591171 玖、發明說明： 【發明所屬之技術領域】 本發明係關於一種將阻燃層粘著加工於固體火箭發動 機鋼殼末端近啣接喷嘴處之設備及其方法。 【先前技術】 固體火箭發動機之推進劑係由多種高能燃料、氧化劑 與膠合劑所組成，經點火系統引燃產生大量氣體，放出極 高熱能，熱量在發動機之有限空間内累積，溫度可高達24〇〇 C至3700 C，危及發動機外殼安全。各類型飛彈，在其發動 機内均必需具備有阻燃層裝置，以維安全。 阻燃層之型態概分橡膠薄片、膠糊、及塗料等，其中橡 膠薄片由於施工容易而廣泛使用於多種中、大型飛彈之火 箭嘗貧貧。美酉本 、u sp 4507165、USP4501841 及 USP 4878431 等，均以不同配方， 製作成可塗佈（coating )或積層（iay Up)於火箭發動機外 殼内之塗料或膠片阻燃材料。 製作完成之阻燃層材料，需以特定之機械方法加工， 使附著於發動機外殼之内壁，保護鋼殼不致因高溫而損 壞。加工方法則針對不同阻燃層型態，而有塗料型阻燃層 之喷塗法（Spray coatinS )，膠糊型阻燃層之刮塗法（paring ) 等膠片狀阻燃層則因應用廣泛而有吹膜膨脹法（㈣⑽仏 mandrel technical)、模製法（m〇lding)、手工積層法（㈤随以 layup)及繞帶法（stripwindingtechnique)等技巧，將阻 5 燃層橡膠膠片加工’使附著於發動機之外殼内壁。 由於需在發動機鋼殼末端加裝喷嘴段，鋼殼在該部位 之内徑快速減縮，以致推進劑燃燒所產生之高溫、高壓氣 體，因通路縮小而壓力遽升，對鋼殼之沖刷力量加大。針 對此一狀況，一般多以增加鋼殼末端阻燃層之厚度以為因 應。但發動機末端之鋼殼，在短距離内口徑縮小而產生·彎 度，因幾何結構之改變，導致在該部位加工粘著阻燃層之 技術困難度增加。例如以傳統之手工積層法施工，易產生 在鋼殼彎曲部位阻燃層粘著不良，或阻燃層與鋼殼間殘存 氣泡等缺點。為確保施工之完善及增加施工之效益，以本 發明特別設計之施工機具及相配合之施工方法，可達提高 工施品質之目的。 【發明内容】 本發明之目的，在提供一種針對火箭發動機鋼殼末端 阻燃層之成型粘著加工機具。藉使用此一機具，可將預鑄 成型之阻燃層膠圈準確定位於發動機鋼殼末端，進而可對 阻燃層膠圈施加壓力，並於加熱後使阻燃層膠圈熟化並強 固粘著於發動機鋼殼内壁。 本發明之另一目的，在提供一種火箭發動機鋼殼末端 阻燃層之施工方法。該方法包含將阻燃層膠片預鑄成型成 一環狀膠圈，並予以部份熟化；然後將部份熟化的阻燃層 膠圈粘著於鋼殼末端之内壁；對該被粘著的阻燃層膠圈施 壓並且加熱，使阻燃層熟化並固著於鋼殼内壁上。於火箭 591171 發射時該被熟化阻燃層可發揮阻燃絕熱之效應，保護發動 機鋼殼，免致燒燬之顧慮。 一般橡膠阻燃層之施卫，多採以生膠使料同方法，使‘ 之枯著於發動機鋼殼之内壁，再行熟化處理。傳統上，最 為簡單可行之方法為手工積層法，但由於不同阻燃層之材 質物性差異，及發動機鋼殼直徑大小不同，施工之難易度 均有相當大之差別，例如含纖維量高之阻燃層膠片，生膠 剛性（toughness)大，加工困難。而大尺寸發動機之貼製阻 燃層，雖可由人員進入鋼殼内施工，但仍因鋼殼内空間狹 窄而昏暗閉塞，施工條件極度不良，而有工業安全之顧慮。 小尺寸之發動機内則更受限於工作空間狹隘，而施工更加 困難。本發明將阻燃層在鋼殼外先期預鑄成型，並予以適 當之部份熟化處理，使阻燃層具有固定之形狀。同時，預 鑄成型之阻燃層經部份熟化，即具一定之硬度，而不易變 形’在操作上增加許多方便。 再者’鋼殼末端因需聯接喷嘴而内徑收縮，其脊管部位 不利阻燃層之施工。若以手工操作，會因壓力施加不勻， 而易在介面間殘留氣泡。氣泡存留於阻燃層與阻燃層或與 鋼殼間，將大為減弱材質介面間之粘著力，使因高溫而碳 化之阻燃層，在推進劑燃燒所生強大氣流沖刷下，極易剝 離’以致耐燒蝕性大為降低。本發明將阻燃層預铸成型， 並先期部份熟化，可避免層與層間產生氣泡。部份熟化之 預鑄成型阻燃層膠圈，在本發明所設計之機具上，以石夕橡 膠塊為膨脹加塵之介質，施力於經定位之預铸膠圈上，可 7 591171 使牢固粘著於鋼殼，能大為提高工作效率，節省工作時間 和人力’提高工作效力。 【實施方式】 本發明提供一種火箭發動機鋼殼末端阻燃層施工機 具，其中一阻燃層膠圈被粘著於該發動機鋼殼末端内壁 上，該機具包含： 一用於固定於該鋼殼末端開口的蓋； 一移動的結合於該蓋的第一金屬塊，其具有一圓錐體 部份，該圓錐體部份的較小端比較大端靠近該蓋，並且該 第一金屬塊可被驅動使該圓錐體部份的較小端靠近或遠離 該蓋垂直移動； 一耐熱橡膠圈，其具有對應於該阻燃層膠圈的形狀的 外緣，及具有對應於該第一金屬塊的圓錐體部份的圓錐形 内緣，於是該耐熱橡膠圈的圓錐形内緣可被放置於該第一 金屬塊的圓錐體部份上，且在該第一金屬塊被置於該發動 機鋼殼内及該蓋被固定於該鋼殼末端開口後，該耐熱橡膠 圈的外緣可密貼於該阻燃層膠圈，此時當該第一金屬塊被 驅動往該蓋靠近時’該阻燃層膠圈為該耐熱橡膠圈所施壓 而緊貼於該鋼殼末端内壁上；而當㈣—金屬塊被驅動遠 離該蓋且該蓋由該鋼殼末端開口取下後，該耐熱橡膠圈及 該第一金屬塊可通過該阻燃層膠圈由該鋼殼末端開口取 出。 較佳的’該施工機具進一步包含一設於該第一金屬塊 8 的螺桿；-設於該蓋的套管，其中該螺桿係沿著該圓錐體· 部份之軸心方向設置，且該螺桿伸入該套管並且露出於該、 蓋；及一結合於該螺桿露出於該蓋的部份的螺帽，於是藉 由旋轉該螺帽可驅動該第一金屬塊靠近或遠離該蓋。更佳 的，該施工機具進一步包含一結合於該蓋的固定鋼板及一 結合於該固定鋼板的第二金屬塊，其中該固定鋼板及第二 金屬塊介於該蓋與該第一金屬塊之間且均具有容納該套管 穿過之中心孔’該固定鋼板具有一等於或略小於該鋼殼末 端開口之直徑，該第二金屬塊具有一等於或略小於該耐熱 橡膠圈的一直立内緣的直徑，於是當該耐熱橡膠圈被置於 該第一金屬塊的圓錐體部份外緣上，該蓋被固定於該鋼殼 末端開口且該螺帽被旋緊時，該固定鋼板及該第二金屬塊 位於該鋼殼内，且該固定鋼板貼於該耐熱緣橡膠圈的一頂 面’且該第二金屬塊的外圓周貼於該耐熱橡圈的直立内緣。 較佳的，該套管露出於該蓋之部份被設有一通氣裝 置’可與一真空幫浦相連接；及該第一金屬塊被設有一通 β 氣孔’其中該蓋係密合於該鋼殼末端開口，於是當該真空 幫浦被啟動時，該發動機鋼殻内被抽真空。 較佳的，該耐熱橡膠圈為具有一 Shore Α硬度為50〜60 之矽橡膠圈。 本發明亦提供一種火箭發動機鋼殼末端阻燃層之施工 方法，該方法包含將阻燃層膠片預鎊成型成一環狀膠圈， 並予以部份熟化；然後將部份熟化的阻燃層膠圈粘著於鋼 殼末端之内壁；對該被粘著的阻燃層膠圈施壓並且對該鋼 殼加熱，使阻燃層熟化並固著於鋼殼内壁上。 較佳的於本發明方法中在對該被粘著的阻燃層膠圈 施壓並且對該鋼殼加熱的同時，對該發動機鋼殼内部抽真 空。 較佳的，於本發明方法中對該被粘著的阻燃層膠圈施 壓係透過一具有一 shore A硬度為50〜60之矽橡膠進行。 以下將參照一較佳實施例說明本發明。 阻燃層膠圈之預鑄成型 依發動機鋼殼末端阻燃層之厚度、寬度和鋼殼末端圓 周之規袼，製作一平板膠片成型模具以製備阻燃層之平板 膠片。將阻燃層之薄片膠料依所需規格剪裁並加以積層， 其層與層間需先行塗刷膠料之溶劑，陰乾後，逐層黏貼， 並以手動操作方式，用滾筒加壓，以排除膠材層面間之空 氣，再放入該成型模具中定型。將完成定型之阻燃層平板 膠片由成型模具取出，膠片之兩端分別以45。切成各自向内 及向外的斜面，再於該兩斜面上塗刷粘著劑後頭尾互相黏 貼’即成阻燃層膠圈之生膠粗胚。 就阻燃層膠圈尺寸，製作一鋼製模具，模具上並附有 通氣裝置，以排除粗胚及模具内之空氣，並可於粗胚熟化 時’使模具内保持真空狀態。在熱壓機（hot press )上預 熱模具，將經阻燃層膠圈之生膠粗胚放入鋼模内，蓋合模 蓋，將模具放入熱壓機之上、下加熱板間，啟動真空裝置， 並依阻燃層膠材的熟化溫度和壓力操作熱壓機，使鋼模内 之阻燃層膠圈之生膠粗胚進行熟化反應，在僅達完全熟化 591171 之四刀之至一刀之一的熟化時間即取出該阻燃層膠圈。 生膠粗胚之熟化程度’可以由熟化反應之起始點至反應終 結點之Μ變化曲線得知，其係使用橡膠流變儀（M_ey ViSC〇meter)測量得到的。截取全部反應曲線之1/4、1/3 或1/2部位之反應日夺間，可大致得到生膠粗胚之1/4、1/3 或1/2彳&熟化之程度。部份熟化之阻燃層膠圈，仍具相 田黏度卩利於與鋼殼相枯著，但因膠圈已部分交聯而具 相當程度硬度，而較易操控，方便後續之加工操作。 將完成部份熟化之阻燃層膠圈由模具中取出，靜置於 清潔不受污染處待用。 施工加壓機具 本發明之火箭發動機鋼殼末端阻燃層粘著加工的施工 加壓機具1#一較佳具體實施例被示於圖一。其功能為針 對定位於鋼殼末端12之阻燃層預鑄膠圈16施加壓力，使 阻燃層膠圈16能在加溫及加壓狀態下，藉助粘著劑15而 牢固粘著於鋼殼末端12之内壁。施工加壓機具丨由鋼殼n 及加壓組件20組成，加壓組件2〇包含加壓用之圓形鋁合 金塊21和22、螺桿23和螺帽24、矽橡膠圈3〇、固定鋼 板25及鋼殼末端蓋40。鋁合金塊21之下緣2ι〇直徑需略 小於阻燃層膠圈16經定位熟化後其内徑最小處之尺寸，如 此鋁合金塊21才能穿過阻燃層膠圈16被取出；上緣212 具有一斜面，頂部則向下直接凹入形成一凹槽214。