinkling are better than the parameters and the pressure Weinuwen Lai Li strip, and ^=^ phase 3 joint 'so the wrinkle severity and the location of the occurrence are quite 峨 = 〇AIAA-89 2418 ^ Development and Certification of The Space Shuttle Redesigned Solid Rocket Motor Nozzle also pointed out that the quality of raw materials is very sensitive. In addition, the touch will also cause partial shortage of material. I avoid material shortage, and must increase the thickness of the blank to reserve sufficient processing volume. This affects the quality of the product and the yield rate, and the material is wasted. The car screams 'increased manufacturing costs. The tiff of the method for solving the wrinkle problem is taken out, and the blank is taken out and formed in a negative mold. However, due to the choice of materials to be the three major pressures, the pressure of the father can provide the fine _5 〇〇 _ 8 1299017 Saki pressure dad, provide pressure above ι〇〇〇_, and, 'pi and ΐί ^ ί布 has enough extensions. However, the use of hydraulic cylinders and slanting f will greatly increase production costs. The "Wei Lu with Beveled Parts" disclosed in the Republic of China No. 201585 patent - Huan Mou Yu manufactures long fiber r large m μ 'can be used to turn the fiber into a large angle. However, it is suitable for molding, and the finished product of more than 2000 psi is not strictly recorded, and the gel assembly is rarely produced. The method is not suitable for manufacturing the tapered molding of the nozzle expansion section. ° 'When' is still not suitable for forming the entangled billet by the pressing method, and the maximum == 2 ▼ tapered composite pipe fitting can be produced at the lowest cost. Molding of the entangled blank by the molding method is that the angle between the pressing direction and the remaining direction of the fiber is too small, and this addition ‘, the dimensional discharge establishes the forming pressure. In particular, the parallel direction of the parallel wrapping belts must be designed to be complicated by the pressure generating machine. The detailed analysis of the tapered pipe fittings _ the shape of the slope of the tank material is used to convert the axial force into the lateral pressure G, %,, 廛 π blank, combined with appropriate temperature control σ entangled tapered pipe fittings.犯 展 冋〇 【 【 【 【 【 【 【 【 【 【 【 【 【 【 【 【 【 n n n n n n n n n n n n n n n n n n n n n n n n n n n n n n n n Vacuum bag packaging supplies. Also known and known in accordance with the method of the present invention for producing a tape-type tapered composite tube-like hot-pressing mold fine '❿ no need to design complex_ a secondary force generator to manufacture a tape-type tapered composite material according to the method of the present invention There are no wrinkles, and the fibers are arranged neatly to meet the design requirements. σ Manufacture of the 彡-type 彡 彡 composite material according to the method of the present invention. The title item can be (4) 7 φ 1299017. For the above purposes, the method for manufacturing a tape-wound tapered composite pipe provided by the present invention comprises the following steps: First, a tape-shaped material having a cut-width is wound around a cone h Forming a conical tubular blank; secondly, depending on the excess portion of the post-embryo, the core is removed to obtain a wrap-around blank; then placed in a specially designed hot stamping mold, which is formed by a general mold = hot press. The towel, the design of the miscellaneous design: the mouth is added (1) when the molding pressure is applied, the slanting surface of the skeining material is more than the vertical pressure of the upper and lower end faces, and then the hot pressing mold is closed; the field is pressed to build (2) ii 'Embodiment of the various points of the blanks to make the finished parts turn over. [Embodiment] Pressing 2::! Example 1 The wrapped tape-type tapered composite pipe fitting resin prepreg according to the present invention, wealth, rhyme _ _ 咖: Degree 12G ± 5C under coating _ resin solution in = Victorian field resin prepreg, resin content of about 35 -. 