TW412457B - Apparatus and method for assembling a helicopter main rotor blade subassembly - Google Patents

Apparatus and method for assembling a helicopter main rotor blade subassembly Download PDF

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Publication number
TW412457B
TW412457B TW087105760A TW87105760A TW412457B TW 412457 B TW412457 B TW 412457B TW 087105760 A TW087105760 A TW 087105760A TW 87105760 A TW87105760 A TW 87105760A TW 412457 B TW412457 B TW 412457B
Authority
TW
Taiwan
Prior art keywords
assembly
spar
wing
blade
leading edge
Prior art date
Application number
TW087105760A
Other languages
Chinese (zh)
Inventor
Kevin P Leahy
Corey D Jones
David A Kovalsky
Original Assignee
Sikorsky Aircraft Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from US08/838,295 external-priority patent/US5832605A/en
Priority claimed from US08/843,527 external-priority patent/US5836062A/en
Application filed by Sikorsky Aircraft Corp filed Critical Sikorsky Aircraft Corp
Application granted granted Critical
Publication of TW412457B publication Critical patent/TW412457B/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
    • B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Robotics (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Wind Motors (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Toys (AREA)

Abstract

An apparatus and method for assembling a helicopter main rotor blade subassembly which includes a lower airfoil skin, a core, an upper airfoil skin, and a spar assembly having a tip end and a root end, the apparatus comprising a lower assembly including a base having a contoured upper airfoil nest, wherein the contoured upper airfoil nest has a root end and a tip end, at least two guide ramps disposed proximal to the contoured upper airfoil nest, wherein at least one of the guide ramps is disposed proximal to the root end and at least one of the guide ramps is disposed proximal to the tip end, and a plurality of leading-edge pusher cams disposed proximal to the contoured upper airfoil nest. An upper assembly configured for mating with the lower assembly is provided, and comprises a support structure and a flexible impervious membrane supported by the support structure, wherein the flexible impervious membrane and the contoured upper airfoil nest define a molding cavity therebetween upon mating of the upper assembly to the lower assembly.

Description

經濟部智慧財產局員工消費合作社印製 412i57 五、發明說明（21 ) 於步驟516中，翼梁組件116之底端ι06及頂端ι〇8 係利用螺检224將導件326、328插入斜面218内直到翼 梁組件116後緣近側之導件328與各斜面218中的圓錐體 222對接為止，而朝弦長方向正確地加以定位。翼梁組件 Π6底端106及頂端108之正確定位並不需保證翼梁組件 116其他部分會有正碟的弦長方向定位。於步驟jig中， 欲朝弦長方向正確地定位整個翼梁組件116，則需啟動前 緣推輪230，使凸輪面232與翼梁組件U6上的結構加固 點136咬合，並使翼梁組件Π6之後膜塊119緊靠著後膜 推銷228。可以了解的是，後膜推銷228位於弦長方向， 而使後膜塊119與後膜推銷228之間的接觸確保翼梁組件 116後緣正確地固定在型芯114所界定的圓錐體121之 内。當翼梁組件110正確定位之後，將接合劑（未示出）塗 在型芯114與翼梁組件116上面，以準備承接下機翼表皮 112。 於步驟520中，下機翼表皮112被配置在型芯114與 翼梁组件U6上面，並利用下機翼表皮112之後緣工具翼 月130與彈簧加載式工具翼片插銷240 一起定位在翼長及 弦長方向上。於步驟522卡，有一塊胎膜板242被配置在 禁葉次組件132上面（見第6圓），其作用在於分配在緊壓 悻不透水隔膜254施用至獎蕾次組件丨32的腎懕 於步驟524中上二袋式過濾器244係被配詈在胎腹柘 其作用在於幫助排出於緊壓期間滯 留在胎膜板242與撓性不透水隔膜254之間的空氣，並減 少槳葉次組件132與撓性不透水隔琪254之間的摩擦。 於步驟526中，支撐結構252轉至第二位置並固定在 {請先閱讀背面之注意事項再填寫本頁) -------^---------^ J. -----------------------Printed by the Consumers ’Cooperative of the Intellectual Property Bureau of the Ministry of Economic Affairs 412i57 V. Description of the invention (21) In step 516, the bottom end ι06 and the top end 08 of the spar assembly 116 are inserted into the inclined surface 218 by using the screw inspection 224 The guide member 328 near the rear edge of the spar assembly 116 abuts on the cone 222 in each inclined surface 218, and is positioned correctly in the chordwise direction. The correct positioning of the bottom end 106 and the top end 108 of the spar assembly Π6 does not need to ensure that the other parts of the spar assembly 116 will be positioned in the chord direction of the positive disc. In step jig, in order to correctly position the entire spar assembly 116 toward the chord length direction, it is necessary to activate the leading edge pusher 230 to engage the cam surface 232 with the structural reinforcement point 136 on the spar assembly U6 and make the spar assembly After Π6, the membrane block 119 abuts on the rear membrane push pin 228. It can be understood that the rear diaphragm push pin 228 is located in the chord direction, and the contact between the rear diaphragm block 119 and the rear diaphragm push pin 228 ensures that the trailing edge of the spar assembly 116 is correctly fixed to the cone 121 defined by the core 114. Inside. When the spar assembly 110 is properly positioned, a cement (not shown) is applied over the core 114 and the spar assembly 116 to prepare to receive the lower wing skin 112. In step 520, the lower wing skin 112 is arranged above the core 114 and the spar assembly U6, and the trailing edge tool wing 130 of the lower wing skin 112 is positioned at the wing length together with the spring-loaded tool wing pin 240. In the chord length direction. At step 522, a fetal membrane plate 242 is arranged on the forbidden leaf sub-assembly 132 (see circle 6), and its role is to distribute the compressed diaphragm 254 and apply it to the kidneys of the prize sub-assembly 32 In step 524, the upper two-bag filter 244 is fitted to the belly of the fetus. Its role is to help exhaust air trapped between the membrane plate 242 and the flexible watertight diaphragm 254 during compression, and reduce the blades. Friction between the subassembly 132 and the flexible water-impermeable barrier 254. In step 526, the support structure 252 is turned to the second position and fixed at {Please read the precautions on the back before filling this page) ------- ^ --------- ^ J.- ----------------------

-24 - 經濟部中央標準居負工消費合作社印f 412451 β7 五、發明説明（1 ) --- 本發明大體上係有關製造裝置及彳法，肖別是有關組 裝直昇機主旋翼槳葉次組件之裝置及方法。 在航太工業中，將複合材料範圍擴大至各種不同結構 及動態之應用有逐漸增加的趨勢，複合材料的—個特殊用 途即為直昇機主旋翼槳葉之裝配。 西考斯基飛機公司已經展開了一項裝配直昇機主旋翼 槳葉之平行製造議定書，其中槳葉次組件與前緣覆套係以 單獨構件同時裝配，接著將預製的槳葉次組件與前緣覆套 組合在一起形成一個組裝好的主旋翼槳葉^組裝好的主旋 翼槳葉被放置在一個抓斗内，隨後在一高壓鍋内硬化而形 成一個完工主旋翼槳葉。 在一項習知技藝的主旋翼槳葉裝配過程中，平行製造 議疋書之槳葉次级件部分首先係將複合表皮與蜂窩芯子組 合，放置在一個其外形與槳葉上機翼相對應的塑膠套内， 並利用多個定位銷朝翼長方向及弦長方向相互定位。有一 根塗有黏著劑的鈦質翼梁與表皮和蜂窩芯子之組合物一起 相互定位，並安裝於蜂窩芯子的一個圓錐體之内。蜂窩芯 子接著被塗上黏著劑，並有一個第二複合表皮配置在蜂窩 芯子和一部份的翼梁上面，且同樣利用定位銷加以定位。 接著有二個其外形與槳葉下機翼相對應的塑膠蓋配置在第 二複合表皮上面，並利用多塊夾板與塑膠套一起咬合，而 使槳葉次組件受到一個緊壓力量。 主旋翼槳葉製造過程的第二個部分係將前緣覆套配置 在樂葉次組件外露的前緣上面。前緣覆套具有一個預製結 本紙張纽制t關家標準（CNS ) A4規格（2ί〇χ297公楚） 4 ---------ά------ΐτ-------^ (請先閲讀背面之注意事項再填寫本頁〕 經濟部中央標準局員工消費合作社印製 412457_B7 五、發明説明（2 ) ' 構，使覆套無法直接插在槳葉次組件上面，相反地，前緣 覆套之機尾邊緣必須攤開來讓前緣覆套能夠插在槳葉次組 件上面。習知技藝的覆套擴展工具包括有分段式角形不銹 鋼金屬板抓斗，與前緣覆套之機尾邊緣—起朝翼長方向配 置，並與其内模線（IML)表面（由複合材料製成）接觸。習 知技藝抓斗的每一個扇形部分各自由側凸輪驅動，藉以展 開前緣覆套之機尾邊緣。 將黏著剞塗在槳葉次組件前緣上面，接著將槳葉次組 件工具旋轉90〇,而使槳葉次組件之前緣面朝上，然後利 用多根螺桿將覆套擴展工具朝槳葉次组件方向往下拉’直 到覆套擴展工具和預定的工具止塊咬合為止。，，下拉，，過程 使覆套擴展工具在前緣覆套上面產生相當大的應力，金屬 板抓斗接著鬆開將前緣覆套之機尾邊緣，而使前緣覆套被 固定在槳葉次組件前緣上面β 上述過程中所用之槳葉次组件工具的一個明顯缺點在 於與塑膠套及塑膠蓋組合運作之多塊夹板無法提供充分的 緊麼作用給㈣次組件，具體地說，由於每塊失板值在其 不連續的翼長方向位置上提供最大的緊麼力量給樂葉次組 件，因此工具作用於槳葉次組件上面的緊壓力量並非均勻 地分佈在槳葉之翼長上面。對於此方法及槳葉次組件工具 的經驗顯示出夾板提供的緊壓作用在於—旦完成的槳葉從 禁葉次組件工具中移除，則紫葉必須在半小時的緊壓作用 之内置入抓斗及高壓鍋内，如此整個槳葉組件才不會鬆 脫》 --------i------，玎------^ ί - (請先聞讀背面之注意事項再填寫本頁)-24-Printed by Central Standard Responsible Workers and Consumer Cooperatives of the Ministry of Economic Affairs f 412451 β7 V. Description of the Invention (1) --- The present invention is generally related to manufacturing equipment and methods, and it is specifically related to the assembly of helicopter main rotor blade subassemblies Device and method. In the aerospace industry, there is a gradual increase in the application of composite materials to a variety of different structures and dynamic applications. One special application of composite materials is the assembly of helicopter main rotor blades. Sikorsky Aircraft Corporation has launched a parallel manufacturing protocol for the assembly of helicopter main rotor blades, in which the blade subassembly and the leading edge cover are assembled together as separate components, and then the prefabricated blade subassembly is assembled with the leading edge. The jackets are combined to form an assembled main rotor blade ^ The assembled main rotor blade is placed in a grab bucket and then hardened in a pressure cooker to form a completed main rotor blade. In the assembly process of the main rotor blade of a conventional technique, the secondary parts of the blade for parallel fabrication of the book are first combined with a composite skin and a honeycomb core, and placed in a shape whose shape is similar to the wings on the blade. Within the corresponding plastic sleeve, a plurality of positioning pins are used to position each other in the wing length direction and the chord length direction. An adhesive-coated titanium spar is positioned with each other with the combination of the skin and the honeycomb core, and is mounted in a cone of the honeycomb core. The honeycomb core is then coated with an adhesive, and a second composite skin is arranged on the honeycomb core and a part of the spar, and is also positioned using positioning pins. Next, two plastic covers whose shapes correspond to the lower wing of the blade are arranged on the second composite skin, and multiple splints are engaged with the plastic sleeve to subject the blade subassembly to a tight pressure. The second part of the main rotor blade manufacturing process is to place the leading edge cover over the exposed leading edge of the leaf subassembly. The leading edge cover has a pre-fabricated paper New Zealand standard (CNS) A4 specification (2ί〇χ297 公 楚) 4 --------- ά ------ ΐτ ---- --- ^ (Please read the precautions on the back before filling this page) Printed by the Consumer Cooperatives of the Central Standards Bureau of the Ministry of Economic Affairs 412457_B7 V. Description of the invention (2) 'structure, so that the cover cannot be directly inserted on the blade sub-assembly Conversely, the trailing edge of the leading edge cover must be spread out so that the leading edge cover can be inserted on the blade sub-assembly. The cover extension tool of the known art includes a segmented angle stainless steel metal plate grab. It is in contact with the trailing edge of the leading edge cover. It is arranged toward the wing length and contacts the inner mold line (IML) surface (made of composite material). Each sector of the conventional skill grab is driven by a side cam. Then, spread the leading edge of the trailing edge cover. Apply the adhesive coating on the leading edge of the blade subassembly, then rotate the blade subassembly tool 90 ° so that the leading edge of the blade subassembly faces up, and then use Multiple screws pull down the sheath expansion tool toward the blade subassembly until the sheath expands The tool and the predetermined tool stopper engage until the pull-down process causes the cover expansion tool to generate considerable stress on the leading edge cover. The metal plate grabber then releases the leading edge of the leading edge cover. And the leading edge cover is fixed on the leading edge of the blade subassembly. Β One of the obvious disadvantages of the blade subassembly tool used in the above process is that the multiple splints operating in combination with the plastic cover and plastic cover cannot provide sufficient tightness. Acts on the sub-assembly, specifically, because each lost plate value provides the maximum tight force to the Leye sub-assembly in its discontinuous wing length direction, the tool acts on the tight pressure on the blade sub-assembly The amount is not evenly distributed over the blade wing length. Experience with this method and blade subassembly tools shows that the compression provided by the splint is that once the completed blade is removed from the forbidden blade subassembly tool, then The purple leaf must be built into the grab bucket and pressure cooker within half an hour of compression, so that the entire paddle assembly will not come loose "-------- i ------, 玎 --- --- ^ ί-(Please read the back Precautions to fill out this page)