紹人 金塊22之直徑略小於鋁合金塊上方凹槽214之直秤， 如此，鋁合金塊22可在鋁合金塊21之上方凹槽内上、下 11 591171 自由運動，鋁合金塊22之中央有一穿透的圓洞，可使螺桿· 23由此伸出，達於發動機外。铭合金塊21上緣212斜面 · 及鋁合金塊22之外圓周與預鑄成型之矽橡膠圈30之内緣 303及301相接。石夕橡膠圈30之外緣302的形狀則隨阻燃 層膠圈16之内側形狀而定。矽橡膠圈30具有由膠圈内部 向外、向下斜面303，其斜角與鋁合金塊21之上方斜角同 為45G，其斜面之高度亦與之相同。石夕橡膠圈3〇與阻燃層 膠圈16具有相同之高度。鋁合金塊22、矽橡膠圈30與阻 燃層膠圈16之上方置一固定鋼板25，其直徑與阻燃層膠 __ 圈16最接近鋼殼末端12處之外徑相同，固定鋼板25可限 定銘合金塊22與矽橡膠圈30之移動。固定鋼板25以三支 連桿26固定在鋼殼末端蓋40上，連桿26之長度，與阻燃 層膠圈16之最後端至鋼殼末端邊緣之距離相同。連桿26 之一端具螺牙，可旋入於固定鋼板25上之螺孔261内，另 、則具螺孔262,可以螺絲401鎖定在鋼殼末端蓋4〇上， 鋁合金塊22具有螺孔221，可以螺絲27鎖定在固定鋼板 25上。鋼殼末端蓋4〇之内徑與鋼殼末端12之外徑相同， 而可以螺絲41鎖定在鋼殼末端12上，鋼殼末端蓋40上附 有〇型環42,螺絲41則附有橡膠墊片（未示於圖中），於是 蓋4〇之螺絲41被鎖定後，可保持鋼殼〖丨内成密封狀態。 蓋40和固定鋼板25之中央均開一圓孔，以容螺桿穿 過，鋁合金塊22、固定鋼板25及蓋4〇之中央圓孔直徑相 同，且大於螺桿23之直徑，可容在螺桿23外置一套管28， 套管28之外徑與鋁合金塊22、固定鋼板25及蓋4〇之中 12 591171 央圓孔直徑相同，套管28之 μ 卜鹄向下延伸，與鋁合金塊· 2之下緣相對齊’上端伸出於蓋4〇之上，套管28可以螺 牙旋緊在蓋4〇上’螺牙間以止线帶保持密封，或以焊接方 式將套管28固定在蓋40上，以保持密封，套管28上端置 一橡膠墊片241 ’當螺帽24向下旋緊時，套管28與螺桿 23間不致漏氣。套管28上方之露出於蓋40處，以鎖螺牙 之方式裝設該通氣裝置281 ’由通氣裝置281接連抽真空 幫浦（未顯示），可抽除發動機1〇鋼殼丨丨内之空氣。鋁合 金塊21上亦須開一通氣孔251，以利排除鋼殼u内之全部 氣體。 將螺帽24向下移動並旋緊，可使鋁合金塊21向上位 移，對矽橡膠圈30造成壓力而變形，進而擠壓阻燃層膠圈 16。由鋼殼U外加熱，阻燃層膠圈16即可在加溫、加壓 之情況下完成熟化。 為使矽橡膠圈30受壓變形後能對阻燃層產生適當的 壓力’應選擇以Shore A硬度計量測硬度為5〇〜60之矽橡 膠材料，以製備矽橡膠圈30。 鋼殼末端阻燃層之粘著加工 實施阻燃層膠圈16加工粘著前，需先行將發動機1〇 之鋼殼11内層，施行喷砂除鏽及溶劑除油之清潔手續，待 溶劑陰乾後，儘速在鋼殼11内層喷塗粘著劑1 5，以防止鋼 殼11繼續生鏽，並於阻燃層膠圈粘著時，產生強固之粘著 力。粘著劑15之選擇，取決於阻燃層膠圈16之組成橡膠 材質而定，如阻燃層係以NBR橡膠為基材，即應採用 13591171 (1) Description of the invention: [Technical field to which the invention belongs] The present invention relates to a device and method for adhesively processing a flame-retardant layer at the end of a steel shell of a solid rocket engine near a nozzle. [Previous technology] The propellant of solid rocket engine is composed of a variety of high-energy fuels, oxidants and cements. It is ignited by the ignition system to generate a large amount of gas, which emits very high thermal energy. The heat is accumulated in the limited space of the engine, and the temperature can reach 24 〇〇C to 3700 C, endanger the safety of the engine casing. All types of missiles must be equipped with a flame-retardant layer device in their engines to maintain safety. The flame retardant layer can be classified into rubber flakes, pastes, and coatings. Among them, rubber flakes are widely used in the fire of a variety of medium and large missiles due to the ease of construction. Mimoto, Usp 4507165, USP4501841, and USP 4878431, etc., are made of coatings or film flame retardant materials that can be coated or laminated in the shell of rocket engines with different formulations. The finished flame retardant material needs to be processed by a specific mechanical method to make it adhere to the inner wall of the engine casing and protect the steel casing from damage due to high temperature. The processing method is aimed at different types of flame retardant layers, and film-like flame retardant layers such as spray coating method of coating flame retardant layer (paring) and paste type flame retardant layer (paring) are widely used due to its wide application. There are techniques such as blown film expansion (㈣⑽ 仏 mandrel technical), molding (molding), manual lamination (㈤ followed by layup), and stripwinding technology (stripwinding technology). Attached to the inner wall of the engine casing. Due to the need to install a nozzle section at the end of the engine's steel shell, the inner diameter of the steel shell shrinks rapidly at this location, so that the high-temperature and high-pressure gas generated by the combustion of the propellant, the pressure rises due to the narrowing of the passage, which increases the scouring force of the steel shell. Big. In response to this situation, it is generally to increase the thickness of the flame retardant layer at the end of the steel shell. However, the steel shell at the end of the engine has a reduced diameter and a short curvature within a short distance. The change in the geometric structure has led to an increase in the technical difficulty of processing the adhesive flame retardant layer at this location. For