1 Fiber This carbon fiber/phenol tree is used with a slitter. The upper thread", the direction in which the fibers are not arranged, is flat in this example; the excess material before and after the removal of the lines 3 and 4 ί6 = the entangled blank as in the third figure is obtained after the weight is obtained. As shown in the third figure, the upper die 1G of the hot stamping die 8 and the middle and the middle of the hot stamping die 8 are shown as positioning pins, top plate, and Π: U expression, this figure is not derailed, Top splint, bottom splint and other rolling 8 1299017 === age system. Third_ before pressurization, ^nVwi: there is a clearance between the face 12 and the upper die 10 (1) u to compress the shift side and the embryo The inner surface of the material 7 has a uniform shape, so when it is prepared, it will have sufficient compression for each part of the billet.
到均溫’同時讓樹脂軟化，然後用2 ^把上核10在下壓，使熱壓模8合模。合模過程中 月:已經軟化’胚料7斜面部位在成型壓 中向伸十 ，丄而，開始流動，在此同時，上模1〇進:步=向： ί: 7已將餘隙13、14填滿。第四圖顯示合T莫後， 前ί槿1G及下模9的相對位置，圖巾麟16代表加壓 丄ΐ 1 由圖可知，胚料7的侧向受相當大的壓縮， 建ί無虞。此外，胚料7係被從内往外壓縮，類似於 j r成」此不會有皺現象發生。合織，開始升溫至 ί _定成型壓力約，在此—成型壓力與溫度 一卜=持2小時使樹脂固化。冷卻至室_，利用頂出銷(未 Γ出〕從頂出銷孔15 頁出即得成品。整個纏帶-模壓的程序如 弟五圖所示，與第一圖的纏帶壓力釜程序比較，可知本發明之 方法簡易許多。 以上程序所製造之纏帶式錐形複合材料管件，外觀平滑無 4何敵摺無須車修即可進行檢驗，且纖維排列相當整齊。以 ^光檢驗，有80%完全沒有瑕疵，而同樣是使用纏帶法，但以 壓=釜成型者，則只有約30%沒有瑕疵。本具體實施例所製造 成°口之實測密度在1· 45到1· 5 g/cm3之間，而壓力爸成型者只 f 1· 40到1· 42 g/cm3。燒蝕試驗結果顯示，壓力釜成型之成 ΰ口，其上皺摺處的燒蝕率明顯較大。圖六顯示燒蝕試驗之溫度 1299017 bh^員示屢力蒼成品皺摺處（曲線17)的傳數導速率 :ί位置(曲線18、19)，本具所製ί 熱並繼，因此沒有局部_過大與 且於外之方法與伽，必織_是，雖然前述 例係使用韻維场樹脂預浸布，但亦可包括其它適 二、材料’ ？、_料概夠誠餘且適合其所欲達成的性 =可。此外，前述雖以專用纏帶機製作纏帶胚料，但亦可使 式纏繞’或以具備自動旋轉夹頭的機器作為辅助工 本發明所謂錐形管件並不限於直斜雜 可適用於曲面斜錐，或具有兩段以上斜度的斜錐，也可以具 2層材料’這些情況下’為避免成品各部密度相差過大，^ ^壓模上模及/或下模的外形設計成並非與纏帶胚料之内面及 /或外面輪廓一致，而是設計成使纏帶胚料在壓縮後，豆 U近的壓縮量。最後，_本频實施_平行製;^ 、屢▼胚料，但並不排除使用傾斜纏帶的可能性。 以上所述者，僅為本創作較佳之實施例而已，並非用以限 定本創作實施之翻’熟f此麟者經本之獅後，在不 ，離本創作之技術思想範圍下所作之均等變化與修飾，皆應涵 蓋於本創作之申請專利範圍内。 【圖式簡單說明】 ，一圖顯示先前技術之纏帶壓力爸製程之主要步驟的流程圖； 第二圖顯示本發明之一具體實施例之纏帶模心與纏帶完成時 之，面示意圖，為清楚顯示，模心未加剖面線； 第三圖顯示本發明之一具體實施例之模壓熱壓模具、纏帶胚料 及兩者之間在壓縮前的相對位置關係的剖視圖·， 第四圖顯示本發明之一具體實施例之模壓熱壓模具、該纏帶胚 2及兩者之間在壓縮後的相對位置關係的剖視圖； 第五圖顯示本發明之纏帶模壓法之製造流程圖；及 第六圖顯示習知之纏帶壓力釜成品與本發明具體實施例成品 1299017 之燒蚀溫度比較。 【主要元件符號說明】 1帶料寬度 2纏帶模心 3、4纏帶多餘材料切除線 5、6纏帶多餘材料 7纏帶胚料 8熱壓熱壓模 9下模 10上模 11纏帶胚料下端面 12纏帶胚料上端面 13、14餘隙 15頂出銷孔 16壓縮前模心位置 17燒蝕試驗溫度曲線 18燒蚀試驗溫度曲線* 19燒姓試驗溫度曲線 20燒蝕試驗溫度曲線 21燒姓試驗溫度曲線 11At the same time, the resin was softened, and then the upper core 10 was pressed down with 2^ to mold the hot stamper 8. Month in the mold clamping process: has softened 'the billet part of the billet 7 is stretched ten in the forming pressure, and starts to flow. At the same time, the upper mold 1 breaks in: step = direction: ί: 7 has the clearance 13 14, fill up. The fourth figure shows the relative position of the front 槿1G and the lower dies 9 after the T-mo, and the towel lining 16 represents the pressure 丄ΐ 1 As can be seen from the figure, the lateral direction of the blank 7 is considerably compressed. Hey. In addition, the blank 7 is compressed from the inside to the outside, similar to j r", which does not cause wrinkles. Cohesive, start to heat up to ί _ set molding pressure about, here - molding pressure and temperature a = 2 hours to cure the resin. Cooling to the chamber _, using the ejector pin (not smashed out) from the ejector pin hole 15 to get the finished product. The entire splicing-molding procedure is shown in the fifth figure, and the winding pressure autoclave program of the first figure In comparison, it can be seen that the method of the present invention is much simpler. The tape-wrapped tapered composite pipe fittings manufactured by the above procedure have a smooth appearance without any need for repair, and the fibers are arranged in a neat manner. 