本紙張尺度適财關CNS (2】0χ 297公釐） 5 412457 A7 --- --B7 五、發明説明（3 ) ---- 除了槳葉次組件之翼長方向上的緊壓作用不足之外， 上述習知技藝的槳葉次組件工具亦無法提供充分的弦長方 向緊壓作用給槳葉次組件。由於槳葉次組件工具於覆套擴 展工具運轉時維持在槳葉次組件周圍的適當位置上，槳葉 -人組件工具無法完全地延伸至槳葉次組件的前緣，因此， 靠近槳葉次組件之上下機翼表皮部分並未受到直接的緊壓 作用，因而不會充分地固定在翼梁上。這種不完全緊壓的 一個缺點在於當將前緣覆套配置在槳葉次組件之前緣上面 時’若有任何一塊複合表皮與翼梁分離的話則前緣覆套 的其中一塊或兩塊機尾邊緣會滑入複合表皮下方，而在前 緣覆套與槳葉次組件之間產生一個不正常交界面，而使組 裝好的槳葉變成不良品。 上述平行議定書中的另一個重要領域為用以組合前緣 覆套與槳葉次組件的覆套擴展工具β習知技藝中的抓斗於 將前緣覆套之機尾邊緣展開時對前緣覆套之IML表面產 生一個剪力作用，習知技藝抓斗所產生的這種剪力作用會 導致前緣覆套之複合材料破裂或分層，造成元件成為不良 品而必須再加工。此外，習知技藝抓斗的運轉在於使抓斗 能夠污損無瑕疫的前緣覆套接合面，同時，抓斗之扇形部 分各自以連績方式運轉，而使複合式重複運轉必須將整個 前緣覆套展開。這種方法不僅費力、耗時、以及浪費，且 這種方法會使前緣覆套之機尾邊緣内產生多餘的應力。 另一種製造主旋翼槳葉之方法發表於美國專利第 5,528,828號之”製造直昇機主旋翼槳葉之方法”與第 本紙張尺度適用中國國—家樣隼（CNS ) Α4規格（210Χ 297公釐） Γ Λ _ {請先閱讀背面之注意事項再填寫本頁 —裝. ，1Τ 經濟部中央標準局員工消費合作社印12 經满部中央標準局員工消費合作社印发 412457 A7 _________ B7 五、發明説明（4 ) ~ 5,570,63i號之，，製造直昇機主旋翼樂葉之裝置，，，兩者均 讓渡給聯合科技公司（下文中分別稱為，，，828專利，，及，,，63】 專利”）。如第i及2圖中所示，，828專利及631，專利中 發表之裝置包括有-個用以組裝及壓緊一禁葉次組件24 之緊壓央具ίο、以及-個於緊壓過程中將一前緣覆套22 展開並插在紫葉次組件24 i面之覆套擴展/插入裝置5〇, 其中禁葉次組件24包括有一塊上機翼表皮12、一塊下機 翼表皮18、一個型芯14、以及一個翼梁組件16。 緊壓夾具10包括有一個下組件26，下組件具有一個 仿形上機翼套28，與一支撐結構3〇安裝在一起；以及一 個上組件32，上組件具有一個壓力袋34，密接於一仿形 支承板36，支承板與一結構支撐桁架38固定在一起。仿 形上機翼套28具有多個刀具銷31，用以定位上機翼表皮 12使其在仿形上機翼套28上面排成一列；以及多個後膜 推銷39，使翼梁組件在仿形上機翼套28内呈弦長方 向排列。固疋於支撐街架38上的翼梁支柱4〇使翼梁組件 16於仿形上機翼套28中呈翼長方向排列。將上下組件Η、 26固定在一起，則壓力袋34被加壓而緊壓著组裝好的槳 葉次組件構件〗2、14、16、18。 覆套擴展/插入裝置50包括有一根活動支柱52、與 活動支柱安裝在一起、並可與其同時移動之上下延長拢架 構件54、56以及數排與牦架構件安裝在一起之吸盤58、 60。有兩個氣壓缸61、62被插在支柱52與各拢架構件54、 56之間，將氣壓缸61、62加壓可使上下牦架構件54 56 本紙張尺度適用中國國家標準（CNS ) A4規格（210X 297公楚） . „裝------訂------威 (請先閱讀背面之注意事項再填寫本頁) 412457 A7 B7 經满部中央標準局貝工消费合作社印^ 五、發明説明（5 ) 在其中前緣覆套22可插入上下排吸盤58、60之間的一個 分離位置之間同步移動，該位置係於其緊壓期間，吸盤以 對接方式和前緣覆套22之各個外模線（〇ml)表面咬合的 一個咬合位置，且為將前緣覆套22展開以插在槳葉次蚯 件24上面的一個運轉位置。有一個真空源64以氣動方式 接至吸盤58、60而在咬合位置上產生吸力，使吸盤58、 6〇與前緣覆套22之各個外模線（〇ML)表面咬合，而使上 下托架構件54、56隨後同步移動至運轉位置而使前緣覆 套22展開。活動支柱52的移動使展開的前緣覆套22於 緊壓期間被配置在槳葉次組件24上面。 關於稍早敘述之槳葉次组件工具，，828專利及63Γ 專利中發表之方法及裝置的一個缺點為緊壓夾具1〇在翼 梁組件16與靠近槳葉次組件24前緣42的部分複合表皮 12、18之間並不提供足夠的緊壓作用。如第2圖中所示， 由於活動支柱52於緊壓期間將前緣覆套22配置在槳葉次 組件24上面，因此槳葉次組件24前緣必須有足夠的餘隙 實際上讓活動支柱52能夠水平地移動至適當位置。因此， 壓力袋34並不完全覆蓋槳葉次組件24之前緣，因而上下 機翼複合表皮12、18無法正確地緊壓於該區域内之翼梁 组件16上面，於是吾人發現到，這些又稱為”接榫”之複 合表皮前緣12、18可能會有將此前緣區域内之翼梁組件 16拱起的一個傾向。這些，，接榫”每個均界定了一個”踏 板”，使前緣覆套22必須將對應的複合表皮12、18重疊 在其上面，使其在前緣覆套22與槳葉次組件24之間具有 本紙張X度適用中國國家標準（CNS ) Μ規格（2〗0x297公釐） [~ —^衣 i I I I、1τ--I - I —-^ r - (請先閲讀背面之注意事碩再填寫本頁；} 结濟部中央榡率局貝工消費合作社印聚 412457 A7 —一__B7_ 五、發明説明（6) 一個適當的交界面。萬一接榫將翼梁組件16拱起時，前 緣覆套22可於安裝期間在接榫下方滑動，而在前緣覆套 22與槳葉次組件24之間形成一個不適當且無法令人接受 之交界面。 此外，設計’828專利及’631專利中發表之覆套擴展〆 插入裝置50的諸項缺點更增加了安裝期間前緣覆套22與 槳葉次組件24之間形成一個不適當交界面的可能性，具 體而言，當前緣覆套22被定位在諸排吸盤58、60之間， 且上下拢架構件54、56處於運轉位置時，則前緣覆套22 之重量產生一個向下力量而作用在下排吸盤6〇上面以及 下杻架構件56上面。吾人已經發現，此作用於下牦架構 件56上之向下力量並未由作用於下氣壓缸62上之壓力充 分地抵消，因此下托架構件56在前緣覆套22重董作用下 會有下陷的傾向。此外，由於吸盤58、6〇係由橡膠風箱 構成，則緣覆套22之重量亦會使下排吸盤6〇内之風箱陷 落，並拉長上排吸盤58内之風箱。作用於托架構件56上 之向下力量以及下排吸盤60陷落的傾向導致前緣覆套22, 之機尾邊緣向下弩曲，而使前緣覆套22與槳葉次組件24 之間發生脫位。此脫位特徵使支柱52水平移動且當前緣 覆套22接近槳葉次組件24前緣時，前緣覆套22之弯曲 會導致刖緣覆套22之上機尾邊緣卡在下機翼複合表皮a 上的接榫下方，而形成一個不當交界面。 加劇此問題的事實在於當支柱52位於緊壓夾具1〇近 側時，緊壓夾具10與覆套擴展/插入裝置5〇封閉了前緣 本紙張尺度適用中國國家標準（CNS ) Α4規格（210X297公釐） 9 ' ά------1Τ------滅 -- (請先閏讀背面之注意事項再填寫本頁) 五、 412457 A7 B7 發明説明（7 經滴部中央標率局員工消費合作社印¾ 覆套22之機尾邊緣，並使操作者非常難以從外觀上辨識 出前緣覆套22之機尾邊緣是否在正確的安裝位置上。在 致力於彌補前緣覆套22之機尾邊緣的定位不確定性時， 前緣覆套22之機尾邊緣可以張地更開（大於每邊127 cm(〇.5 in)的一個較佳位移），而使其中一個機尾邊緣較不 可能卡在其中一個接榫下方。然而，將每邊的機尾邊緣展 開超過1.27 cm(0.5 in)時的一個缺點在於前緣覆套22内 之複合材料及加熱底板受到這種過度展開而產生的應力時 可能更容易受到損壞而必須再加工。 因此本發明的一個目的在於提供一種組裝直昇機主旋 翼槳葉次組件之裝置及方法’其提供了槳葉次組件完整的 弦長及翼長方向之緊壓作用。 本發明另一個目的在提供一種組裝直昇機主旋翼槳葉 次組件之裝置及方法，其能使作用在直昇機主旋翼槳葉次 組件上的應力減至最小。 本發明另一個目的在提供一種組裝直昇機主旋翼槳葉 欠組件之裝置及方法，#能減少升高'運輸以及精確定位 禁葉次組件構件所須之人工程度。 這些及其他目的於本發明中可藉由組裝直昇機主旋翼 ㈣次組件的—個裝置來達成，職葉次組件包括有-塊 機翼表皮、個型4、一塊上機翼表皮、以及一個具有 -頂端和-底端之翼梁組件，該翼梁組件包括有一個下组 其具有一個含一仿形上機翼套之底座，而仿形上機翼 具有個底端和-個頂端、配置在仿形上機翼套近侧的 本紙張錢剌 ----------裝— (讀先閱讀背面之注意事項再填寫本頁〕 訂------喊------- ml r . · 經濟部中央標準局負工消費合作社印製 412457 A7 __B7 五、發明説明（8 ) 第一及第二導軌面，其中第一導軌面係配置在底端近側， 而第二導軌面配置在頂端近側，並具有多個配置在仿形上 機翼特近側之前緣推輪。 有一個上組件用以和下組件匹配，並包括有一個支標 結構和一個由支撐結構支撐的撓性不透水隔膜其中撓性 不透水隔膜與仿形上機翼套於上組件與下組件咬合時在其 間界定了一個模穴。 前述諸目的於本發明中更可藉由裝配直昇機槳葉次組 件的一個方法來達成，該槳葉次組件包括有_塊下機翼表 皮、一個具有一圓錐體於其内形成之型芯、一塊上機翼表 皮、以及一個具有一頂端和一底端之翼梁組件。 該方法步驟包括提供一個具有一用以和一上組件匹配 之下組件的槳葉緊壓裝置。下組件具有一個含—仿形上機 翼套之底座，包括有一個底端和一個頂端、至少兩個配置 在仿形上機翼套近側之導軌面其中導軌面於其内界定了 圓雜體，且其中至少其中一個導軌面係8己置在底端近側， 而至少其中一個導軌面配置在頂端近侧，並具有多個配置 在仿形上機翼套近側之前緣推輪。 上組件包括有一個用以支撐一撓性不透水隔膜之支撐 結構，其令撓性不透水隔膜與仿形上機翼套於上組件與下 組件咬合時在其間界定了一個模穴。 該方法步驟更包括將上機翼表皮和型芯與仿形上機翼 特配置在一起、將一頂端支撐襯墊與翼梁頂端接在—起、 將一底端支撐襯墊與翼梁底端接在一起，其中頂端支撐襯 --------、▲------1T------^ {請先閱讀背面之注意事項再填寫本頁) 經滴部中央標準局員工消贫合作社印奴 412451 A7 ______· _ B7 五、發明説明（9 ) <整1與底端支推概塾每個均具有和導軌面一起使用之導面及 導件^接著將至少其中一個導面與至少其中一個導軌面對 接，^(¼翼梁組件朝翼長方向配置在仿形上機翼套内。藉 由將導件插入導軌面中的圓錐體以及利用前緣推輪將翼梁 組件插入型芯中的圓錐體内，將翼梁組件朝弦長方向配置 在仿形上機翼套内β接著將下機翼表皮與型芯及翼梁組件 配置在一起而形成直昇機槳葉次組件，並接著使上下組件 咬合。模穴中的空氣接著被排出，空氣之排出導致撓性不 透水隔膜對直昇機槳葉次組件施以緊壓力量。 從下列詳細敘述中，本發明之其他目的及優點對於那 些熟悉此技術的人將會變的更明顯，其中僅由例示出完成 本發明所考慮之最佳模式，而繪示並敘述了本發明之較佳 實施例。必須了解的是，本發明能夠作各方面之修正均 不會偏離本發明》因此，諸幅附圖及敘述僅作為例示用而 非加以限制。 第1圖為習知技藝緊壓夾具及覆套擴展/插入裝置的 一個透視圖； 第2圖為第1圖之習知技藝裝置的一個部分平面圖； 第3Α圖為一 Η-60直昇機之示範主旋翼槳葉的一個 頂視圖； 第3Β圖為第3Α圖之主旋翼槳葉沿線段3Β_3β所取 的一個橫截面圖； 第3C圖為例示於第3Β圖之前緣覆套的一個放大部 分透視圖； 本紙浃A度適用中國國家樣準（CNS ) A4規格（210X297公釐） 12 I ^ ~. -1τ------- - - (請先閲讀背面之注意事項再填寫本頁} 412457 A7 B7 經濟部中央標準局貝工消貧合作社印裝 五、發明説明（10 第3D圖為用於第3A圖之示範主旋翼槳葉之翼梁組 件的一個放大部分透視圖； 第4圊為具體表現出本發明特色之槳葉緊壓裝置的一 個透視圖； 第5圖為第4圖之槳葉緊壓裝置沿線段5-5所取的一 個部分橫載面圖，包括了第3B圖之主旋翼槳葉橫載面圊； 第ό圖為第4圖之槳葉緊壓裝置沿線段6_6所取的一 個橫截面圊，包括了第3Β圖之主旋翼槳葉橫截面圓，並 描繪了上組件與下組件之咬合； 第7圖為具體表現出本發明特色之支撐裝置的一個平 面圖，該裝置係用以支撐第3D圖之翼梁組件； 第8圖為第7圖之翼梁組件及支撑襯塾的一個部分斷 面平面圖； 第9圖具體表現出本發明特色之前緣覆套安裝裝置的 一個平面圖； 第10圖為描繪了第9囷之前緣覆套安裝裝置的氣壓 缸、吸盤、導管、真空幫浦、以及真空蓄壓器互相連接的 一個圓形； 第11圖為第9圖之前緣覆套安裝裝置的一個平面圖， 其描繪了槳葉次組件之前緣正被插入前緣覆套中； 第12圖為例示了一種製造能夠具體表面出本發明色 之槳葉次组件方法的一個流程圊；以及 第13圖為例示了一種將前緣覆套安裝於槳葉次組件 上面，並能夠具體表現出本發明特色之方法的一個流程 表紙張尺度適用中國國家標準（CM ) Α4規格（210Χ 297公釐 ---------—裝------訂------裱 (請先閲讀背面之注意事項再填寫本頁) 13 經濟部中央標準局負工消費合作社印掣 41245Ϊ A7 ---------- B7 五、發明説明（n )， 圖〇 完成本發明之最佳模式 下文中進一步詳述之裝置及方法包括有用於西考斯基 飛機公司所製造的H-60直昇機之主旋翼槳葉裝配的部分 製造協定，然而應該了解的是，此處所述之裝置及方法適 用於一般主旋翼槳葉之裝配。 主旋翼槳葉 第3A-3D圖中示範性地例示了一片h-60主旋翼樂葉 MO’包括有一個前緣102和一個後緣1〇4，兩者共同界 疋了旋翼槳葉100的弦，並有一個底端和一個頂端 108,兩者共同界定了旋翼槳葉100的翼長（主旋翼槳葉1〇〇 的一個頂蓋109係分開裝配，以連接至主旋翼槳葉ι〇〇的 頂端108)。主旋翼槳葉1〇〇包括有分別界定槳葉1〇〇之 上下空氣動力表面的上下機翼表皮110、丨12、一個型芯 Π4、一個翼梁組件116以及一個前緣覆套120 ^上下機 翼表皮110、112、型芯114以及翼梁組件116共同界定 了一個槳葉次組件132 » 在所述實施例中，上下機翼表皮110、112係由好幾 層習知技藝中著名的預浸膠體複合材料、例如内嵌於適當 樹脂填料的編織玻璃纖維，所形成的預製構件。有多個對 應的後緣工具翼片130從上下機翼表皮110、112之後緣 延伸，而每個後緣工具翼片130内形成有一個開口 131。 下文將更徹底討論到，在槳葉組裝過程中，後緣工具翼片 130有助於上下機翼表皮110、112之正確翼長方向及弦 本紙張尺度適用中國國家標準（CNS ) A4規格（210X297公釐） 14 ^ 1裝------訂------成 (诗先閱讀背面之注^一^^項再填寫本頁} ^濟部中央榡準局員工消贽合作.社印製 A7 ______B7 五、發明説明（12 ) 長方向定位。 在所述實施例中，型芯Π4係由一種常用於航太用途 之蜂巢狀材料構成，例如nomexr(nomexr係美國德 拉威州維明頓市東印度杜邦公司之aramid纖維或織品的 註冊商標），並作為上下機翼表皮11〇、112之間的一個低 重量、結構強化構件。型芯114之前緣界定了一個圓雜體 121，用以和翼梁組件116之後緣咬合。上機翼表皮11〇、 下機翼表皮112以及型芯114具有多個定位開口 134穿過 該處而形成，以促進翼梁組件116在一槳葉緊壓裝置2〇〇 中的定位，下文將進一步詳細敘述。當主旋翼槳葉10〇已 經裝配完成之後，將諸定位開口 134用複合材料修補，使 上機翼表皮110及下機翼表皮112具有空氣動力上平滑表 面。翼梁組件116包括有一個翼梁117、一個或多個配重 118、以及後膜塊Π9。翼梁117係作為主旋翼槳葉1〇〇 的主要結構件，於直昇機運轉其間承受主旋翼1〇〇内產生 的扭力、彎力、剪力以及離心力等動態負荷。所述實施例 之翼梁117係由鈦製成，然而在其他實施例中翼梁ι17 可由其他金屬製成，或許由複合材料或其等搭配而成β 配重Π 8係用以靜態及動態地平衡主旋翼槳葉ι〇〇。 在所述實施例中，配重118分別由密度較低至密度較高的 材料製成，例如泡珠、鎢、以及錯，配置在底端1 〇6至頂 端108的翼長方向上，並提供了用以平衡主旋翼槳葉ι〇〇 之靜態及動態平衡所需的重量分配。所製造的配重118包 括有結構加固點136，其提供了配重118與前緣覆套120 本紙張尺度適财關家縣（CNS ) Α4祕⑺ϋχ297公趁） 15 -裝------訂------寐 (請先閲讀背面之注意Ϋ項再填寫本頁) 經濟部中央標準局負工消費合作社印聚 41245? A7 ______ B7 五、發明説明（13 ) ^ 内模線（IML)表面之間的實際咬合。配重11 §係以黏著方 式接於翼梁117之前緣上，使接合的配重n8被插入前緣 覆套120與翼梁117的前緣之間。 後膜塊119係以黏著方式接於翼梁117之後緣上對應 於上機翼表皮110及型芯114内之定位開口 134的不連續 位置處。藉由定位開口 134，後膜塊119有助於翼梁組件 116在槳葉緊壓裝置200内的定位，下文將進—步詳述之。 在所述實施例中，第3C圖中將更詳細例示之前緣覆 套120係由複合材料及抗磨材料製成的一個預製混合構 件。覆套120具有一個U形構造，其界定了主旋翼槳葉ι〇〇 之前緣102。覆套120具有一層或更多層122的預浸膠體 複合材料、例如内嵌於適當樹脂填料的編織玻璃纖維，並 界定了前緣覆套120之内模線（IML)、一個第一耐磨板條 124以及一個第二耐磨板條126。前緣覆套12〇提供了主 旋翼槳葉100之前緣102的抗磨保護、控制主旋翼槳葉ι〇〇 之機翼公差、並容納主旋翼槳葉去冰器組件（未示出）。 下文將更詳細地討論主旋翼槳葉1〇〇之製造方法，該 方法使用了槳葉緊壓裝置200、一個支撐裝置300以及一 個前緣覆套安裝裝置400。 槳葉緊壓裝置 參看第4圖，槳葉緊壓裝置200具有一個下組件2〇2, 用以和一上組件250咬合。下組件202包括有一個底座 206,其具有一個仿形上機翼套2〇8，其中仿形上機翼套2〇8 係用以和槳葉次組件132之上機翼的外形咬合，並具有一 本紙張尺度適用中國國家標率（CNS ) Α4規格（210Χ 297公釐） 16 ' ------,π------- ^ (請先閱讀背面之注意事項再填寫本頁} 經濟部中央標準局負工消費合作社印^ A7 _____B7 五、發明説明（14 ) ~ 個和槳葉次組件132之底端106相對應的内侧端21〇，以 及一個和槳葉次組件132之頂端108相對應的外側端 212。有兩個導軌面214、216配置在仿形上機翼套208之 近側，而使導執面214位於仿形上機翼套208之内側端21 〇 的近側，而導軌面216位於仿形上機翼套208之外側端212 的近側*每個導軌面214、216内均具有一個斜面218， 終止於一圓錐體222處。此外，有一根螺栓224與各個導 軌面214、216搭配，而使螺栓224之轉動能夠帶動螺栓 224朝圓錐體222方向而在斜面218上移動。 有三個後膜推銷凹座226在仿形上機翼套208内與槳 葉次組件132内之定位開口 134相對應的翼長及弦長方向 位置處形成，如第5圖中所示，有三個後膜推銷228與與 定位開口 134及後膜推銷凹座226 —起運作，使後膜推銷 228於槳葉次組件132製造時能夠用在各種不同用途上， 下文將更詳細敘述之。此外，有三個前緣推輪23〇，每個 均具有一凸輪面232,並配置在仿形上機翼套2〇8之前緣 近側，使每個前緣推輪230被配置在與後膜推銷凹座226 相對應的一個翼長方向位置處。前緣推輪230係以習知技 藝中建構凸輪的一個傳統方式建構，使前緣推輪230之運 轉促使凸輪面232朝後膜推銷228的一個弦長方向推進。 參看第4及6圖，有一個真空源234與底座206配置 在一起，並具有多條導管236從該處延伸，其中每條導管 236均終止於底座206内的一個對應開口 238處。在所述 實施例中，真空源234包括有一具傳統真空泵，而開口 238 本纸張尺度適用中國國家標準（CNS ) Α4規格（210X297公釐） 17 ——I-.---- έ------IT------Μ (請先閱讀背面之注意事項再填寫本頁) 經部中央標準局貝工消費合作祍印製 4124^ A： ----一__B7 五、發明説明（丨5 ) 1 排成兩列，一列位於仿形上機翼套208之前緣近侧，一列 位於仿形上機翼套208之後緣近侧。此外，有五個彈簧加 載式工具翼片插銷240排成一列配置在仿形上機翼套208 之後緣近側與槳葉次組件132後緣工具翼片130内之開口 131相對應的弦長及翼長方向位置處。 參看第4及6圖，上組件250包括有一個支撐結構 252,用以支撐一個撓性不透水隔膜254。在所述實施例 中，支撐結構252係利用多個樞軸256而接在底座206上， 使支撐結構252能夠從撓性不透水隔膜254未蓋住仿形上 機翼套208的第一位置轉動至撓性不透水隔膜254蓋住仿 形上機翼套208的第二位置《支撐結構252、撓性不透水 隔膜254、仿形上機翼套208以及底座206係建構在一起， 使當支撐結構252位於第二位置時撓性不透水隔膜254能 夠蓋住仿形上機翼套208，而在支撐結構252與底座206 之間形成一個不透氣密封。此外，當支撐結構252位於第 二位置時，撓性不透水隔膜254與仿形上機翼套208在其 之間界定了一個模穴258。在所述實施例中，底座206中 的開口 238係建構成當真空源234啟動時，真空源234將 模穴258内之空氣排出，以將撓性不透水隔膜254拉向仿 形上機翼套208。 支撐裝置 參看第3A-D、4及7圖，支撐裝置300於槳葉次組 件裝配期間和槳葉緊壓裝置200 —起使用，支撐装置300 包括有一個底端支撐襯墊302，用以接至翼梁117之底端 本紙張尺度適用申囡國家標準（CN£; ) Α4規格（210X297公釐） 18 1裝------訂-------^ (請先閱讀背面之注意事項再填寫本頁) 經濟部中央標率局員工消費合作社印繁 412457 A7 __B7 五、發明説明（l6 ) 106; —個頂端支撐襯墊304，用以接至117之頂端108; 一個底端變速箱308，接至底端支撑襯墊302;以及一個 起重裝置338，用以支撐底端及頂端變速箱308、306。關 於第8圖繪示之實施例，底端支撐襯墊302包括有一個底 座310，該底座具有一對從該處延伸之構件312、314，用 以插入翼梁117之底端106内。其中一個構件312具有兩 個從該處延伸之彈簧加載式叉子316，與翼梁117内的一 對相對應開口 117A —起使用，並將底端支擇襯塾302與 翼梁117固定在一起。頂端支撐襯墊304具有數個角形凸 緣320，插入翼梁117之頂端1〇8内，且其内具有多個與 翼梁117頂端108内之諸開口相對應的開口 322，供將頂 蓋109固定至槳葉次組件132。有多根螺栓324與開口 322 一起使用，供將頂端支撐襯墊304定位並固定在翼梁π? 上。 參看第6及8圖，每個支撐概墊302、304更包括有 兩個從該處朝翼長方向延伸、而終止於一變速箱固定板 329處之導件326、328，該固定板有助於將支撐襯墊3〇2、 304接至其各自的變速箱308、306上。在所述實施例令， 靠近翼梁組件116後緣之導件328係圓柱形輥子，用以和 導軌面214、216内之斜面218咬合》此外，每個變速箱 固定板329包括有一個導面330，位於導件326、328近 側之固定板329侧上面。下文t將更詳細討論到，導件 326、328及導面330係與導軌面214、216 —起使用，以 在槳葉次組件132製造其間將翼梁組件116適當地定位。 本紙張尺度適用中國國家標準（CNS ) A4現格（210X297公董） 19 --------^袭------"------^ (請先閱讀背面之注意事項再填寫本頁) 經濟部中央標準局員工消費合作社印^ f 41245? A7 ______B7 五、發明説明（1? ) ^ 參看第7及8圖，頂端變速箱306及底端變速箱3〇8 每個均配置了傳統的傳動裝置，使每個變速箱306、308 能夠使翼梁組件116朝大體上垂直之方向平移亦能夠使 翼梁組件116繞著其縱軸丨23旋轉《在所述實施例中，變 速箱306、308具有可旋轉曲柄334、336，供以手動方式 朝垂直及旋轉方向、或其中任一方向推動翼梁組件116。 在其他實施例中，電動馬達可以和變速箱3〇6、3〇8 一起 使用，使翼梁組件116產生垂直及旋轉運動、或其中任一 種運動。 起重裝置338包括有一個傳統橋式起重機，如習知技 藝中用以吊起製造環境中之材料的起重機。在所述實施例 中，起重裝置338包括有起重索，接至每個變速箱3〇6、 308，而起重裝置338能夠朝垂直及水平方向或其中任 何一方向移動變速箱306、308。 前緣覆套安裝裝置 參看第9、10及II圖，前緣覆套安裝裝置4〇〇包括 有一個下組件402，其係接至一上組件45〇。 下組件402包括有一個底座4〇4，其具有多個接至該 處且排在對置列之氣壓缸406 ^每個氣壓缸4〇6具有一個 平移構件408，其受到加壓空氣組41〇提供給氣壓缸4〇6 的加壓空氣時能夠作平移運動。平移構件4〇8係接於對置 的拢架構件412上，其中牦架構件412係用以支撐多個吸 盤414。氣壓缸紙按架構件412以及吸盤414係配置 成使對置列的吸盤414在受到加壓空氣組41〇之加壓空 本紙張尺度適用中國國家標準（CNS ) A4規格（2^297公楚）_— I '-裝 . I —* --訂—— __ I--喊 (請先閱讀背面之注意事項再填寫本頁) 20 經潢部中央標準局貝工消費合作社印聚 412457 A7 ---—..._____B7 五、發明説明（18 ) ^ --- 作用時能夠同步移動。 在所述實施例中，了組件402 包括有四個真空泵 416,接至四個真空蓄壓器418，其中真空蓄壓器418係 透過多條對應的導管422而接至多個吸盤414。真空泵416 及真空蓄壓器418 —起提供吸力給多個吸盤414。在所述 實施例中，諸吸盤414及其對應的導管422被分成四條線 路，其中母條線路係接至其中一個真空蓄壓器4丨8。有多 個閥門424與諸條導管422 —起搭配，其作用在於調節吸 盤414之真空壓力。真空蓄歷器418係一項傳統設計，設 計成具有一個預定的儲存量，以迅速提供每個吸盤414介 於大約 67.73 kPa 與 84.66 kPa(20 in.Hg 與 25 in.Hg)之間 的真空壓力。有一個前緣覆套仿形套42〇被插在對置列的 吸盤414之間，並用以支撐前緣覆套12〇 β在其他實施例 中’真空泵416、真空蓄壓器418以及線路之數目可以和 那些實施例中所述者不同，以滿足那些實施例之操作需 求。 上技件450包括有五根支柱452，大體上從底座404 垂直延伸、並朝翼長方向定位在與槳葉次組件132之後緣 工具翼片130位置相對應的位置處。每根支柱452具有一 塊仿形夾板454接至該處，其中每塊仿形夾板454具有一 個圍道曲面456、一個绞接固定構件458、以及一個工具 翼片插銷460 β圍道曲面456及鉸接固定構件458係將槳 葉次組件132夾在其間，而工具翼片插銷460與槳葉次組 件132工具翼片130 —起正確地定位槳葉次組件Π2。在 本紙乐尺度適用中國國家標準（C’NS } A4規格（210X 297公釐） 21 — I— H ϋ 1 丨 ϋ n I 丨-^, - · (請先閱讀背面之注意事項再填寫本頁) 經濟、邓中央標準局貝工消費合作社印聚 41245? A7 —________B7 五、發明説明（19 ) 所述實施例中，每塊仿形夾板454能夠提供一個開放结 構，使鉸接固疋構件458能夠定位於圍道曲面456遠側， 並提供一個封閉結構，使较接固定構件458能夠定位於圍 道曲面456近側，並用以固定槳葉次組件η:。此外，上 組件450亦包括有三個後膜推銷凹座451，於圍道曲面456 及橋接構件（未不出）兩者、或其中任何一方内形成，該橋 接構件係於相鄰的仿形夾板454之間延伸，並定位在與槳 葉-人組件132内之定位開口 134相對應的翼長及弦長位置 處。 仿开々爽板454係接至支柱452，而使仿形夹板454能 夠相對於前緣覆套仿形套420作平移運動。在所述實施例 中，有一個回轉輪462及差速器464以傳統傳動方式配置， 並以機械方式聯結至仿形夾板454，供以手動方式將仿形 夾板454對仿形套420作平移運動。在其他實施例中平 移運動可利用電動馬達及液壓系統兩者或其中任何一方 完成。 槳葉次組件裝配方法 參看第3A-D及4-8圖中例示之槳葉次组件】32、藥 葉緊壓裝置200以及支撐裝置300，並參看第12圖之流 程圖，現在將更詳細討論槳葉次組件132之裝配方法MF。 於步驟500中，上機翼表皮11〇及型芯1U係配置在 上機翼套208上面。在所述實施例中，上機翼表皮110及 型芯114於配置在上機翼套208之前係以黏著方式接在一 起，以減少裝配時間*於步驟502中，上機翼表皮n〇與 本紙張尺度適用中規格（21〇Χ職釐） 22 J iT------ ^ - 銲 (請先閲讀背面之注意事項再填寫本頁) 五、 發明説明（2〇 ) Α7 Β7 _濟部中央標準局貝工消费合作社印 型芯114之組合物係利用後緣工具翼片13〇内之開口 ι31 配置在彈簧加載式工具翼片插銷24〇周圍之方式而朝翼長 及弦長方向配置在上機翼套208上面。此外，後膜推銷228 穿過型芯114内之定位開口 134及上機翼表皮11〇，並穿 入後膜推銷凹座226内。 在所述實施例中，一種習知技藝中供以黏著方式將槳 葉翼梁接至表皮/型芯組合物之著名接合劑於進行步驟504 之前塗在翼梁組件116上面。於步驟504中，底端支撐襯 墊302被接至翼梁117底端106，而頂端支撐襯墊3〇4被 接至翼梁117頂端1〇8。於步驟506及508中，底端支撐 襯墊302被接至底端變速箱308，而頂端支撐襯墊3〇4被 接至頂端變速箱306，兩個變速箱306、308接著依序接 至起重索340，使翼梁組件116由起重裝置338支撲著。 於步驟510中，翼梁組件116被起重裝置338吊起並 加以定位，使底端支撐襯墊302位於仿形上機翼套208之 内侧端210上面的導軌面214近侧，並使頂端支撐襯墊3〇4 位於仿形上機翼套208之外側端212上面的導軌面216近 側。於步驟512中，底端支撐襯墊302與頂端支撐襯墊3〇4 兩者之導件326、328與導軌面214、216中的斜面218咬 合。接著藉由將導面330對接在緊靠仿形上機翼套2〇8外 側端212上之導軌面216的頂端支撐襯墊304上面而將翼 梁組件116朝翼長方向定位》於步驟514中，底端變速箱 308脫離底端支撐襯墊302，而頂端變速箱306脫離頂端 支撐襯墊304。 ---------^-- (請先閱讀背面之注意事項再填寫本頁) •丨踩— I f. * .I ml 本紙乐尺度適用中國國家標準（CNS ) A4規格（2!0x297公釐） 23 經濟部智慧財產局員工消費合作社印製 412i57 五、發明說明（21 ) 於步驟516中，翼梁組件116之底端ι06及頂端ι〇8 係利用螺检224將導件326、328插入斜面218内直到翼 梁組件116後緣近側之導件328與各斜面218中的圓錐體 222對接為止，而朝弦長方向正確地加以定位。翼梁組件 Π6底端106及頂端108之正確定位並不需保證翼梁組件 116其他部分會有正碟的弦長方向定位。於步驟jig中， 欲朝弦長方向正確地定位整個翼梁組件116，則需啟動前 緣推輪230，使凸輪面232與翼梁組件U6上的結構加固 點136咬合，並使翼梁組件Π6之後膜塊119緊靠著後膜 推銷228。可以了解的是，後膜推銷228位於弦長方向， 而使後膜塊119與後膜推銷228之間的接觸確保翼梁組件 116後緣正確地固定在型芯114所界定的圓錐體121之 内。當翼梁組件110正確定位之後，將接合劑（未示出）塗 在型芯114與翼梁組件116上面，以準備承接下機翼表皮 112。 於步驟520中，下機翼表皮112被配置在型芯114與 翼梁组件U6上面，並利用下機翼表皮112之後緣工具翼 月130與彈簧加載式工具翼片插銷240 一起定位在翼長及 弦長方向上。於步驟522卡，有一塊胎膜板242被配置在 禁葉次組件132上面（見第6圓），其作用在於分配在緊壓 悻不透水隔膜254施用至獎蕾次組件丨32的腎懕 於步驟524中上二袋式過濾器244係被配詈在胎腹柘 其作用在於幫助排出於緊壓期間滯 留在胎膜板242與撓性不透水隔膜254之間的空氣，並減 少槳葉次組件132與撓性不透水隔琪254之間的摩擦。 