example, the traditional manual lamination method is easy to produce shortcomings such as poor adhesion of the flame retardant layer in the curved part of the steel shell, or residual air bubbles between the flame retardant layer and the steel shell. In order to ensure the perfection of construction and increase the benefits of construction, the purpose of improving the quality of construction can be achieved by using the specially designed construction equipment and matching construction methods of the present invention. SUMMARY OF THE INVENTION The object of the present invention is to provide a molding and adhesion processing tool for a flame-resistant layer at the end of a steel shell of a rocket engine. By using this machine, the flame retardant rubber ring formed by the concrete can be accurately positioned at the end of the steel casing of the engine, so that the flame retardant rubber ring can be pressed, and the flame retardant rubber ring can be matured and firmly adhered after heating. Focus on the inner wall of the engine steel shell. Another object of the present invention is to provide a construction method of a flame retardant layer at the end of a steel shell of a rocket engine. The method includes forming a flame-retardant film into a ring-shaped rubber ring and partially curing the rubber ring; and then partially curing the flame-retardant rubber ring to the inner wall of the end of the steel shell; The burning layer rubber ring is pressed and heated to ripen and fix the flame retardant layer on the inner wall of the steel shell. When the rocket 591171 is launched, the cured flame retardant layer can exert the effect of flame retardant insulation and protect the steel casing of the engine from the fear of burnout. Generally, the flame retardant layer of rubber is protected by the same method of using raw rubber to make the ‘dry on the inner wall of the engine steel shell, and then aging treatment. Traditionally, the most simple and feasible method is manual lamination. However, due to the different physical properties of different flame-retardant layers and the diameter of the engine steel shell, the difficulty of construction is quite different, such as the resistance of high fiber content. Laminated film has high toughness of raw rubber and is difficult to process. For large-size engines, although the flame retarding layer is attached to the steel shell for construction, it is still dimly occluded due to the narrow space in the steel shell, extremely poor construction conditions, and concerns about industrial safety. The smaller size of the engine is more constrained by the narrow working space and the construction is more difficult. In the present invention, the flame-retardant layer is preliminarily molded outside the steel shell, and an appropriate partial curing treatment is performed to make the flame-retardant layer have a fixed shape. At the same time, the pre-molded flame-retardant layer is partially cured, that is, it has a certain hardness and is not easily deformed, which adds a lot of convenience in operation. In addition, the inner diameter of the end of the steel casing shrinks due to the need to connect the nozzle, and its spinal tube portion is not conducive to the construction of the flame retardant layer. If it is operated manually, uneven pressure will be applied and air bubbles will easily remain between the interfaces. Air bubbles remain between the flame retardant layer and the flame retardant layer or with the steel shell, which will greatly reduce the adhesion between the material interfaces, so that the flame retardant layer that is carbonized due to high temperature will be easily washed away by the strong airflow generated by the propellant combustion. Peeling 'so that the ablation resistance is greatly reduced. In the present invention, the flame-retardant layer is pre-molded and partially matured in advance to prevent air bubbles from being generated between the layers. Part of