80% of them have no flaws at all, and the same is used for the tape wrapping method, but only about 30% of the pressure-formed molds have no flaws. The measured density of the mouthpiece produced in this embodiment is 1.45 to 1· Between 5 g/cm3, and the pressure dad molding only f 1·40 to 1.42 g/cm3. The ablation test results show that the ablation rate of the wrinkles on the upper part of the pressure cooker is significantly larger. Figure 6 shows the temperature of the ablation test 1299017 bh ^ member shows the transfer rate of the wrinkles of the finished product (curve 17): ί position (curves 18, 19), the heat generated by the tool, and therefore There is no local _ too large and outside method and gamma, must weave _ Yes, although the aforementioned examples use rhyme field resin Prepreg, but it can also include other suitable materials, materials, and materials that are sufficient and suitable for the desired properties. In addition, although the above-mentioned special tape wrapping machine is used to make the wrapping material, The invention can be used for the winding of the machine or the machine with the automatic rotating chuck as the auxiliary tool. The so-called conical tube member is not limited to the straight oblique shape, and can be applied to the curved bevel, or the inclined cone having two or more slopes, or 2 The layer material 'in these cases' is designed to avoid the difference in the density of the finished parts, and the shape of the upper and/or lower molds of the stamper is not designed to conform to the inner and/or outer contours of the entangled blank, but is designed such that After the compression of the billet, the amount of compression of the bean U is close. Finally, the _ local frequency is implemented as a parallel system; ^, and the number of the blanks is repeated, but the possibility of using the slanting tape is not excluded. For the purpose of the preferred embodiment of the present invention, it is not intended to limit the implementation of the singularity of the lion, and the equal change and modification made by the technical idea of the creation should be covered. Within the scope of the patent application for this creation. BRIEF DESCRIPTION OF THE DRAWINGS A diagram showing a flow chart of the main steps of the prior art wrapping pressure dad process; the second drawing shows a schematic view of the wrapping core and the wrapping of one embodiment of the present invention, for clarity It is shown that the mold core is not hatched; the third figure shows a cross-sectional view of the relative positional relationship between the molded hot stamping die, the wrapped billet and the prior art before compression in one embodiment of the present invention, and the fourth figure shows the present A cross-sectional view showing a relative positional relationship between a molded hot stamping die, the wrapped tape 2 and a compressed portion thereof according to an embodiment of the present invention; and a fifth drawing showing a manufacturing flow chart of the tape wrapping molding method of the present invention; Figure 6 shows a comparison of the ablation temperature of the finished tape wound autoclave with the finished product 1299017 of the specific embodiment of the present invention. [Main component symbol description] 1 strip width 2 wrapped ribbon core 3, 4 wrapped with excess material cutting line 5, 6 wrapped with excess material 7 wrapped with billet 8 hot pressed hot stamping die 9 lower die 10 upper die 11 wrapped with billet blank lower end 12 wrapped with billet upper end end face 13, 14 clearance 15 top pin hole 16 compression front mold Heart position 17 ablation test temperature Erosion test temperature profile curve 18 * 20 19 firing temperature erosion test temperature profile name Test name Test firing temperature curve 21 curve 11