於步驟526中，支撐結構252轉至第二位置並固定在 {請先閱讀背面之注意事項再填寫本頁) -------^---------^ J. -----------------------The paper size is suitable for financial management CNS (2) 0χ 297 mm 5 412457 A7 ----B7 V. Description of the invention (3) ---- Except for the pressing effect of the blade sub-component in the direction of the wing length is insufficient In addition, the blade sub-assembly tool of the above-mentioned conventional technique cannot provide sufficient compression in the chord length direction to the blade sub-assembly. Since the blade sub-assembly tool is maintained in a proper position around the blade sub-assembly while the sheath expansion tool is running, the blade-human assembly tool cannot fully extend to the leading edge of the blade sub-assembly, so it is close to the blade sub-assembly. The skin parts of the upper and lower wings of the module are not directly pressed, and therefore are not sufficiently fixed on the spar. One disadvantage of this incomplete compression is that when the leading edge cover is placed above the leading edge of the blade subassembly, 'if any of the composite skin is separated from the spar, one or both of the leading edge covers The trailing edge will slide under the compound skin, and an abnormal interface will be created between the leading edge cover and the blade subassembly, making the assembled blade into a defective product. Another important field in the above-mentioned parallel protocol is the cover expansion tool used to combine the leading edge cover and the blade sub-assembly. The grab in the conventional art faces the leading edge when the trailing edge of the leading edge cover is deployed. The IML surface of the cover produces a shearing effect. This kind of shearing force produced by the conventional skill grab will cause the composite material of the leading edge cover to crack or delaminate, causing the component to become defective and must be reprocessed. In addition, the operation of the conventional skill grab is to enable the grab to deface the front edge covering joint surface of the flawless plague. At the same time, the fan-shaped parts of the grab are operated in a continuous manner. Margin cover unfolds. Not only is this method laborious, time consuming, and wasteful, but it also causes unnecessary stress in the tail edge of the leading edge cover. Another method for manufacturing main rotor blades was published in US Patent No. 5,528,828 "Method for Manufacturing Main Rotor Blades for Helicopters" and this paper standard is applicable to China-Home Sample (CNS) A4 specification (210 × 297 mm) Γ Λ _ {Please read the precautions on the back before filling out this page—installation., 1T printed by the Consumers' Cooperative of the Central Standards Bureau of the Ministry of Economic Affairs 12 Printed and issued by the Consumers ’Cooperative of the Central Standards Bureau of the Ministry of Economic Affairs 412457 A7 _________ B7 ) ~ 5,570,63i, the device for manufacturing the helicopter's main rotor, Le Ye, and both were transferred to United Science and Technology Corporation (hereinafter referred to as ", 828 patents, and ,, 63" patents " ). As shown in Figures i and 2, the 828 patent and 631, the devices published in the patent include a compression centering device for assembling and compacting a forbidden leaf subassembly 24, and a During the pressing process, a leading edge cover 22 is unfolded and inserted into the cover expansion / insertion device 50 on the side of the purple leaf sub-assembly 24, wherein the leaf-forbidden sub-assembly 24 includes an upper wing skin 12, and a lower plane. Wing skin 18, a core 14, A spar assembly 16. The compression fixture 10 includes a lower assembly 26 having a contoured upper wing cover 28 mounted together with a support structure 30; and an upper assembly 32 having an pressure The bag 34 is in close contact with a contoured support plate 36, which is fixed to a structural support truss 38. The contoured upper wing cover 28 has a plurality of cutter pins 31 for positioning the upper wing skin 12 so that The upper wing cover 28 is lined up in a row; and a plurality of rear membrane push pins 39 enable the spar components to be arranged in a chord-length direction within the contoured upper wing cover 28. The spar pillars fixed on the supporting street frame 38 40. The spar assembly 16 is arranged in the wing length direction in the contoured upper wing cover 28. When the upper and lower assemblies Η and 26 are fixed together, the pressure bag 34 is pressurized and pressed against the assembled blades. Component components: 2, 14, 16, 18. The cover expansion / insertion device 50 includes a movable pillar 52, which is installed with the movable pillar and can be moved with the upper and lower extension frame members 54, 56 and several rows and牦 Frame parts are mounted together with suction cups 58, 60. There are two air pressure 61 and 62 are inserted between the pillar 52 and the frame members 54 and 56. Pressurizing the pneumatic cylinders 61 and 62 can make the upper and lower frame members 54 56. This paper size applies to the Chinese National Standard (CNS) A4 specification (210X 297). Gongchu). „Installation ------ Order ------ Wei (Please read the notes on the back before filling this page) 412457 A7 B7 Printed by the Shellfish Consumer Cooperative of the Central Bureau of Standards ^ V. Description of the invention (5) The leading edge cover 22 can be inserted and moved synchronously between a separated position between the upper and lower suction cups 58 and 60. This position is during the pressing period of the suction cup and the leading edge cover 22 in a docking manner. A bite position where the surface of each outer mold line (0 ml) bites, and a running position where the leading edge cover 22 is expanded to be inserted above the blade secondary member 24. A vacuum source 64 is pneumatically connected to the suction cups 58 and 60 to generate suction force at the occluded position, so that the suction cups 58 and 60 are engaged with the surface of each outer mold line (0ML) of the leading edge cover 22, so that the upper and lower brackets The frame members 54 and 56 are then moved to the operating position simultaneously to unfold the leading edge cover 22. The movement of the movable pillar 52 causes the deployed leading edge cover 22 to be disposed on the blade sub-assembly 24 during the pressing period. Regarding the blade subassembly tool described earlier, one of the disadvantages of the methods and devices published in the 828 and 63Γ patents is that the clamping fixture 10 is compounded on the spar assembly 16 and the part near the leading edge 42 of the blade subassembly 24 The epidermis 12, 18 does not provide sufficient compression. As shown in FIG. 2, since the movable pillar 52 arranges the leading edge cover 22 on the blade sub-assembly 24 during the pressing, the leading edge of the blade sub-assembly 24 must have sufficient clearance to actually allow the movable pillar 52 can be moved horizontally to the appropriate position. Therefore, the pressure bag 34 does not completely cover the leading edge of the blade sub-assembly 24, so the upper and lower wing composite skins 12, 18 cannot be properly pressed onto the spar assembly 16 in this area, so I have found that these are also called The composite skin front edges 12, 18 which are "joints" may have a tendency to arch the spar assembly 16 in the area of the leading edge. These, the joints each define a "pedal", so that the leading edge cover 22 must overlap the corresponding composite skins 12, 18 on it, so that it covers the leading edge cover 22 and the blade subassembly 24 If there is a X degree between this paper, the Chinese National Standard (CNS) M specification (2〗 0x297 mm) [~ — ^ 衣 i III, 1τ--I-I —- ^ r-(Please read the notes on the back first Master fill in this page again;} Yin Ju 412457 A7, Central Engineering Bureau of the Ministry of Commerce, Ministry of Economic Affairs and Economics, a __B7_ V. Description of the invention (6) An appropriate interface. In case the tenon arches the spar assembly 16 At this time, the leading edge cover 22 can slide under the joint during installation, and an inappropriate and unacceptable interface is formed between the leading edge cover 22 and the blade subassembly 24. In addition, the design '828 The shortcomings of the sheath expansion / insertion device 50 disclosed in the patent and the '631 patent further increase the possibility of forming an inappropriate interface between the leading edge sheath 22 and the blade subassembly 24 during installation, specifically, The front edge cover 22 is positioned between the rows of suction cups 58 and 60, and the frame members 54 are closed up and down. When the 56 is in the running position, the weight of the leading edge cover 22 generates a downward force and acts on the upper row of suction cups 60 and the lower frame member 56. I have found that this action acts on the lower frame member 56. The downward force is not sufficiently offset by the pressure acting on the lower cylinder 62, so the lower bracket member 56 tends to sink under the action of the leading edge cover 22. In addition, since the suction cups 58 and 60 are Composed of rubber bellows, the weight of the edge cover 22 will also cause the bellows in the lower suction cup 60 to fall, and elongate the bellows in the upper suction cup 58. The downward force acting on the bracket member 56 And the tendency of the lower suction cup 60 to fall causes the leading edge cover 22, the tail edge of the machine to bow downward, dislocation between the leading edge cover 22 and the paddle subassembly 24. This dislocation feature causes the pillar 52 to move horizontally When the leading edge cover 22 is close to the leading edge of the blade sub-assembly 24, the bending of the leading edge cover 22 will cause the upper edge of the trailing edge cover 22 to be caught under the joint on the lower wing composite skin a. An improper interface. The fact that exacerbates this problem is that when pillar 52 When it is located near the compression clamp 10, the compression clamp 10 and the cover expansion / insertion device 50 close the leading edge. The paper size applies the Chinese National Standard (CNS) Α4 specification (210X297 mm). 9 'ά --- --- 1Τ ------ extinguish-- (Please read the notes on the back before filling out this page) V. 412457 A7 B7 Invention Description (7 Printed by the Employee Consumer Cooperative of the Central Standards Bureau of Didi Ministry ¾ Cover The tail edge of the 22 and makes it very difficult for the operator to identify from the appearance whether the tail edge of the leading edge cover 22 is in the correct installation position. The positioning of the tail edge of the leading edge cover 22 is uncertain When in use, the trailing edge of the leading edge cover 22 can be opened wider (more than a better displacement of 127 cm (0.5 in) on each side), making one of the trailing edges less likely to get stuck in one Below the joint. However, a disadvantage when the tail edge of each side is expanded more than 1.27 cm (0.5 in) is that the composite material in the leading edge cover 22 and the heating bottom plate may be more vulnerable to damage due to the stress caused by such excessive expansion. Must be reprocessed. Therefore, an object of the present invention is to provide a device and method for assembling a helicopter main rotor blade sub-assembly ', which provides a complete chord length and wing length compression effect of the blade sub-assembly. Another object of the present invention is to provide a device and method for assembling a helicopter main rotor blade sub-assembly, which can minimize the stress acting on the helicopter main rotor blade sub-assembly. Another object of the present invention is to provide a device and a method for assembling a helicopter main rotor blade under-assembly, which can reduce the labor required for lifting and precise positioning of the blade-inhibiting sub-assembly components. These and other objectives can be achieved in the present invention by assembling a device for a helicopter main rotor sub-assembly. The leaf sub-assembly includes a wing skin, a type 4, an upper wing skin, and a -Top and -bottom spar assembly, the spar assembly includes a lower group having a base including a contoured upper wing cover, and the contoured upper wing has a bottom end and a top end, a configuration On the profiling, the paper near the wing cover is 剌 ------------ install— (read the precautions on the back before filling in this page) Order ------ scream-- ---- ml r. · Printed by the Central Bureau of Standards, Ministry of Economic Affairs and Consumer Cooperatives 412457 A7 __B7 V. Description of the invention (8) The first and second guide surfaces, where the first guide surface is arranged near the bottom end, The second guide surface is arranged near the top end and has a plurality of front edge push wheels arranged on the proximate upper side of the profiled upper