the cured slab forming flame retardant rubber ring, on the machine designed by the present invention, using Shixi rubber block as the expansion and dusting medium, applying force on the positioned pre-cast rubber ring, can be 7 591171 It is firmly adhered to the steel shell, which can greatly improve work efficiency, save work time and manpower, and improve work efficiency. [Embodiment] The present invention provides a construction tool for a flame retardant layer on the end of a steel shell of a rocket engine. A flame retardant rubber ring is adhered to the inner wall of the end of the steel shell of the engine. The tool includes: a for fixing to the steel shell A cover that is open at the end; a first metal block that is coupled to the cover and has a cone portion, the smaller end of the cone portion being closer to the cover than the larger end, and the first metal block can be The driving causes the smaller end of the cone portion to move vertically toward or away from the cover; a heat-resistant rubber ring having an outer edge corresponding to the shape of the flame-retardant rubber ring, and having a first metal block corresponding to the The conical inner edge of the cone portion, so the conical inner edge of the heat-resistant rubber ring can be placed on the cone portion of the first metal block, and the first metal block is placed on the engine steel casing Inside and after the cover is fixed to the opening of the end of the steel shell, the outer edge of the heat-resistant rubber ring can be closely attached to the flame-retardant rubber ring. At this time, when the first metal block is driven closer to the cover, the resistance Burning layer rubber ring is applied by the heat-resistant rubber ring It is closely attached to the inner wall of the end of the steel shell; and when the metal block is driven away from the cover and the cover is removed from the end of the steel shell, the heat-resistant rubber ring and the first metal block can pass the flame retardant The rubber ring is taken out from the opening at the end of the steel shell. Preferably, the construction tool further includes a screw provided on the first metal block 8; a sleeve provided on the cover, wherein the screw is provided along an axial direction of the cone portion; and A screw extends into the sleeve and is exposed to the cover; and a nut coupled to a portion of the screw exposed to the cover, so that the first metal block can be driven closer to or away from the cover by rotating the nut. More preferably, the construction tool further includes a fixed steel plate coupled to the cover and a second metal block coupled to the fixed steel plate, wherein the fixed steel plate and the second metal block are interposed between the cover and the first metal block. The fixed steel plate has a diameter equal to or slightly smaller than the end opening of the steel shell, and the second metal block has an upright inside which is equal to or slightly smaller than the heat-resistant rubber ring. The diameter of the flange, so when the heat-resistant rubber ring is placed on the outer edge of the cone portion of the first metal block, the cover is fixed to the end of the steel shell opening and the nut is screwed, the fixed steel plate and The second metal block is located in the steel shell, the fixed steel plate is affixed to a top surface of the heat-resistant rubber ring, and the outer circumference of the second metal block is affixed to the upright inner edge of the heat-resistant rubber ring. Preferably, a part of the sleeve exposed on the cover is provided with a ventilation device 'can be connected to a vacuum pump; and the first metal block is provided with a β air hole', wherein the cover is tightly attached to the The end of the steel case is open, so when the vacuum pump is activated, the inside of the engine steel case is evacuated. Preferably, the heat-resistant rubber ring is a silicon rubber ring having a Shore A hardness of 50-60. The invention