【正文】 ly to ensure both that dimensional tolerances are met and that the curing process has been successful bubbles or voids in the laminate might have been formed as a result of contamination of the raw materials for example The Use of Composites in Aircraft Design Among the first uses of modern posite materials was about 30 years ago when boron reinforced epoxy posite was used for the skins of the empennages of the US F14 and F15 fighters Initially posite materials were used only in secondary structures but as knowledge and development of the materials has improved their use in primary structures such as wings and fuselages has increased The following table lists some air craft in which significant amounts of posite materials are used in the airframe Composites in Aerospace Applications Initially the percentage by structural weight of posites used in manufacturing was very small at around two percent in the F15 for example However the percentage has gr own considerably through 19 percent in the F18 up to 24 percent in the F22 The image below from Reference 1shows the distribution of materials in the F18EF aircraft The AV8B Harrier GR7 has posite wing sections and the GR7A features a posite rear fuselage Composite materials are used extensively in the Eurofighter the wing skins forward fuselage flaperons and rudder all make use of posites Toughened epoxy skins constitute about 75 per cent of the exterior area In total about 40 percent of the structure al weight of the Eurofighter is carbonfibrereinforced posite material Other European fighter typically feature between about 20 and 25 percent posites by weight 26 percent for Dassaults Rafael and 20 to 25 percent for the Saab Gripen and the EADS Mako The B2 stealth bomber is an interesting case The requirement for stealth means that radarabsorbing material must be added to the exterior of the air craft with a conitant weight penalty Composite materials are therefore used in the primary structure to offset this penalty The use of posite materials in mercial transport aircr aft is attractive because reduced airframe weight enables better fuel economy and therefore lowers operating costs The first significant use of posite material in a mercial aircraft was by Airbus in 1983 in the rudder of the A300 and A310 and then in 1985 in the vertical tail fin In the latter case the 2020 parts excluding fasteners of the metal fin was reduced to fewer than 100 for the posite fin lowering its weight and production cost Later a honeyb core with CFRP faceplates was used for the elevator of the A310Following these successes posite materials were used for the entire tail structure of the A320 which also featured posite fuselage belly skins finfuselage fairings fixed leading and trailingedge bottom access panels and deflectors trailingedge flaps and flaptrack fairings spoilers ailerons wheel doors main gear leg fairing doors and nacelles In addition the floor panels were made of GFRP In total posites constitute 28 per cent of the weight of the A320 airframe The A340500 and 600 feature additional posite structures including the rear pressure bulkhead the keel beam and some of the fixed leading edge of the wing The last is particularly significant as it constitutes the first largescale use of a thermoplastic matrix posite ponent on a mercial transport aircraft Composites enabled a 20 percent saving in weight along with a lower production time and improved damage tolerance The A380 is about 2022 percent posites by weight and also makes extensive use of GLARE glassfibrereinforced aluminium alloy which features in the front fairing upper fuselage shells crown and side panels and the upper sections of the forward and aft upper fuselage GLARE laminates are made up of four or more 038 mm 0015 in thick sheets of aluminium allo y and glass fibre resin bond film GLARE offers weight savings of between 15 and 30 percent over aluminium alloy along with very good fatigue resistance The top and bottom skin panels of the A380 and the front centre and rear spars contain。 s 經(jīng)過攤平拋光區(qū)溫度在 9001050 粘度為 10271032 Pa 03 MgO＞ 20177。畢業(yè)論文 450td 浮法玻璃原料車間工藝的初步設(shè)計 畢業(yè)設(shè)計論文 題目 450td 浮法玻璃原料車間工藝的初步設(shè)計 450td 浮法玻璃原料車間工藝的初步設(shè)計 摘 要 浮法玻璃是現(xiàn)如今生產(chǎn)平板玻璃的廣范使用方法并且原料車間又是浮法玻璃生產(chǎn)過程中的最為主要的環(huán)節(jié)本設(shè)計是 450td 浮法玻璃原料車間工藝的初步設(shè)計其主要是對浮法玻璃原料車間的設(shè)計方案和工藝流程進(jìn)行闡述原料車間的核心任務(wù)就是把質(zhì)量和粒度都符合要求的粉料經(jīng)破碎篩分等工藝流程制備成制定玻璃品種生產(chǎn) 過程中所需的配合料并最終送進(jìn)窯頭進(jìn)行熔制該環(huán)節(jié)過程中的精準(zhǔn)配料和生產(chǎn)過程中的穩(wěn)定運行決定了所生產(chǎn)玻璃質(zhì)量的優(yōu)劣因此在浮法玻璃原料車間設(shè)計中工藝方案的確定和裝備設(shè)備的選取尤為重要對于原料車間內(nèi)的合理化布局每一部分的緊密銜接都是保證玻璃質(zhì)量的關(guān)鍵本設(shè)計中主要敘述了現(xiàn)如今玻璃行業(yè)的發(fā)展情況和存在的問題原料成分的選取和配比計算設(shè)備選取和經(jīng)濟(jì)效益等部分最后通過手繪和 CAD 繪圖倆種方式對原料車間的整體布局進(jìn)行了繪制整個設(shè)計的內(nèi)容完整結(jié)合了生產(chǎn)過程中的實際情況對實際生產(chǎn)有一定的指導(dǎo)意義 關(guān)鍵詞浮法玻璃原料工藝流程平衡計算 450td float glass raw materials workshop process the preliminary design ABSTRACT Float glass is the production of flat glass is now a wide range of use and workshop materials is the most major part of the float glass production process The design is a process of preliminary design of the 450t d float glass workshop materials which is mainly described the design and process of float glass workshop materials The core task of the workshop materials to meet the requirements of quality and particle size powder by crushing and screening process was prepared with the materials needed in the development of varieties of glass production process and ultimately sent to the kiln head melting The link in the process of precise ingredients and production processes in the stable operation of the quality of glass pr