wing. There is an upper component to match the lower component, and includes a support structure and a A flexible water-impermeable membrane supported by a supporting structure, wherein the flexible water-impermeable membrane and the contoured upper wing are sleeved on the upper group When engaging with the lower component, a mold cavity is defined during the engagement. The foregoing objects in the present invention can be achieved by a method of assembling a helicopter blade sub-assembly, which includes a lower wing skin, A core having a cone formed therein, an upper wing skin, and a spar component having a top end and a bottom end. The method steps include providing a component having a base for mating with an upper component. The blade pressing device of the component. The lower component has a base including a contoured upper wing cover, which includes a bottom end and a top end, and at least two guide surfaces arranged near the contoured upper wing cover. A circular body is defined within the surface, and at least one of the guide surfaces 8 is disposed near the bottom end, and at least one of the guide surfaces is disposed near the top end, and has a plurality of wings configured on the contour. The proximal leading edge pusher is sleeved. The upper component includes a supporting structure for supporting a flexible water-impermeable membrane, which allows the flexible water-impermeable membrane and the contoured upper wing to be sleeved between the upper and lower components when the upper component and the lower component engage. A method cavity is defined in between. The method steps further include arranging the upper wing skin and core and the contoured upper wing together, connecting a top support pad to the top of the spar, and a bottom end. The support pad is connected to the bottom end of the spar, of which the top support lining --------, ▲ ------ 1T ------ ^ {Please read the precautions on the back before filling (This page) Poverty Alleviation Cooperatives of the Central Standards Bureau of the Ministry of Economic Affairs, India 412451 A7 ______ · _ B7 V. Description of the Invention (9) < The whole 1 and the bottom support profile each have a guide surface and a guide member used together with the guide surface ^ Then, at least one of the guide surfaces is in contact with at least one of the guide surfaces, ^ (¼ the spar assembly toward The wing length is arranged in the contoured upper wing cover. By inserting the guide into the cone in the guide surface and using the leading edge pusher to insert the spar assembly into the cone in the core, the spar assembly is directed toward the chord It is placed in the profiled upper wing cover in the long direction, and then the lower wing skin is arranged with the core and spar components to form a helicopter blade sub-assembly, and then the upper and lower components are engaged. The air in the cavity is then Exhaust, the exhaust of air causes the flexible impervious diaphragm to exert a tight pressure on the helicopter blade subassembly. From the following detailed description, other objects and advantages of the present invention will become more apparent to those skilled in the art, Among them, only the best mode considered for completing the present invention is illustrated by example, and the preferred embodiment of the present invention is shown and described. It must be understood that the invention can be modified in various aspects without departing from the invention. ,various The drawings and description are for illustration purposes only and are not limiting. Figure 1 is a perspective view of the conventional art compression clamp and cover expansion / insertion device; Figure 2 is a view of the conventional art device of Figure 1 Partial plan view; Figure 3A is a top view of a demonstration main rotor blade of a Η-60 helicopter; Figure 3B is a cross-sectional view of the main rotor blade along line 3B_3β in Figure 3A; Figure 3C is An enlarged partial perspective view of the leading edge cover illustrated in Figure 3B; The paper A is suitable for China National Standard (CNS) A4 specification (210X297 mm) 12 I ^ ~. -1τ -------- -(Please read the notes on the back before filling out this page) 412457 A7 B7 Printed by the Peasant Poverty Alleviation Cooperative of the Central Standards Bureau of the Ministry of Economic Affairs 5. Description of the invention (10 3D picture is a model main rotor blade used in Fig. 3A A perspective view of an enlarged part of a spar assembly; Fig. 4 is a perspective view of a blade pressing device specifically showing the characteristics of the present invention; Fig. 5 is a line segment 5-5 of the blade pressing device of Fig. 4 A partial cross-sectional view taken, including the main rotor blade of Figure 3B Loading surface; Figure 6 is a cross section taken along line 6_6 of the blade pressing device of Figure 4, including the circle cross section of the main rotor blade of Figure 3B, and depicting the upper and lower components Fig. 7 is a plan view of a supporting device specifically showing the characteristics of the present invention, the device is used to support the spar assembly of Fig. 3D; Fig. 8 is the spar assembly and supporting lining of Fig. 7 A partial cross-sectional plan view; FIG. 9 is a plan view showing the leading edge cover installation device with the features of the present invention; FIG. 10 is a pneumatic cylinder, suction cup, duct, and vacuum help depicting the 9th front edge cover installation device; A circle connected to the pump and the vacuum accumulator; FIG. 11 is a plan view of the leading edge cover installation device of FIG. 9, which depicts that the leading edge of the blade subassembly is being inserted into the leading edge cover; FIG. 12 is a flowchart illustrating a method of manufacturing a blade sub-assembly capable of displaying the color of the present invention on a specific surface; and FIG. 13 is a diagram illustrating a method of installing a leading edge cover on the blade sub-assembly, which can be specifically expressed. Out A flow chart of the method of the invention is characterized in that the paper size is applicable to the Chinese National Standard (CM) A4 specification (210 × 297 mm) ----------------------------- Please read the notes on the back before filling this page) 13 Printed by the Central Standards Bureau of the Ministry of Economic Affairs and Consumer Cooperatives 41245Ϊ A7 ---------- B7 V. Description of the invention (n), Figure 〇Complete the invention Best Mode The devices and methods described in further detail below include some manufacturing agreements for the assembly of the main rotor blades of H-60 helicopters manufactured by Sikorsky Aircraft Company. However, it should be understood that The device and method are suitable for the assembly of general main rotor blades. The main rotor blades 3A-3D exemplarily illustrate a piece of h-60 main rotor blade MO 'including a leading edge 102 and a trailing edge 104, both of which collectively define the rotor blade 100. Chord, and has a bottom end and a top end 108, which together define the wing length of the rotor blade 100 (a top cover 109 of the main rotor blade 100 is separately assembled to connect to the main rotor blade ι. 〇 Top 108). The main rotor blade 100 includes upper and lower wing skins 110, 12 defining aerodynamic surfaces above and below the blade 100, a core Π4, a spar assembly 116, and a leading edge cover 120 ^ up and down The wing skins 110, 112, the core 114, and the spar assembly 116 collectively define a blade sub-assembly 132 »In the illustrated embodiment, the upper and lower wing skins 110, 112 are prepared by several layers of well-known techniques. A pre-formed member made of a dip-impregnated composite material, such as woven glass fibers embedded in a suitable resin filler. A plurality of corresponding trailing edge tool fins 130 extend from the trailing edges of the upper and lower wing skins 110, 112, and an opening 131 is formed in each of the trailing edge tool fins 130. As will be discussed more thoroughly below, during the blade assembly process, the trailing edge tool fins 130 help to correct the correct wing length direction of the upper and lower wing skins 110, 112 and the chord size of the paper. The Chinese National Standard (CNS) A4 specification ( 210X297 mm) 14 ^ 1 pack ------ order -------- Cheng (Read the note on the back of the poem ^ a ^ ^ item before filling out this page} ^ The staff of the Ministry of Economic Affairs Central Bureau of Standards Bureau eliminates cooperation Printed by the agency A7 ______B7 V. Description of the invention (12) Longitudinal positioning. In the described embodiment, the core Π4 is composed of a honeycomb-like material commonly used in aerospace applications, such as nomexr (nomexr is the United States Dravier (Registered trademark of aramid fiber or fabric of East India DuPont, Wilmington, Calif.), And serves as a low-weight, structural strengthening member between the upper and lower wing skins 11 and 112. The core 114 defines a round body 121 at the leading edge To engage the trailing edge of the spar assembly 116. The upper wing skin 110, the lower wing skin 112, and the core 114 have a plurality of positioning openings 134 formed therethrough to promote the spar assembly 116 in a paddle. Positioning of the leaf pressing device 200, which will be described in further detail below Detailed description. After the main rotor blade 100 has been assembled, the positioning openings 134 are repaired with composite materials, so that the upper wing skin 110 and the lower wing skin 112 have aerodynamic upper smooth surfaces. The spar assembly 116 includes: A spar 117, one or more counterweights 118, and a rear diaphragm Π 9. The spar 117 is the main structural member of the main rotor blade 100, and receives the torque generated by the main rotor 100 during the operation of the helicopter. Dynamic load such as bending force, bending force, shear force, centrifugal force, etc. The spar 117 of the embodiment is made of titanium, but in other embodiments the spar ι17 may be made of other metals, perhaps made of composite materials or the like. The β counterweight Π 8 is used to statically and dynamically balance the main rotor blades ι〇〇. In the embodiment, the counterweight 118 is made of a material with a lower density to a higher density, such as bubble beads, Tungsten and aluminum are arranged in the wing length direction from the bottom 106 to the top 108, and provide the weight distribution required to balance the static and dynamic balance of the main rotor blade ι〇〇. The counterweight manufactured 118 includes structural reinforcement 136, which provides a counterweight 118 and a leading edge cover 120 paper size Shicai Guanjia County (CNS) Α4 secret 公 χ297 while taking advantage of (Please read the note on the back first and then fill out this page.) Printed by the Central Standards Bureau of the Ministry of Economic Affairs and Consumer Cooperatives, Printed Collection 41245? A7 ______ B7 V. Description of the Invention (13) ^ The actual engagement between the inner mold line (IML) surfaces. The counterweight 11 § is adhesively connected to the leading edge of the spar 117 so that the joined counterweight n8 is inserted between the leading edge cover 120 and the leading edge of the spar 117. The rear membrane block 119 is adhesively connected to the discontinuous position of the rear edge of the spar 117 corresponding to the positioning opening 134 in the upper wing skin 110 and the core 114. By positioning the opening 134, the rear membrane block 119 facilitates the positioning of the spar assembly 116 within the blade compression device 200, which will be described in further detail below. In the illustrated embodiment, the leading edge cover 120 is a prefabricated hybrid member made of a composite material and an anti-wear material in more detail in FIG. 3C. The cover 120 has a U-shaped configuration that defines the leading edge 102 of the main rotor blade. The cover 120 has one or more layers of prepreg colloidal material 122, such as woven glass fiber embedded in a suitable resin filler, and defines the inner mold line (IML) of the leading edge cover 120, a first wear resistant The slat 124 and a second wear-resistant slat 126. The leading edge cover 120 provides wear protection for the leading edge 102 of the main rotor blade 100, controls wing tolerances of the main rotor blade ιOO, and accommodates the main rotor blade de-icer assembly (not shown). The method of manufacturing the main rotor blade 100 will be discussed in more detail below. This method uses a blade pressing device 200, a support device 300, and a leading edge shroud installation device 400. Paddle Compression Device Referring to FIG. 4, the paddle compression device 200 has a lower assembly 200 for engaging with an upper assembly 250. The lower component 202 includes a base 206 having a