also provides a construction method of a flame retardant layer at the end of a steel shell of a rocket engine. The method includes forming a flame retardant film into a ring-shaped rubber ring, and partially curing the flame retardant film; and then partially curing the flame retardant layer rubber. The ring is adhered to the inner wall of the end of the steel shell; pressure is applied to the adhered flame retardant rubber ring and the steel shell is heated to mature and fix the flame retardant layer on the inner wall of the steel shell. It is preferred that in the method of the present invention, the inside of the steel casing of the engine is evacuated while applying pressure to the adhered flame retardant rubber ring and heating the steel casing. Preferably, in the method of the present invention, the pressure applied to the adhered flame retardant rubber ring is performed through a silicone rubber having a shore A hardness of 50-60. The invention will be described below with reference to a preferred embodiment. Forming of the rubber ring of the flame retardant layer According to the thickness and width of the flame retardant layer at the end of the steel casing of the engine and the circumference of the end of the steel casing, a flat film forming mold is prepared to prepare the flat film of the flame retardant layer. The flame retardant layer of the rubber compound is cut and laminated according to the required specifications. The solvent of the rubber compound must be applied between the layers and the layers. After drying, it should be pasted layer by layer, and manually pressed with a roller to eliminate it. The air between the layers of the plastic material is then placed in the forming mold for setting. Take out the finished flame-retardant flat plate film from the forming mold, and the two ends of the film should be 45. Cut into the inward and outward oblique surfaces, and then apply the adhesive on the two oblique surfaces, and then stick the head and tail to each other to form the crude rubber embryo of the flame retardant rubber ring. Regarding the size of the rubber ring of the flame retardant layer, a steel mold is made, and a venting device is attached to the mold to eliminate the air in the rough embryo and the mold, and the vacuum state of the mold can be maintained when the rough embryo is matured. Preheat the mold on a hot press, put the raw rubber rough material after the flame retardant rubber ring into the steel mold, close the mold cover, and place the mold between the upper and lower heating plates of the hot press. , Start the vacuum device, and operate the hot press according to the maturation temperature and pressure of the flame retardant rubber material, so that the raw rubber rough embryo of the flame retardant rubber ring in the steel mold undergoes the ripening reaction, and only reaches the full ripeness of 591171. Take out the aging ring of the flame retardant layer to one-knife. The maturation degree of the crude rubber embryo can be known from the M change curve from the starting point of the ripening reaction to the end point of the reaction, which is measured by using a rubber rheometer (M_ey Viscometer). Intercept the reaction time of 1/4, 1/3, or 1/2 of the entire reaction curve, and roughly obtain the degree of 1/4, 1/3, or 1/2 彳 & maturation of the crude rubber embryo. Part of the cured flame retardant rubber ring still has the same viscosity, which is conducive to dryness with the steel shell, but because the rubber ring has been partially crosslinked and has a certain degree of hardness, it is easier to handle and facilitate subsequent processing operations. Remove the partially cured flame retardant rubber ring from the mold and leave it in a clean and uncontaminated place for use. Construction pressurization tool A preferred embodiment of the construction pressurization tool 1 # for the adhesion processing of the flame-resistant layer at the end of the steel shell of the rocket engine of the present invention is shown in FIG. Its function is to apply pressure to the flame retardant rubber ring 16 positioned at the end 12 of the steel shell, so that the flame retardant rubber ring 16 can be firmly adhered to the steel with the help of the adhesive 15 under a heated and pressurized state. The inner wall of the shell end 12. Construction press machine 丨 It consists of a steel shell n and a pressurizing component 20. The pressurizing component 20 includes round aluminum blocks 21 and 22 for pressing, a screw 23 and a nut 24, a silicone rubber ring 30, and a fixed steel plate. 25 和 40。 Steel case end cover 40. The diameter of the lower edge of the aluminum alloy block 21 is slightly smaller than the size of the inner diameter of the flame retardant rubber ring 16 after being positioned and matured, so that the aluminum alloy block 21 can be taken out through the flame retardant rubber ring 16; 212 has an inclined surface, and the top is directly recessed downward to form a groove 214. The diameter of Shaoren bullion 22 is slightly smaller than the straight scale of the groove 214 above the aluminum alloy block. In this way, the aluminum alloy block 22 can move up and down 11 591171 in the groove above the aluminum alloy block 21, and the center of the aluminum alloy block 22 is free. There is a penetrating circular hole, which can make the screw · 23 protrude from this and reach the engine. The upper edge 212 bevel of the alloy block 21 and the outer periphery of the aluminum alloy block 22 are in contact with the inner edges 303 and 301 of the silicone rubber ring 30 formed by the concrete. The shape of the outer edge 302 of the Shixi rubber ring 30 depends on the shape of the inner side of the flame retardant rubber ring 16. The silicon rubber ring 30 has an inclined surface 303 outward and downward from the inside of the rubber ring. The inclined angle is the same as that of the aluminum alloy block 21, and the height of the inclined surface is the same. The Shixi rubber ring 30 has the same height as the flame-retardant layer rubber ring 16. A fixed steel plate 25 is placed above the aluminum alloy block 22, the silicon rubber ring 30 and the flame retardant rubber ring 16, and its diameter is the same as the outer diameter of the flame retardant rubber ring 16 closest to the end of the steel shell. The fixed steel plate 25 The movement of the alloy block 22 and the silicone rubber ring 30 can be limited. The fixed steel plate 25 is fixed on the steel case end cover 40 by three connecting rods 26, and the length of the connecting rod 26 is the same as the distance from the rear end of the flame retardant rubber ring 16 to the end edge of the steel case. One end of the connecting rod 26 is provided with a screw thread, and can be screwed into a screw hole 261 on the fixed steel plate 25, and the other has a screw hole 262, which can be screwed on the steel case end cover 40 with a screw 401. The aluminum alloy block 22 has a screw The hole 221 can be locked on the fixed steel plate 25 with a screw 27. The inner diameter of the steel case end cover 40 is the same as the outer diameter of the steel case end 12, and the screw 41 can be locked on the steel case end 12, the steel case end cover 40 is provided with an o-ring 42, and the screw 41 is provided with rubber. Gasket (not shown in the figure), so after the cover 41's screw 41 is locked, the steel case can be kept sealed inside. A circular hole is opened in the center of the cover 40 and the fixed steel plate 25 to allow the screw to pass through. The central circular holes of the aluminum alloy block 22, the fixed steel plate 25 and the cover 40 have the same diameter and are larger than the diameter of the screw 23, and can be accommodated in the screw 23. An external set of tubes 28, the outer diameter of the sleeve 28 is the same as the diameter of the central circular hole of the aluminum alloy block 22, the fixed steel plate 25, and the cover 40. The diameter of the circular hole of the sleeve 28 extends downward, and it is the same as that of the aluminum alloy. The lower edge of the block 2 is relatively aligned. The upper end protrudes above the cover 40, and the sleeve 28 can be screwed on the cover 40. The thread between the screws is sealed with a stop band, or the sleeve is welded. 