contoured upper wing cover 208, wherein the contoured upper wing cover 208 is used to engage the shape of the wing above the blade sub-assembly 132, and Have a paper standard applicable to China National Standards (CNS) Α4 specifications (210 × 297 mm) 16 '------, π ------- ^ (Please read the notes on the back before filling in this Page} Printed by the Central Standards Bureau of the Ministry of Economic Affairs, Consumer Cooperatives ^ A7 _____B7 V. Description of the invention (14) ~ one inner side 21 corresponding to the bottom end 106 of the blade sub-assembly 132, and one blade sub-assembly 132 The outer end 212 corresponding to the top end 108. There are two guide surfaces 214, 216 arranged near the contoured upper wing cover 208, so that the guide surface 214 is located at the inner end 21 of the contoured upper wing cover 208. The guide surface 216 is located near the outer end 212 of the contoured upper wing cover 208. Each guide surface 214, 216 has an inclined surface 218 that terminates in a cone 222. In addition, there is one The bolt 224 is matched with each guide surface 214, 216, so that the rotation of the bolt 224 can drive the bolt 224 toward the cone 222 and The inclined surface 218 moves up. There are three rear film push pin recesses 226 formed at the wing length and chord length position in the contoured upper wing cover 208 and the positioning opening 134 in the blade sub-assembly 132, as shown in FIG. As shown in the figure, there are three rear diaphragm push pins 228 operating in conjunction with the positioning opening 134 and the rear diaphragm push socket 226, so that the rear diaphragm push pin 228 can be used for various purposes during the manufacture of the blade sub-assembly 132, as will be described later. In detail, in addition, there are three leading edge pushing wheels 23, each of which has a cam surface 232, and is arranged near the leading edge of the contoured wing cover 208, so that each leading edge pushing wheel 230 is It is arranged at a position in the wing length direction corresponding to the rear film push pin recess 226. The leading edge push wheel 230 is constructed in a conventional way of constructing a cam in the conventional art, and the operation of the leading edge push wheel 230 promotes the cam surface 232. Advancing towards a chord length of the rear membrane push pin 228. Referring to Figures 4 and 6, there is a vacuum source 234 arranged with the base 206 and having a plurality of ducts 236 extending therefrom, each of which terminates at There is a corresponding opening 238 in the base 206. In the embodiment, the vacuum source 234 includes a traditional vacuum pump, and the opening 238 paper size is applicable to China National Standard (CNS) A4 specification (210X297 mm) 17 ——I -.---- έ ----- -IT ------ Μ (Please read the notes on the back before filling out this page) Printed by the Central Bureau of Standards of the Ministry of Economic Affairs of the People's Republic of China 4124 ^ A: ---- 一 __B7 V. Description of the invention ( 5) 1 arranged in two rows, one row is located near the leading edge of the contoured upper wing cover 208, and one row is located near the trailing edge of the contoured upper wing cover 208. In addition, there are five spring-loaded tool blade pins 240 arranged in a row near the trailing edge of the contoured upper wing sleeve 208 and the chord lengths corresponding to the openings 131 in the trailing edge tool blade 130 of the blade subassembly 132 And at the wing length. 4 and 6, the upper assembly 250 includes a support structure 252 for supporting a flexible water-impermeable membrane 254. In the described embodiment, the support structure 252 is connected to the base 206 by using a plurality of pivots 256, so that the support structure 252 can move from the flexible water-impermeable membrane 254 to the first position of the contoured upper wing cover 208 Rotate to the second position where the flexible watertight diaphragm 254 covers the contoured upper wing cover 208. The supporting structure 252, the flexible watertight diaphragm 254, the contoured upper wing cover 208, and the base 206 are constructed together so that when When the support structure 252 is in the second position, the flexible water-impermeable membrane 254 can cover the contoured upper wing cover 208, and an air-tight seal is formed between the support structure 252 and the base 206. In addition, when the support structure 252 is in the second position, the flexible watertight membrane 254 and the contoured upper wing sleeve 208 define a cavity 258 therebetween. In the illustrated embodiment, the opening 238 in the base 206 is constructed so that when the vacuum source 234 is activated, the vacuum source 234 exhausts the air in the cavity 258 to pull the flexible water-impermeable diaphragm 254 toward the contoured upper wing. Set of 208. Refer to Figures 3A-D, 4 and 7 for the supporting device. The supporting device 300 is used together with the blade pressing device 200 during the assembly of the blade sub-assembly. The supporting device 300 includes a bottom support pad 302 for receiving To the bottom of the spar 117, the paper size applies to the national standard of Shenyang (CN £;) Α4 size (210X297 mm) 18 1 pack -------- Order ------- ^ (Please read the back first Please pay attention to this page and fill in this page again.) Employee Consumer Cooperatives, Central Standards Bureau, Ministry of Economic Affairs, India Fanfan 412457 A7 __B7 V. Description of the Invention (l6) 106; a top support pad 304 for connecting to the top 108 of 117; a bottom The end gearbox 308 is connected to the bottom end support pad 302; and a lifting device 338 is used to support the bottom and top gearboxes 308, 306. In the embodiment shown in FIG. 8, the bottom end support pad 302 includes a base base 310 having a pair of members 312 and 314 extending therefrom for insertion into the bottom end 106 of the spar 117. One of the members 312 has two spring-loaded forks 316 extending from the same, and is used together with a pair of corresponding openings 117A in the spar 117, and fixes the bottom support lining 302 and the spar 117 together. . The top support pad 304 has a plurality of angular flanges 320 inserted into the top 108 of the spar 117, and there are a plurality of openings 322 corresponding to the openings in the top 108 of the spar 117 for the top cover. 109 is fixed to the blade subassembly 132. A plurality of bolts 324 are used with the opening 322 for positioning and fixing the top support pad 304 on the spar π ?. Referring to Figures 6 and 8, each support pad 302, 304 further includes two guides 326, 328 extending from there toward the wing length and terminating at a transmission fixing plate 329. The fixing plate has Helps connect the support pads 302, 304 to their respective gearboxes 308, 306. In the described embodiment, the guide 328 near the rear edge of the spar assembly 116 is a cylindrical roller for engaging with the inclined surface 218 in the guide surfaces 214 and 216. In addition, each transmission fixing plate 329 includes a guide The surface 330 is located on the upper side of the fixed plate 329 near the guides 326 and 328. As discussed in more detail below, guides 326, 328 and guide surface 330 are used in conjunction with guide surfaces 214, 216 to properly position spar assembly 116 during blade subassembly 132 manufacture. This paper size is applicable to Chinese National Standard (CNS) A4 now (210X297 public director) 19 -------- ^ Attack ------ " ------ ^ (Please read the Note: Please fill in this page again.) Printed by the Consumers' Cooperative of the Central Standards Bureau of the Ministry of Economic Affairs ^ f 41245? A7 ______B7 V. Description of the invention (1?) ^ See Figures 7 and 8 for the top gearbox 306 and the bottom gearbox 308 Each is equipped with a conventional transmission, enabling each gearbox 306, 308 to translate the spar assembly 116 in a generally vertical direction and also to rotate the spar assembly 116 about its longitudinal axis. In the embodiment, the gearboxes 306, 308 have rotatable cranks 334, 336 for manually pushing the spar assembly 116 in vertical and rotational directions, or in either direction. In other embodiments, the electric motor may be used with the gearboxes 306, 308 to cause the spar assembly 116 to generate vertical and rotary motions, or any of these motions. The lifting device 338 includes a conventional bridge crane, such as a crane known in the art for lifting materials in a manufacturing environment. In the described embodiment, the lifting device 338 includes a lifting cable connected to each of the transmissions 306, 308, and the lifting device 338 can move the transmission 306 in the vertical and horizontal directions or any of them. 308. Leading edge cover mounting device Referring to Figures 9, 10 and II, the leading edge cover mounting device 400 includes a lower component 402 that is connected to an upper component 45. The lower assembly 402 includes a base 400, which has a plurality of pneumatic cylinders 406 connected to it and arranged in opposite rows. Each pneumatic cylinder 406 has a translation member 408, which is subjected to a pressurized air group 41. 〇The pressurized air supplied to the pneumatic cylinder 406 can perform translational movement. The translation member 408 is connected to the opposite frame member 412, and the frame member 412 is used to support a plurality of suction cups 414. The pneumatic cylinder paper is arranged according to the structural member 412 and the suction cup 414 so that the opposite rows of the suction cups 414 are pressurized by the pressurized air group 41 °. The size of the paper is applicable to the Chinese National Standard (CNS) A4 specification (2 ^ 297 cm). ) _— I '-pack. I — *-order—— __ I-- shout (please read the precautions on the back before filling out this page) ---..._____ B7 V. Description of the invention (18) ^ --- Able to move synchronously when acting. In the illustrated embodiment, the assembly 402 includes four vacuum pumps 416 connected to four vacuum pressure accumulators 418, wherein the vacuum pressure accumulator 418 is connected to a plurality of suction cups 414 through a plurality of corresponding conduits 422. The vacuum pump 416 and the vacuum accumulator 418 together provide suction to a plurality of suction cups 414. In the illustrated embodiment, the suction cups 414 and their corresponding conduits 422 are divided into four lines, wherein the bus lines are connected to one of the vacuum accumulators 4 and 8. A plurality of valves 424 cooperate with the ducts 422, and their function is to adjust the vacuum pressure of the suction cup 414. The vacuum accumulator 418 is a traditional design designed to have a predetermined storage capacity to quickly provide a vacuum between approximately 67.73 kPa and 84.66 kPa (20 in.Hg and 25 in.Hg) per suction cup 414 pressure. A leading edge covering profile 42 is inserted between the opposite rows of suction cups 414 and is used to support the leading edge covering 12o β. In other embodiments, the 'vacuum pump 416, the vacuum accumulator 418, and the circuit The number may be different from those described in those embodiments to meet the operational requirements of those embodiments. The upper piece 450 includes five pillars 452 that extend substantially perpendicularly from the base 404 and are positioned toward the wing length at positions corresponding to the position of the trailing edge tool blade 130 of the blade sub-assembly 132. Each post 452 has a contoured splint 454 connected thereto, wherein each contoured splint 454 has a channel curved surface 456, a hinged fixing member 458, and a tool wing pin 460 β channel curved surface 456 and hinges. The fixing member 458 sandwiches the blade sub-assembly 132 therebetween, and the tool fin pin 460 and the blade sub-assembly 132 tool fin 130 correctly position the blade sub-assembly Π2. Chinese paper standard (C'NS} A4 specification (210X 297mm) applies to this paper music scale ) Economy, Deng Central Standards Bureau, Shellfish Consumer Cooperatives Co., Ltd. 41245? A7 —________ B7 V. Description of the Invention (19) In the embodiment described, each contoured splint 454 can provide an open structure, so that the hinged fixing member 458 can It is positioned on the far side of the fence 456 and provides a closed structure, so that the fixed fixing member 458 can be positioned on the near side of the fence 456, and is used to fix the blade subassembly η: In addition, the upper assembly 450 also includes three The rear film push-out recess 451 is formed on both the curved surface 456 of the road and the bridge member (not shown), or the bridge member extends between the adjacent profiling plywood 454 and is positioned between the Positions corresponding to the wing length and chord length of the positioning opening 134 in the paddle-person assembly 