28 is fixed on the cover 40 to maintain a seal. A rubber washer 241 is placed on the upper end of the sleeve 28. When the nut 24 is screwed down, there is no air leakage between the sleeve 28 and the screw 23. The upper part of the sleeve 28 is exposed at the cover 40, and the venting device 281 is installed in the manner of a locking screw. The venting device 281 is successively evacuated by a vacuum pump (not shown), and the engine 10 steel casing can be removed. air. The aluminum alloy block 21 must also be provided with a vent hole 251 to facilitate the exclusion of all the gas in the steel shell u. Moving the nut 24 downward and tightening it can cause the aluminum alloy block 21 to move upward, causing pressure on the silicone rubber ring 30 to deform, and then squeezing the flame-retardant rubber ring 16. Heated from the outside of the steel shell U, the rubber ring 16 of the flame-retardant layer can be cured under heating and pressure. In order to make the silicone rubber ring 30 have a proper pressure on the flame retardant layer after being deformed under pressure, a silicon rubber material with a hardness of 50 to 60 measured by Shore A hardness measurement should be selected to prepare the silicone rubber ring 30. Adhesive processing of the flame retardant layer at the end of the steel shell Before the flame retardant rubber ring 16 is processed and adhered, the inner layer of the steel shell 11 of the engine 10 must be cleaned by sandblasting and rust removal and solvent degreasing. Then, spray the adhesive 15 on the inner layer of the steel shell 11 as soon as possible to prevent the steel shell 11 from continuing to rust, and when the rubber ring of the flame retardant layer is adhered, a strong adhesive force is generated. The choice of adhesive 15 depends on the rubber material of the rubber ring 16 of the flame retardant layer. If the flame retardant layer is based on NBR rubber, 13 should be used.
Chemlock 234為粘著劑，以EpDM橡膠為基材之阻燃層， 則需使用Chemlock 238為粘著劑。 將經半熟化之阻燃層膠圈丨6之外侧噴塗粘著劑1 5，該 部位須與鋼喊緊密粘著。使粘著劑丨5中之溶劑在室溫下陰 乾，將阻燃層膠圈16定位於鋼殼末端12處，將鋁合金塊 21由鋼殼末端12開口處，放入於鋼殼内此時與鋁合金塊 21 —體的螺桿23伸出於鋼殼外且被夾持呈懸吊狀態。再 於鋁合金塊21斜邊上平整放下矽橡膠圈3〇，使定位在阻 燃層膠圈16之内側。然後將預先結合之鋁合金塊22、固 疋鋼板25、及連桿26之整體組件仔細放入於發動機鋼殼 11中，使鋁合金塊22適當嵌入於鋁合金塊21之上方凹槽 214中。此一步驟亦可以分解動作執行，即在鋁合金塊2ι 和22及矽橡膠圈30定位後，先將固定鋼板25定位，由固 疋鋼板25之穿孔25 1及鋁合金塊22上之螺孔221以螺絲 27將鋁合金塊22鎖定在固定鋼板25，然後，將各連桿26 分別旋入固定鋼板25上，將鋼殼末端蓋4〇仔細定位，使 固定於其上之套管28穿過固定鋼板25,套管28進入鋁合 金塊22後’以螺絲401穿過蓋4〇上之穿孔402並旋入螺 孔262 ’將連桿26與鋼殼末端蓋4〇連接。鋼殼末端蓋4〇 定位後’旋緊螺絲41，在螺桿23上放置橡膠墊片241及 鎖上螺帽24。將通氣裝置281與真空幫浦（未顯示）相連 接，經鋁合金塊21内之開孔216，抽取鋼殼u内阻燃層膠 圈16與鋼殼末端12及其他部位間之空氣，即可旋緊螺帽 24’進而拉動銘合金塊21向上運動，擠壓矽橡膠圈3〇， 591171 矽橡膠圈30因受力而變形，但因其上、下及一侧邊均因受 硬質金屬件21、22及25之阻擋，其變形之體積只能向軟 質之阻燃層膠圈丨6方向位移，因而對阻燃層膠圈16產生 壓力。保持鋼殼11内之真空狀態，依阻燃層膠圈之加工條 件，在鋼殼π外加熱，使阻燃層膠圈16繼續進行熟化反 應’使達完全熟化之程度。 阻燃層膠圈16完全熟化，並牢固粘著於鋼殼末端12 後，停止加熱。待阻燃層膠圈16冷卻至室溫後，逐步拆卸 各組件，完成阻燃層膠圈16之粘著加工。 ％ 【圖式簡單說明】 圖一係火箭發動機末端阻燃層粘著加工之施工機具的 剖面示意圖。 【主要元件圓號說明】 匕施工加壓裝置；10··發動機；11·.鋼殼；12··鋼殼末端；_ 13··鋼殼直筒段；14··鋼殼圓頭端；μ••粘著劑； 16··阻燃層膠圈；20··加壓組件；21、22••鋁合金塊； 210··銘合金塊下緣；212··鋁合金塊上緣； 214··鋁合金塊上方凹槽；216••通氣孔； 221、261、262··螺孔；251 ' 402··穿孔；23··螺桿； 26··連桿；24··螺帽；241··墊圈；25··固定鋼板； 27、41、401··螺絲；28··套管；281·.通氣裝置； 30··矽橡膠圈；301··矽橡膠圈内緣； 302··矽橡膠圈外緣；303··矽橡膠圈下緣斜面； 40··鋼殼末端蓋；42..0型環 15Chemlock 234 is an adhesive. For flame retardant layer based on EpDM rubber, Chemlock 238 is required as an adhesive. Spray the adhesive 15 on the outer side of the semi-cured flame retardant rubber ring 丨 6, and this part must be tightly adhered to the steel. Allow the solvent in the adhesive 5 to dry at room temperature, position the flame retardant rubber ring 16 at the end of the steel shell 12 and place the aluminum alloy block 21 from the end of the steel shell 12 into the steel shell. The screw 23, which is integral with the aluminum alloy block 21, extends out of the steel shell and is held in a suspended state. Then put the silicone rubber ring 30 down on the hypotenuse of the aluminum alloy block 21 so as to be positioned inside the flame retarder rubber ring 16. Then, the entire assembly of the pre-bonded aluminum alloy block 22, the solid steel plate 25, and the connecting rod 26 is carefully placed in the engine steel shell 11 so that the aluminum alloy block 22 is properly embedded in the groove 214 above the aluminum alloy block 21. . This step can also be performed by disassembling the action, that is, after positioning the aluminum alloy blocks 2ι and 22 and the silicone rubber ring 30, the fixed steel plate 25 is first positioned, and the perforations 25 1 of the solid steel plate 25 and the screw holes on the aluminum alloy block 22 are positioned. 221 Lock the aluminum alloy block 22 to the fixed steel plate 25 with screws 27, and then screw each link 26 into the fixed steel plate 25, and carefully position the end cover 40 of the steel shell so that the sleeve 28 fixed thereon is worn. After fixing the steel plate 25, the sleeve 28 enters the aluminum alloy block 22 'through the hole 402 on the cover 40 with a screw 401 and screwed into the screw hole 262' to connect the connecting rod 26 with the end cover 40 of the steel shell. After positioning the end cap of the steel casing 40, the screw 41 is tightened, a rubber washer 241 is placed on the screw 23, and the nut 24 is locked. Connect the ventilation device 281 with a vacuum pump (not shown), and extract the air between the flame retardant rubber ring 16 in the steel shell u and the steel shell end 12 and other parts through the opening 216 in the aluminum alloy block 21, that is, The nut 24 'can be tightened to pull the alloy block 21 to move upwards, and the silicone rubber ring 30 is squeezed. 591171 The silicone rubber ring 30 is deformed by the force, but the upper, lower and one sides are hard metal. For the barriers of pieces 21, 22 and 25, the deformed volume can only be displaced in the direction of the soft flame-retardant layer rubber ring 丨 6, which causes pressure on the flame-retardant layer rubber ring 16. The vacuum state inside the steel shell 11 is maintained, and the flame retardant rubber ring 16 is heated outside the steel shell π in accordance with the processing conditions of the flame retardant rubber ring, so that the flame retardant rubber ring 16 continues to undergo a curing reaction to a degree of complete curing. After the flame retardant rubber ring 16 is completely cured and firmly adheres to the end 12 of the steel shell, the heating is stopped. After the flame retardant rubber ring 16 is cooled to room temperature, the components are gradually disassembled to complete the adhesion processing of the flame retardant rubber ring 16. % [Schematic description] Figure 1 is a schematic cross-sectional view of a construction machine for the adhesion processing of the flame retardant layer at the end of a rocket engine. [Description of horns of main components] Construction pressurization device for dagger; 10 ·· engine; 11 ·· steel case; 12 ·· steel case end; _ 13 ·· steel case straight section; 14 ·· steel case round end; μ • • Adhesives; 16 ·· Flame retardant rubber rings; 20 ·· Pressure components; 21, 22 •• Aluminum alloy blocks; 210 ·· Ming alloy block lower edge; 212 ·· Aluminum alloy block upper edge; 214 · · Slots above aluminum block; 216 ·· Ventilation holes; 221, 261, 262 ·· Screw holes; 251 '402 ·· Perforation; 23 ·· Screw; 26 ·· Link rod; 24 ·· Nuts; 241 · · Washers; 25 ·· Fixed steel plates; 27, 41, 401 ·· Screws; 28 ·· Sleeves; 281 ·. Ventilation devices; 30 ·· Silicone rubber rings; 301 ·· Inner edge of silicon rubber rings; 302 ·· Silicone Outer edge of rubber ring; bevel of lower edge of 303 · silicone rubber ring; 40 ·· steel end cap; 42..0 ring 15