132. The imitation opening plate 454 is connected to the pillar 452, so that the contouring splint 454 can cover the contouring sleeve relative to the leading edge. 420 for translational movement. In the implementation Among them, there is a rotary wheel 462 and a differential 464 configured by a traditional transmission method, and mechanically coupled to the contouring splint 454 for manual translation of the contouring splint 454 to the contouring sleeve 420. Among other things, In the embodiment, the translational movement can be completed by using either or both of the electric motor and the hydraulic system. For the blade subassembly assembly method, see the blade subassembly illustrated in Figures 3A-D and 4-8. The device 200 and the supporting device 300, and referring to the flowchart in FIG. 12, will now discuss the assembly method MF of the blade sub-assembly 132 in more detail. In step 500, the upper wing skin 11 and the core 1U are arranged on the upper side. Above the wing cover 208. In the described embodiment, the upper wing skin 110 and the core 114 are bonded together before being disposed on the upper wing cover 208 to reduce assembly time. In step 502, the upper The wing skin no. 0 and this paper size are applicable to the specification (21〇χ 职) 22 J iT -------- ^-Welding (Please read the precautions on the back before filling this page) V. Description of the invention (2 〇) Α7 Β7 _Beijing Consumer Cooperatives, Central Bureau of Standards, Ministry of Economic Affairs The composition of the printed core 114 is arranged on the upper wing cover 208 in the direction of the wing length and chord length by using the opening ι31 in the trailing edge tool wing 13 and arranging it around the spring-loaded tool wing pin 24. In addition, the rear membrane push pin 228 passes through the positioning opening 134 in the core 114 and the upper wing skin 11 and penetrates into the rear membrane push pin recess 226. In the embodiment, a conventional technique is provided for The well-known bonding agent that attaches the blade spar to the skin / core composition in an adhesive manner is applied to the spar assembly 116 before performing step 504. In step 504, the bottom support pad 302 is connected to the bottom end 106 of the spar 117, and the top support pad 304 is connected to the top 108 of the spar 117. In steps 506 and 508, the bottom support pad 302 is connected to the bottom gearbox 308, and the top support pad 304 is connected to the top gearbox 306. The two gearboxes 306, 308 are then sequentially connected to The hoisting rope 340 causes the spar assembly 116 to flutter by the hoisting device 338. In step 510, the spar assembly 116 is lifted and positioned by the lifting device 338, so that the bottom end support pad 302 is located near the guide rail surface 214 above the inside end 210 of the contoured upper wing cover 208, and the top end The support pad 30 is located near the guide rail surface 216 above the outer end 212 of the contoured upper wing cover 208. In step 512, the guides 326, 328 of both the bottom support pad 302 and the top support pad 304 are engaged with the inclined surfaces 218 of the guide rail surfaces 214, 216. Next, by positioning the guide surface 330 on the top support pad 304 of the guide rail surface 216 abutting on the outer end 212 of the profiled upper wing cover 208, the spar assembly 116 is positioned in the wing length direction at step 514. In the middle, the bottom gearbox 308 is disengaged from the bottom support pad 302 and the top gearbox 306 is disengaged from the top support pad 304. --------- ^-(Please read the notes on the back before filling in this page) • 丨 Step — I f. * .I ml The paper scale is applicable to the Chinese National Standard (CNS) A4 specification (2 (0x297 mm) 23 Printed by the Consumer Cooperatives of the Intellectual Property Bureau of the Ministry of Economic Affairs 412i57 5. Description of the invention (21) In step 516, the bottom end ι06 and the top end of the spar assembly 116 are guided by the screw inspection 224 326 and 328 are inserted into the inclined surface 218 until the guide member 328 near the rear edge of the spar assembly 116 abuts the cone 222 in each inclined surface 218 and is positioned correctly in the chordwise direction. The correct positioning of the bottom end 106 and the top end 108 of the spar assembly Π6 does not need to ensure that the other parts of the spar assembly 116 will be positioned in the chord direction of the positive disc. In step jig, in order to correctly position the entire spar assembly 116 toward the chord length direction, it is necessary to activate the leading edge pusher 230 to engage the cam surface 232 with the structural reinforcement point 136 on the spar assembly U6 and make the spar assembly After Π6, the membrane block 119 abuts on the rear membrane push pin 228. It can be understood that the rear diaphragm push pin 228 is located in the chord direction, and the contact between the rear diaphragm block 119 and the rear diaphragm push pin 228 ensures that the trailing edge of the spar assembly 116 is correctly fixed to the cone 121 defined by the core 114. Inside. When the spar assembly 110 is properly positioned, a cement (not shown) is applied over the core 114 and the spar assembly 116 to prepare to receive the lower wing skin 112. In step 520, the lower wing skin 112 is arranged above the core 114 and the spar assembly U6, and the trailing edge tool wing 130 of the lower wing skin 112 is positioned at the wing length together with the spring-loaded tool wing pin 240. In the chord length direction. At step 522, a fetal membrane plate 242 is arranged on the forbidden leaf sub-assembly 132 (see circle 6), and its role is to distribute the compressed diaphragm 254 and apply it to the kidneys of the prize sub-assembly 32 In step 524, the upper two-bag filter 244 is fitted to the belly of the fetus. Its role is to help exhaust air trapped between the membrane plate 242 and the flexible watertight diaphragm 254 during compression, and reduce the blades. Friction between the subassembly 132 and the flexible water-impermeable barrier 254. In step 526, the support structure 252 is turned to the second position and fixed at {Please read the precautions on the back before filling this page) ------- ^ --------- ^ J.- ----------------------

-24 - 經漓部中央標率局負工消费合作社印^ «2457 A7 s*---_—___B7___ 五、發明説明（22 ) ' 正確位置上，而使撓性不透水隔膜254蓋住槳葉次組件！ 32 與仿形上機翼套208,藉以在其間形成密閉的模穴258。 於步驟528中，真空源234被啟動，藉以排出模穴258中 的空氣。在所述實施例中，由真空源234提供的真空壓力 大約等於44_〇2 kPa(13 in.Hg)。從模穴258中排出空氣可 使撓性不透水隔膜254被拉向仿形上機翼套208 ,藉以提 供緊壓作用給槳葉次组件132之諸構件。 於步驟530中，真空源234被關閉，且支撐結構252 轉回到第一位置，而撓性不透水隔膜254不再蓋住槳葉次 組件132。欲準備將壓緊的槳葉次組件132從槳葉緊魔裝 置200中移除，則袋式過濾器244、胎膜板242、前緣推 輪230以及後膜推銷228通通都要移除。於步驟532及534 中，底端支撐襯墊302再度接至底端變速箱3〇8，而頂端 支撐襯墊304再度接至底端變速箱306，接著兩個變速箱 306、308依序再度接至起重索340，使槳葉次組件132 由起重裝置338支撐著。 於步驟536中，螺栓224被鬆開，而導件326、328 滑出斜面218之外，使底端支撐襯墊302及頂端支樓襯墊 304不再受槳葉緊壓裝置200之作用。槳葉次組件132接 著由支撐裝置300從槳葉緊壓裝置200送往前緣覆套安裝 裝置400。 安裝前緣覆套之方法 參看第3A-D及7-11圖中例示之槳葉次組件η?、支 撐裝置300、以及前緣覆套安裝裝置400，並參看第η圖 本紙張尺度適用中國國家標準（CNS ) A4規格（2丨0X297公釐） , . i------IT------^ (請先閲讀背面之注意事項再填寫本頁) 412457 經濟部中央標準局舅工消費合作社印1Ϊ A7 B7 五、發明説明（23 ) 之流程圖，現在將更詳細討論將前緣覆套12〇與壓緊之槳 葉次組件13 2安裝在一起的—個方法]vil。 於步驟600中，在準配配置前緣覆套安裝裝置4〇〇内 的前緣覆套120時，對置列的吸盤414經過檢查以確保吸 盤414在脫離位置，其中對置列的吸盤414被隔開大於前 緣覆套120寬度WLES的一個距離（見第3C圖）。於步驟 602中，前緣覆套120被配置在前緣覆套仿形套420之内， 並藉由對接前緣覆套120頂端至一工具止擋（未示出）而朝 翼長方向定位。於步驟604中，對置列的吸盤414被氣壓 紅406推進一個咬合位置，使每個吸盤414均與前緣覆套 120機尾邊緣之各外模線（〇ML)表面對接咬合。 於步驟606中，真空泵416被啟動，藉以在各對應的 真空蓄壓器418内累積真空壓力。於步驟608中，閥門424 開啟，而使真空蓄壓器418内累積的真空壓力對吸盤414 產生作用，藉以在各吸盤414與前緣覆套120的OML表 面之間產生吸力。在所述實施例中，每個吸盤414具有一 個風箱形設計，使其在諸閥門424開啟時，各吸盤414之 風箱形部分陷落，而使前緣覆套120機尾邊緣之OML表 面被拉向對置的拢架構件412。在所述實施例中，吸盤414 係建構成當產生的真空壓力介於大約67刀3 kPa與84.66 kPa(20 in.Hg與25 in.Hg)之間時，各吸盤414之風箱形部 分陷落大約1.27 em(0.5 in·)，而使前緣覆套120寬度WLES 增加大約2.54 cm(l in.)。在另外實施例中，吸盤414設 計與作用在吸盤414上之吸力大小可從敘述過的實施例中 本紙張X度適用中國國家標準{ CNS ) A4规格（210X297公釐） 26 , 1 ------1T-------^ (請先閲讀背面之注意事項再填荇本頁) 經漪部中央標準局負工消费合作社印聚 412457 A7 ______________ 五、發明説明（24 ) 加以修改，以增加或減少前緣覆套12〇之展開程度。此外， 可利用氣壓知406移動對置列的吸盤414，使其彼此之間 遠離，而使前緣覆套12〇額外增加展開程度。 於將槳葉次组件132與前緣覆套安裝裝置400配置在 一起之前，可將接合劑（未示出）塗在槳葉次組件132之前 緣133上面（見第9圖），藉以黏著方式將前緣覆套120接 在槳葉次組件132上面。於步驟610中，支撐裝置300之 底端及頂端變速箱306、308經過調整以確保槳葉次組件 132大體上朝垂直方向，而槳葉次組件132之前緣133面 向下。於步驟612中，後膜推銷228被插入前緣覆套安裝 裝置400之上組件450中的後膜推銷凹座451内，而仿形 夾板454處於開啟狀態，使鉸接固定構件458被定位在圍 道曲面456之遠側。於步驟614中，槳葉次組件132被支 撐裝置300送往開啟的仿形失板454並配置在其内，使後 膜插銷228穿過上機翼表皮11〇與型芯114中的定位開口 134，並使工具翼片插銷460穿過對應的工具翼片開口 132，藉以確保槳葉次組件132正確地定位在前緣覆套安 裝裝置400内。於步驟616中，仿形夾板454處於關閉狀 態，使鉸接固定構件458與槳葉次組件132之下機翼表皮 112對接，藉以將槳葉次組件132固定在仿形夾板454之 内。 於步騾618中，底端變速箱308脫離底端支撐襯墊 302,而頂端變速箱306脫離頂端支撐襯墊304。於步驟620 中，仿形夾板454利用回轉輪462向下平移，而使槳葉次 本紙張尺度適用中國國家標準（CNS ) A4規格（2丨0X297公楚） 27 --------,i------^------t (請先閱讀背面之注意事項再填寫本頁} 經漪部中央標準局貝工消費合作社印製 412457 A7 ----..__ ___B7 i、發明説明（25 ) 組件132之前緣133被插入展開的前緣覆套12〇内。於步 驟622中，從外觀上檢查槳葉次組件132之前緣133與前 緣覆套120，以確保槳葉次組件132之前緣133正確地插 入前緣覆套120内，而使前緣覆套12〇之機尾邊緣與上機 翼表皮110及下機翼表皮112兩者重疊。尤其是，步驟622 係一項檢查，以確保前緣覆套120之機尾邊緣不會導致上 機翼表皮110或下機翼表皮112與翼梁組件116之間分 離。 於步驟624中，與導管422配置在一起之閥門424被 關閉，而使作用於各吸盤414之真空壓力中斷，導致前緣 覆套120與槳葉次組件132之前緣133裝配在一起。於步 驟626中，仿形夾板454利用回轉輪462向上平移，而使 組裝好的主旋翼槳葉1〇〇之前緣1〇2越過對置列的吸盤 414。於步驟628及630中，底端支撐襯墊302再接至底 端變速箱308，而頂端支撐襯墊304再接至頂端變速箱 306，然後兩個變速箱306、308依序再接至起重索340, 而使主旋翼槳葉100由起重裝置338支樓著。 於步驟632及634中，仿形夾板454開啟，而主旋翼 槳葉100脫離工具翼片插銷460及後膜推銷228，使主旋 翼槳葉100能夠由支撐裝置300推向前緣覆套安裝裝置 400的遠方β 對於習知技藝具有一般技術的人將很容易看出’本發 明達成了上述所有目的，在閱讀過前述諸項規格之後，具 有一般技術的人將能夠完成此處廣泛討論的本發明各種改 變、等值替換以及其他各方面。因此此處所認可之保護僅 會受到依附項申請專利範圍及其等值項中的定義所限制。 本紙張尺度適财賴家規格（21Qx297公楚） ---.----d------------妹 (請先閱讀背面之注意事項再填寫本頁) Γ 412457 A7 B7 五、發明説明（26 元件標號對照表 經濟部中夹標準局貝工消費合作社印製 10 緊壓夾具 62' 62氣壓缸 12 上機翼表皮 64真空源 14 型芯 100 主旋翼槳葉 16 翼梁組件 102 前緣 18 下機翼表皮 104 後緣 22 前緣覆套 106 底端 24 槳葉次組件 108 頂端 26 下組件 109 頂蓋 28 仿形上機翼套 110、 112機翼表皮 30 支撐結構 114 型芯 31 刀具銷 116 翼梁組件 32 上组件 117 翼梁 34 壓力袋 117A 開口 36 支承板 118 配重 38 結構支撐桁架 119 後膜塊 39 推銷 120 前緣覆套 40 翼梁支柱 121 圓錐體 42 前緣 122 層 50 覆套擴展/插入裝置 123 縱軸 52 活動支柱 124 第一 _磨板條 54 > 56 拢架構件 126 第二耐磨板條 58 、60 吸盤 130 工具翼片 本紙張尺度適用中國國家標準.（CNS ) A4規格（210X 297公釐） 29 1- I - - -- H. ^ n - —I—----- .. . . 丁 Jv° (請先閱讀背面之注意事項再填寫本頁) 412457 A7 B7 五、發明説明（27 ) 經濟部中央標準局員Η消費合作社印^ 131 開口 244 袋式過濾器 132 槳葉次組件 250 上組件 133 前緣 252 支撐結構 134 定位開口 254 不透水隔膜 136 結構加固點 256 極轴 200 槳葉緊壓裝置 258 模穴 202 下組件 300 支撐裝置 206 底座 302 底端支樓襯塾 208 仿形上機翼套 304 頂端支撐襯墊 210 内侧端 306、 308變速箱 212 外側端 310 底座 214、 216導軌面 312、 314構件 218 斜面 320 角形凸緣 222 圓錐體 322 開口 224 螺栓 324 螺栓 226 推銷凹座 326、 328導件 228 推銷 329 變速箱固定板 230 推輪 330 導面 234 真空源 334、 336曲柄 236 導管 338 起重裝置 238 開口 400 前緣覆套安裝裝置 240 彈簧加載式工具 402 下組件 翼片插銷 404 底座 242 胎膜板 406 氣壓缸 (請先閱讀背面之注意事項再填寫本頁) 本紙張尺度適用中國國家標準（CNS ) Α4規格（210X297公釐） 30 經满部中央標率局員工消費合作社印m 412457 A7 B7 五、發明説明（28 ) 408 平移構件 450 上組件 410 加壓空氣組 451 後膜推銷凹座 412 托架構件 452 支柱 414 吸盤 454 仿形夾板 416 真空泵 456 圍道曲面 418 真空蓄壓器 458 鉸接固定構件 420 前緣覆套仿形套 460 工具翼片插銷 422 導管 462 回轉輪 424 閥門 464 差速器 ----------I------IT-------0 (請先閱讀背面之注意事項再填寫本\3;) 本纸張尺度適用中國國家標準（CNS ) A4規格（210X297公釐） 31-24-Printed by the Central Standards Bureau Offshore Consumer Cooperatives ^ «2457 A7 s * ---_____ B7___ V. Description of the invention (22) 'In the correct position, the flexible impervious diaphragm 254 covers the paddle Leaf subassembly! 32 and the contoured upper wing cover 208, thereby forming a closed mold cavity 258 therebetween. In step 528, the vacuum source 234 is activated to exhaust the air in the cavity 258. In the illustrated embodiment, the vacuum pressure provided by the vacuum source 234 is approximately equal to 44- 02 kPa (13 in. Hg). Exhausting air from the cavity 258 causes the flexible, water-impermeable membrane 254 to be pulled toward the contoured upper wing sleeve 208, thereby providing compression to the components of the blade subassembly 132. In step 530, the vacuum source 234 is turned off, the support structure 252 is turned back to the first position, and the flexible impervious diaphragm 254 no longer covers the blade sub-assembly 132. To prepare to remove the compressed blade sub-assembly 132 from the blade tightening device 200, the bag filter 244, the membrane sheet 242, the leading edge pusher 230, and the rear membrane pusher 228 must all be removed. In steps 532 and 534, the bottom support pad 302 is connected to the bottom gearbox 308 again, and the top support pad 304 is connected to the bottom gearbox 306 again, and then the two gearboxes 306, 308 are sequentially re-used. Connected to the hoisting rope 340, the blade sub-assembly 132 is supported by the hoisting device 338. In step 536, the bolt 224 is loosened, and the guides 326, 328 slide out of the inclined surface 218, so that the bottom support pad 302 and the top support pad 304 are no longer affected by the blade pressing device 200. The blade sub-assembly 132 is then sent from the blade pressing device 200 to the leading edge shroud installation device 400 by the support device 300. For the method of installing the leading edge cover, see the blade sub-assembly η ?, support device 300, and leading edge cover installation device 400 illustrated in Figures 3A-D and 7-11, and refer to Figure η. The paper dimensions are applicable to China. National Standard (CNS) A4 specification (2 丨 0X297mm),. I ------ IT ------ ^ (Please read the notes on the back before filling this page) 412457 Central Bureau of Standards, Ministry of Economic Affairs舅 工 消费 合 合作 印 1Ϊ A7 B7 V. Flowchart of the description of the invention (23), we will now discuss in more detail a method of installing the leading edge cover 120 and the pressing blade subassembly 13 2 together] vil . In step 600, when the leading edge cover 120 in the leading edge cover installation device 400 is configured, the suction cups 414 in the opposite row are checked to ensure that the suction cups 414 are in the disengaged position, and the suction cups 414 in the opposite row are arranged. They are separated by a distance greater than the width WLES of the leading edge cover 120 (see Figure 3C). In step 602, the leading edge cover 120 is disposed within the leading edge cover profile 420, and is positioned in the wing length direction by docking the top edge of the leading edge cover 120 to a tool stop (not shown). . In step 604, the suction cups 414 of the opposite row are pushed into a occlusion position by the air pressure red 406, so that each of the suction cups 414 engages with the outer mold line (OML) surface of the tail edge of the leading edge cover 120. In step 606, the vacuum pump 416 is activated, so that the vacuum pressure is accumulated in each corresponding vacuum accumulator 418. In step 608, the valve 424 is opened, so that the vacuum pressure accumulated in the vacuum accumulator 418 acts on the suction cups 414, thereby generating suction between each of the suction cups 414 and the OML surface of the leading edge cover 120. In the described embodiment, each suction cup 414 has a bellows-shaped design, so that when the valves 424 are opened, the bellows-shaped portion of each suction cup 414 sinks, so that the leading edge covers the OML surface of the tail edge of the machine 120 It is pulled toward the opposite frame member 412. In the illustrated embodiment, the suction cups 414 are constructed to form a bellows-shaped portion of each suction cup 414 when the generated vacuum pressure is between approximately 67 kPa 3 kPa and 84.66 kPa (20 in.Hg and 25 in.Hg). The sinking is about 1.27 em (0.5 in.), And the leading edge cover 120 width WLES is increased by about 2.54 cm (l in.). In another embodiment, the design of the suction cup 414 and the magnitude of the suction force acting on the suction cup 414 may be from the described embodiment. The X degree of the paper is adapted to the Chinese National Standard {CNS) A4 (210X297 mm) 26, 1 --- --- 1T ------- ^ (Please read the notes on the back before filling out this page) Printed by the Central Standards Bureau of the Ministry of Economic Affairs and Consumer Cooperatives of the Ministry of Economic Affairs 412457 A7 ______________ V. Description of the Invention (24) Modified In order to increase or decrease the opening degree of the leading edge cover 120. In addition, the opposing suction cups 414 can be moved by using the air pressure sensor 406 to keep them away from each other, and the leading edge cover 120 can be further expanded. Before disposing the blade sub-assembly 132 and the leading edge cover installation device 400 together, a bonding agent (not shown) can be applied on the leading edge 133 of the blade sub-assembly 132 (see FIG. 9), thereby adhering. The leading edge cover 120 is attached to the blade sub-assembly 132. In step 610, the bottom end of the support device 300 and the top gearboxes 306, 308 are adjusted to ensure that the blade sub-assembly 132 is generally vertical, and the leading edge 133 of the blade sub-assembly 132 faces downward. In step 612, the rear film push pin 228 is inserted into the rear film push pin recess 451 in the assembly 450 above the leading edge cover installation device 400, and the contoured splint 454 is in an open state, so that the hinged fixing member 458 is positioned around the periphery. The far side of the road surface 456. In step 614, the blade sub-assembly 132 is sent by the supporting device 300 to the opened profiling lost plate 454 and is disposed therein, so that the rear membrane latch 228 passes through the positioning openings in the upper wing skin 11 and the core 114. 134 and pass the tool blade insert pin 460 through the corresponding tool blade opening 132 to ensure that the blade sub-assembly 132 is correctly positioned in the leading edge cover installation device 400. In step 616, the profiling splint 454 is in a closed state, so that the hinge fixing member 458 is in contact with the wing skin 112 under the blade sub-assembly 132, thereby fixing the blade sub-assembly 132 within the profiling splint 454. In step 618, the bottom gearbox 308 is disengaged from the bottom support pad 302 and the top gearbox 306 is disengaged from the top support pad 304. In step 620, the profiling splint 454 is translated downward by the rotary wheel 462, so that the paper size of the paddle blade is in accordance with the Chinese National Standard (CNS) A4 specification (2 丨 0X297). 27 ------- -, i ------ ^ ------ t (Please read the notes on the back before filling in this page} Printed by the Shell Standard Consumer Cooperative of the Central Standards Bureau of the Ministry of Economic Affairs 412457 A7 ---- .. __ ___B7 i. Description of the invention (25) The leading edge 133 of the component 132 is inserted into the expanded leading edge cover 120. In step 622, the leading edge 133 and the leading edge cover 120 of the blade sub-assembly 132 are visually checked. In order to ensure that the leading edge 133 of the blade sub-assembly 132 is correctly inserted into the leading edge cover 120, the trailing edge of the leading edge cover 120 is overlapped with both the upper wing skin 110 and the lower wing skin 112. Especially Step 622 is a check to ensure that the trailing edge of the leading edge cover 120 does not cause separation between the upper wing skin 110 or the lower wing skin 112 and the spar assembly 116. In step 624, it is connected to the duct 422 The valve 424 disposed together is closed, so that the vacuum pressure applied to each suction cup 414 is interrupted, which causes the leading edge cover 120 and the blade sub-assembly 132 The edges 133 are assembled together. In step 626, the profiling splint 454 is translated upwards by the turning wheel 462, so that the assembled main rotor blade 100 passes the leading edge 102 over the opposite suction cup 414. In step In 628 and 630, the bottom support pad 302 is connected to the bottom gearbox 308, and the top support pad 304 is connected to the top gearbox 306, and then the two gearboxes 306, 308 are connected to the lifting rope in order. 340, and the main rotor blade 100 is supported by the lifting device 338. In steps 632 and 634, the profiling splint 454 is opened, and the main rotor blade 100 is separated from the tool blade pin 460 and the rear membrane push pin 228, so that The main rotor blade 100 can be pushed by the support device 300 to a distance β to the front cover installation device 400. It will be easy to see for those skilled in the art that the present invention achieves all the above-mentioned objectives. After the specifications of this item, those with ordinary skills will be able to complete the various changes, equivalent replacements, and other aspects of the invention widely discussed here. Therefore, the protection recognized here will only be covered by the scope of patents and their equivalents in the attached application. By definition . This paper is suitable for home finance (21Qx297). ---.---- d ------------ Girl (Please read the precautions on the back before filling this page) Γ 412457 A7 B7 V. Description of the invention (26 Component labeling comparison table Printed by the Ministry of Economic Affairs of the Standards Bureau Shellfish Consumer Cooperatives Co., Ltd. 10 Compression fixture 62 '62 Pneumatic cylinder 12 Upper wing skin 64 Vacuum source 14 Core 100 Main rotor blades 16 Spar assembly 102 leading edge 18 lower wing skin 104 trailing edge 22 leading edge cover 106 bottom 24 blade subassembly 108 top 26 lower component 109 top cover 28 contoured upper wing cover 110, 112 wing skin 30 Support structure 114 core 31 cutter pin 116 spar assembly 32 upper assembly 117 spar 34 pressure bag 117A opening 36 support plate 118 counterweight 38 structural support truss 119 rear diaphragm block 39 push pin 120 front edge cover 40 spar strut 121 cone Body 42 Front edge 122 Layer 50 Cover expansion / insertion device 123 Longitudinal axis 52 Movable strut 124 First _Strip 54 > 56 Frame member 126 Second wear-resistant slat 58, 60 Suction cup 130 Tool wing paper Standards apply Chinese National Standard. (CNS) A4 (210X 297mm) 29 1- I---H. ^ n--I ------ .... Ding Jv ° (Please read the notes on the back before filling this page) 412457 A7 B7 V. Description of the invention (27) Member of the Central Standards Bureau of the Ministry of Economic Affairs and the Consumer Cooperative Cooperative Association ^ 131 Opening 244 Bag filter 132 Paddle subassembly 250 Upper assembly 133 Leading edge 252 Support structure 134 Positioning opening 254 Impervious diaphragm 136 Structural reinforcement point 256 Polar axis 200 Paddle pressing device 258 Mold cavity 202 Lower component 300 Supporting device 206 Base 302 Bottom support lining 208 Contour upper wing cover 304 Top support pad 210 Inner end 306, 308 Gearbox 212 Outer end 310 Base 214, 216 Guide surface 312, 314 member 218 Bevel 320 angle flange 222 cone 322 opening 224 bolt 324 bolt 226 push pin recess 326, 328 guide 228 push pin 329 transmission fixing plate 230 push wheel 330 guide surface 234 vacuum source 334, 336 crank 236 conduit 338 lifting device 238 opening 400 front edge cover installation device 240 spring-loaded tool 402 lower component flap pin 404 base 242 membrane plate 406 pneumatic cylinder ( (Please read the notes on the back before filling this page) This paper size is applicable to Chinese National Standard (CNS) A4 specification (210X297 mm) 30 Printed by the Central Standards Bureau Staff Consumer Cooperatives m 412457 A7 B7 V. Invention Description (28 ) 408 translation member 450 upper assembly 410 pressurized air group 451 rear membrane push-out recess 412 bracket member 452 support 414 suction cup 454 profiled splint 416 vacuum pump 456 wall curved surface 418 vacuum accumulator 458 hinged fixing member 420 front edge cover Profiling sleeve 460 Tool wing pin 422 Conduit 462 Slewing wheel 424 Valve 464 Differential ---------- I ------ IT ------- 0 (Please read first Note on the back then fill in this \ 3;) This paper size is applicable to China National Standard (CNS) A4 specification (210X297 mm) 31

Claims (1)

申請專利範園 翼 第871〇576〇號專利申請案申請專利範圍修正本 修正日期：89年5月 h 一種組裝直昇機主旋翼㈣次組件之裝置，該次組件 匕括有境下機翼表皮'一個型芯、-塊上機翼表皮、 、及個具有-頂端與一底端之翼梁組件，該裝置包 括有： (a) 一個下組件，其皂括有 一個具有一仿形上機翼套之底座，該仿形上機 套具有一個底端和一個頂端， 配置在該仿形上機翼套近侧之第一及第二導軌 面’該第一導軌面係配置在該底端近側，而該第二 導軌面配置在該頂端近側，以及 多個配置在該仿形上機翼套近側之前緣推輪； (b) 個用以和該下組件匹配之上纟且件，其包括有一個 支揮結構和一個由該支撐結構支撐之撓性不透水隔 膜；以及 (c) 該撓性不透水隔膜與該仿形上機翼套於該上組件與 該下組件咬合時在其間界定了—個模穴。 2.如申請專利範圍第1項之裝置，其更包括有： (a) —個頂端支撐襯墊，其與該翼梁組件之該頂端一起 使用； (b) —個底端支撐襯墊，其與該翼梁組件之該底端一起 使用：以及 (c) 該頂端支撐襯墊與該底端支撐襯墊每個均具有導面 本紙張尺度適用中國國家榇準（CNS ) A4規格（210X297公釐） (請先閱讀背面之注意事項再填寫本頁> 訂 經濟部智慧財產局員工消費合作杜印製 32Apply for a patent Fan Yuanyi No. 871057660 Patent Application Application Amendment to the Patent Scope Amendment Date: May 89h h A device for assembling a helicopter main rotor sub-assembly, which sub-frames the surface of the under-wing wing skin ' A core, an upper wing skin, and a spar assembly having a top end and a bottom end, the device includes: (a) a lower assembly including a contoured upper wing The base of the sleeve, the contoured upper casing has a bottom end and a top end, and the first and second guide rail surfaces disposed near the contoured upper wing casing. The first rail surface is disposed near the bottom end. Side, and the second guide surface is arranged near the top end, and a plurality of push wheels arranged near the leading edge of the contoured upper wing cover; (b) upper and lower parts for matching the lower component; Including a support structure and a flexible water-impermeable membrane supported by the support structure; and (c) the flexible water-impermeable membrane and the contoured upper wing are sleeved when the upper component engages with the lower component A mold cavity was defined in between. 2. The device according to item 1 of the patent application scope, further comprising: (a) a top support pad used with the top of the spar assembly; (b) a bottom support pad, It is used with the bottom end of the spar assembly: and (c) the top support pad and the bottom support pad each have a guide surface. This paper size is applicable to China National Standard (CNS) A4 (210X297). (Mm) (Please read the precautions on the back before filling out this page> Order the consumer cooperation of the Intellectual Property Bureau of the Ministry of Economic Affairs Du printed 32 申請專利範園 翼 第871〇576〇號專利申請案申請專利範圍修正本 修正日期：89年5月 h 一種組裝直昇機主旋翼㈣次組件之裝置，該次組件 匕括有境下機翼表皮'一個型芯、-塊上機翼表皮、 、及個具有-頂端與一底端之翼梁組件，該裝置包 括有： (a) 一個下組件，其皂括有 一個具有一仿形上機翼套之底座，該仿形上機 套具有一個底端和一個頂端， 配置在該仿形上機翼套近侧之第一及第二導軌 面’該第一導軌面係配置在該底端近側，而該第二 導軌面配置在該頂端近側，以及 多個配置在該仿形上機翼套近側之前緣推輪； (b) 個用以和該下組件匹配之上纟且件，其包括有一個 支揮結構和一個由該支撐結構支撐之撓性不透水隔 膜；以及 (c) 該撓性不透水隔膜與該仿形上機翼套於該上組件與 該下組件咬合時在其間界定了—個模穴。 2.如申請專利範圍第1項之裝置，其更包括有： (a) —個頂端支撐襯墊，其與該翼梁組件之該頂端一起 使用； (b) —個底端支撐襯墊，其與該翼梁組件之該底端一起 使用：以及 (c) 該頂端支撐襯墊與該底端支撐襯墊每個均具有導面 本紙張尺度適用中國國家榇準（CNS ) A4規格（210X297公釐） (請先閱讀背面之注意事項再填寫本頁> 訂 經濟部智慧財產局員工消費合作杜印製 32 A8 68 C8 _______ D8 六、申請~ 及導件，與該導軌面一起將該翼梁組件朝弦長及翼 長方向定位於該仿形上機翼套上面。 3.如申請專利範圍第2項之裝置，其中每個該導軌面包 括有： (a) 界定於其内並終止於一圓錐體處的一個斜面’藉以 該斜面能夠與該導件咬合；以及 (b) 大體上平行於筚斜面的一根螺栓，該螺栓能夠相對 於該圓錐體而移動，藉使該螺栓能夠於該導件和該 斜面咬合時將該導件推向該圓錐體。 4·如申請專利範圍第1項之裝置，其更包括有： 0)—個接至該頂端支撐概墊之頂端變速箱；以及 (b) —個接至該底端支撐襯墊之底端變速箱； (c) 該須端及該底端變速箱能夠使該翼梁組件或該直昇 機主旋翼槳葉次组件繞著該翼梁組件的一根縱軸旋 轉，並能使該翼梁組件或該直昇機主旋翼槳葉次組 件大體上朝垂直方向移動。 5. 如申請專利範圍第4項之裝置，其更包括有： 一個接至該頂端及該底端變速箱之起重裝置，該起 重裝置能夠朝大體上垂直與大體上水平之方向移動該翼 梁組件或該直昇機主旋翼槳葉次组件。 6. 如申請專利範圍第1項之裝置，其中該下組件更包括 有一個真空源，其具有多條從該處延伸之導管，且其 中該仿形上機翼套具有多個開口，該導管係接至該開 口而互相流通，藉使該真空源能夠從該模穴中排出空 本紙張尺度適用中國國家標準（CNS ) A4規格（210X297公釐） {請先聞讀背面之注^h項再填寫本頁) 訂 經濟部智慧財產局員工消費合作社印製 33 經濟部智慧財產局員工消費合作社印製 j j A A AS 412457 ll _- _ D8 六、申請專利範圍 氣。 7. 如申請專利範圍第1項之裝置，其中該直昇機主旋翼 槳葉次組件更包括有多個接至該處之後緣工具翼片， 每個後緣工具翼片内均定了一個開口，並且其中 該下組件更包括有多個配置在該仿形上機翼套近側 之彈簧加載式後緣工具翼片插銷，藉使該彈簧加載式後 緣工具翼片插銷能夠插入該後緣工具翼片之開口内，以 促進直昇機主旋翼槳葉次組件在該下組件上面的正確翼 長及弦長方向定位。 8. —種裝配直昇機槳葉次組件之方法，該槳葉次組件包 括有一塊下機翼表皮、一個具有一圓錐體於其内形成 之型思、一塊上機翼表皮、以及一個具有一頂端與一 底端之翼梁組件，該方法步驟包括： (a)提供一個具有一下組件之槳葉緊壓裝置，該下組件 係與一上組件咬合， 該下組件包括有 一個具有一仿形上機翼套之底座，該仿形上機翼 套具有一個底端與一個頂端， 至少兩個配置在該仿形上機翼套近側之導軌面， 該導軌面於其内界定了圓錐體，至少其中—個該導軌 面係配置在該底端近側，且至少其中一個該導轨面係 配置在該頂端近側，以及 多個配置在該仿形上機翼套近侧之前緣推輪， 該上組件包括有 本紙張尺度適用中國菌家祿準（CNS) A4規格（210X297公;^ ) (請先閱讀背面之注意事項再填寫本I) .1T .丨線- 34 經濟部智慧財產局員工消費合作钍印製 41245? g88 __ _ >^^^1·· ^—— - --- 六、申請專利範圍' 一個用以支撐一撓性不透水隔膜之支撐結構，該 換性不透水隔膜與該仿形上機翼套於該上组件與該下 組件咬合時在其間界定了一個模穴； (b) 將該上機翼表皮及該型芯與該仿形上機翼套配置在 一起： (c) 將一頂端支撐襯墊與該翼梁组件之該頂端接在一 起，並將一底端夫撐襯墊與該翼梁組件之該底端接 在起，該頂端支撑概塾與該底端支撑觀塾每個均 具有導面及導件，與該導執面一起使用： (d) 藉由對接至少其中—個該導面與至少其中一個該導 軌面，將該翼梁組件朝翼長方向定位於該仿形上機 翼套中； (e) 藉由將該導件插入該導軌面之圓錐體内，並利用該 前緣推輪將該翼梁組件插入該型芯之園錐體内，而 朝弦長方向將該翼梁組件定位於該仿形上機翼套 内； (0將該下機翼表皮與該型芯及該翼梁組件配置在一起 而形成直昇機葉次組件； (g) 使該上組件與該下組件咬合；以及 (h) 從該模穴令排出空氣，藉以排出造成該撓性不透水 隔膜對直昇機槳葉次組件施以緊壓力量之空氣。 9.如申請專利範圍第8項之方法’其步驟更包括在進行 該上組件與該下組件的咬合步驟之前，於該槳葉次組 件上安裝一胎模板及一袋式過濾器之步驟。 本紙張逋用中國g家椟準（CNS) A现^ (21(5><297公着)-~~ ---- _ p . In Hi I n 社 (n (锖先閱讀背面之注意事項再填寫本頁) *1T 線， -35 - 經濟部智慧財產局員工消費合作社印製 AS B8 C8-έίΜ^Ί_-々、申請專利範園 10. 如申請專利範圍第8項之方法，其中該下組件更包括 有一個真空源，該真空源其具有多條從該處延伸並終 止於該仿形上機翼套内之多個相對應開口的導管，藉 使該真空源能夠將該空氣從該模穴中排出。 11. 如申請專利範圍第8項之方法，其更包括有一個用以 接至該頂端支撐襯墊之頂端支撐组件，以及一個接至 該底端支撐襯墊之底端支撐組件，該頂端支撐組件及 該底端支撐組件係以活動方式支撐該翼梁組件或該槳 葉次組件》 12. 如申請專利範圍第11項之方法，其中該頂端支撐組 件及該底端支撐組件包括有： 一個接至該頂端支撐襯墊之頂端變速箱和一個接至 該底端支撐襯墊之底端變速箱，該頂端及該底端變速 箱係以活動方式將該翼梁組件或該槳葉次組件繞著該 翼梁組件的一根縱軸旋轉，並以活動方式使該翼梁組 件或該槳葉次組件大體上朝垂直方向平移；以及 一個接至該頂端及該底端變速箱之起重裝置，該起 重裝置係以活動方式將該翼梁組件或該槳葉次組件朝 大趙上垂直的一個方向或大體上水平的一個方向平 移0 (請先閣讀背面之注意事項再填寫本頁) 本紙張尺度適用_國國家標準（CNS ) A4規格（210X297公釐） 36Apply for a patent Fan Yuanyi No. 871057660 Patent Application Application Amendment to the Patent Scope Amendment Date: May 89h h A device for assembling a helicopter main rotor sub-assembly, which sub-frames the surface of the under-wing wing skin ' A core, an upper wing skin, and a spar assembly having a top end and a bottom end, the device includes: (a) a lower assembly including a contoured upper wing The base of the sleeve, the contoured upper casing has a bottom end and a top end, and the first and second guide rail surfaces disposed near the contoured upper wing casing. The first rail surface is disposed near the bottom end. Side, and the second guide surface is arranged near the top end, and a plurality of push wheels arranged near the leading edge of the contoured upper wing cover; (b) upper and lower parts for matching the lower component; Including a support structure and a flexible water-impermeable membrane supported by the support structure; and (c) the flexible water-impermeable membrane and the contoured upper wing are sleeved when the upper component engages with the lower component A mold cavity was defined in between. 2. The device according to item 1 of the patent application scope, further comprising: (a) a top support pad used with the top of the spar assembly; (b) a bottom support pad, It is used with the bottom end of the spar assembly: and (c) the top support pad and the bottom support pad each have a guide surface. This paper size is applicable to China National Standard (CNS) A4 (210X297). (Mm) (Please read the precautions on the back before filling in this page> Order the consumer cooperation of the Intellectual Property Bureau of the Ministry of Economic Affairs, Du printed 32 A8 68 C8 _______ D8 VI. Application ~ and guide, together with the guide surface The spar assembly is positioned on the contoured upper wing cover towards the chord length and wing length direction. 3. As for the device in the scope of patent application item 2, each of the guide rail surfaces includes: (a) defined in it and An inclined plane terminating at a cone, whereby the inclined plane can engage the guide; and (b) a bolt substantially parallel to the sloping plane, the bolt being able to move relative to the cone, whereby the bolt Able to engage the guide and the bevel The guide member is pushed toward the cone at the time. 4. As the device of the scope of patent application No. 1, it further includes: 0) a top gearbox connected to the top support pad; and (b)-a A bottom-end gearbox connected to the bottom-end support pad; (c) the whisker and the bottom-end gearbox enable the spar assembly or the helicopter main rotor blade subassembly to surround one of the spar assembly The longitudinal axis rotates and can move the spar assembly or the helicopter main rotor blade sub-assembly substantially in a vertical direction. 5. If the device in the scope of patent application No. 4 further includes: a lifting device connected to the top and bottom transmissions, the lifting device can move the direction substantially vertical and substantially horizontally A spar assembly or a helicopter main rotor blade subassembly. 6. The device of claim 1, wherein the lower assembly further includes a vacuum source having a plurality of ducts extending therefrom, and wherein the contoured upper wing cover has a plurality of openings, and the duct It is connected to the opening and communicates with each other, so that the vacuum source can discharge the empty paper from the cavity. The size of the paper is applicable to China National Standard (CNS) A4 (210X297 mm). {Please read the note ^ h on the back first (Fill in this page again) Order Printed by the Employees 'Cooperatives of the Intellectual Property Bureau of the Ministry of Economic Affairs 33 Printed by the Employees' Cooperatives of the Intellectual Property Bureau of the Ministry of Economic Affairs jj AA AS 412457 ll _- _ D8 6. The scope of patent application. 7. If the device of the scope of patent application is applied for, the main rotor blade sub-assembly of the helicopter further includes a plurality of trailing edge tool blades connected thereto, and an opening is defined in each trailing edge tool blade, And the lower component further includes a plurality of spring-loaded trailing edge tool wing pins disposed near the contoured upper wing sleeve, so that the spring-loaded trailing edge tool wing pins can be inserted into the trailing edge tool The opening of the airfoil is used to facilitate the correct positioning of the main rotor blade sub-assembly of the helicopter on the lower assembly and the chord length direction. 8. A method of assembling a helicopter blade sub-assembly, the blade sub-assembly includes a lower wing skin, a shape having a cone formed therein, an upper wing skin, and a top With a bottom spar assembly, the method steps include: (a) providing a blade pressing device with a lower assembly, the lower assembly is engaged with an upper assembly, and the lower assembly includes a contoured upper The base of the wing cover, the contoured upper wing cover has a bottom end and a top end, at least two guide surfaces arranged near the contoured wing cover, the guide surface defining a cone inside, At least one of the guide rails is disposed near the bottom end, and at least one of the guide rails is disposed near the top end, and a plurality of front edge push wheels are disposed near the contour of the wing cover. The upper package includes the paper size applicable to China ’s bacteria standard (CNS) A4 (210X297); ^ (Please read the notes on the back before filling in this I). 1T. 丨 Line-34 Intellectual Property of the Ministry of Economic Affairs Bureau employee consumption钍 Printed 41245? G88 __ _ > ^^^ 1 ·· ^ ——---- VI. Scope of Patent Application 'A support structure to support a flexible water-impermeable membrane, which The contoured upper wing cover defines a cavity therebetween when the upper component and the lower component are engaged; (b) the upper wing skin and the core are configured with the contoured upper wing cover: (c) A top support pad is connected to the top end of the spar assembly, and a bottom end support pad is connected to the bottom end of the spar assembly. The top support is generally connected to the The bottom support views each have a guide surface and a guide member for use with the guide surface: (d) By butting at least one of the guide surface and at least one of the guide surface, the spar assembly is directed toward The wing length is positioned in the contoured upper wing cover; (e) by inserting the guide into the cone of the guide surface, and using the leading edge pusher to insert the spar assembly into the core garden Inside the cone, and position the spar assembly in the contoured upper wing cover towards the chord length direction; (0 the lower wing skin and the The core and the spar assembly are arranged together to form a helicopter blade subassembly; (g) the upper assembly is engaged with the lower assembly; and (h) air is exhausted from the cavity to cause the flexible impermeability The diaphragm applies a tight amount of air to the helicopter blade sub-assembly. 9. The method according to item 8 of the patent application, the steps of which further include performing the step of engaging the upper component and the lower component before the blade sub-assembly. The steps of installing a tire template and a bag filter on the module. This paper uses China National Standard (CNS) A Now ^ (21 (5 > &297; by the public)-~~ ---- p . In Hi I n 社 (n (锖 Please read the notes on the back before filling in this page) * 1T line, -35-Printed by ASB8 C8-έίΜ ^ Ί_-々, patent application by the Intellectual Property Bureau Staff Consumer Cooperatives, Ministry of Economic Affairs Fan Yuan 10. The method of claim 8 in which the lower assembly further includes a vacuum source having a plurality of vacuum sources extending from there and terminating in the contoured upper wing cover. Corresponding opening duct, so that the vacuum source can expel the air from the cavity11. If the method of claim 8 is applied, it further comprises a top support assembly for connecting to the top support pad, and a bottom support assembly for connecting to the bottom support pad, the top support The component and the bottom support component are used to movably support the spar component or the blade sub-component. "12. The method according to item 11 of the patent application, wherein the top support component and the bottom support component include: a A top gearbox connected to the top support pad and a bottom gearbox connected to the bottom support pad, the top and bottom gearboxes movably attach the spar assembly or the blade subassembly Rotate about a longitudinal axis of the spar assembly and move the spar assembly or the blade subassembly substantially vertically in a movable manner; and a lifting gear connected to the top and bottom gearboxes Device, the lifting device is to move the spar assembly or the blade sub-assembly to a vertical direction or a substantially horizontal direction on Da Zhao in a movable manner (please read the precautions on the back before filling This page) This paper scale applicable _ National Standards (CNS) A4 size (210X297 mm) 36
TW087105760A 1997-04-16 1998-04-15 Apparatus and method for assembling a helicopter main rotor blade subassembly TW412457B (en)

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US08/838,295 US5832605A (en) 1997-04-16 1997-04-16 Methods for fabricating a helicopter main rotor blade
US08/843,527 US5836062A (en) 1997-04-16 1997-04-16 Apparatus for assembling a helicopter main rotor blade subassembly

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JP4067574B2 (en) 2008-03-26
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CN1252754A (en) 2000-05-10
CN1064897C (en) 2001-04-25

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