CN105711804A - 一种飞机机身底部阻燃隔热吸音材料结构 - Google Patents
一种飞机机身底部阻燃隔热吸音材料结构 Download PDFInfo
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Abstract
一种飞机机身底部阻燃隔热吸音材料结构，其特征在于从外到内依次由外壳、泡沫、内壳及机身内底板组成；所述的外壳为碳纤维或玻璃纤维与树脂胶的高分子复合材料，泡沫为开孔泡沫，孔隙率95％～99％，容重6Kg/m3～15Kg/m3，成分为三聚氰胺，厚度为10mm～200mm，内壳为碳纤维增强塑料；其中泡沫放在外壳与内壳之间的空腔体内，腔体两侧的顶端各设有一个水阀，水阀间距为1m～5m，其与飞机上的储水箱相连接，水阀为电动开关，开关连线位于飞机前舱及后舱内。本发明的有益之处是①提高阻燃性；②隔热吸音；③泡沫轻质，阻燃方式简单实用且环保经济。
Description
技术领域
本发明涉及一种飞机机身底部材料结构，特别是涉及一种飞机机身底部阻燃隔热吸音材料结构。
背景技术
民用飞机机身底部结构阻燃性直接关系到发生迫降事故时乘客的安全与飞机的损失，是民用飞机机身结构设计的一个重要方面。保持机身结构完整性、使乘客享受舒适空间和避免飞机迫降着陆时漏油起火的危险是民用飞机机身结构阻燃性及隔热吸音性设计的三个主要目标。
随着人们对航空安全的重视程度越来越高，越来越多的学者和科研机构开始研究各种提高民用飞机阻燃性的方法。目前对民用飞机的阻燃性的研究主要集中在机身材料结构、起落架系统和飞机舱体及系统包括乘客座椅等这几个方面，其中机身结构阻燃性设计一直备受关注。
传统民用飞机的圆形截面机身底部和蒙皮/骨架金属薄壁结构，使得飞机在迫降时，机身底部与地面直接摩擦容易导致漏油起火，从而引发危险。所以解决飞机迫降时机身底部易着火的问题尤为重要。
申请公告号为CN101941521A的中国发明专利公开了一种高强度高安全复合材料轻型飞机机身结构。所述机身结构由玻璃纤维+碳纤维+树脂胶复合材料制作胶接而成的箱体结构，由π型机座、右大梁、前起落架支撑座、前机身中地板、左大梁、左侧梁、后机身隔框、右侧梁、右侧地板、地板前横梁、左侧地板、地板后横梁、机身蒙皮、行李仓隔板等通过胶接组成。在机身中段形成结实牢固的箱体结构，π型机座与机身蒙皮、右大梁、左大梁及前机身中地板胶接，使发动机连接安全可靠。本发明是一种以较轻的重量保证机身强度的结构，提高复合材料机身的结构强度和安全性的高强度高安全复合材料轻型飞机机身结构。
申请公告号为CN103625054A的中国发明专利公开了一种飞机机身外壳，包括蒙皮基材和防护涂层，该防护涂层包括一层锌黄丙烯酸聚氨酯底漆和两层氟碳面漆，所述氟碳面漆的A组分包括下列成分：高羟基含氟丙烯酸树脂、颜色填料、纳米氧化镁、纳米二氧化钛、流平剂、消泡剂、分散剂、催化剂和溶剂。根据本发明的飞机机身外壳能够更好地适应当前日益苛刻的飞行条件，提高了飞行安全性。
现有的飞机机身发明设计很少涉及机身阻燃性问题，一般都是选用阻燃性机身材料或添加阻燃性制备成复合材料作为机身蒙皮，本发明采用在机身底部外壳与内壳的空腔体内放入三聚氰胺泡沫，三聚氰胺可吸水亦可保水，当飞机迫降时，避免机身底部与地面摩擦导致漏油起火，可自动打开水阀，当泡沫吸入足够水后，可阻隔外面的火焰，保证乘客的安全，同时降低飞机的经济损失。本发明的设计不仅提高了阻燃性，泡沫的优异性能也为乘客提供了舒适的空间。
发明内容
本发明的目的在于克服现有飞机机身底部与地面摩擦易漏油起火的问题，提供一种飞机机身底部阻燃隔热吸音材料结构。
为实现本发明的目的，所采用的技术方案是：一种飞机机身底部阻燃隔热吸音材料结构，其特征在于从外到内依次由外壳、泡沫、内壳及机身内底板组成；所述的外壳为碳纤维或玻璃纤维与树脂胶的高分子复合材料，泡沫为开孔泡沫，孔隙率95％～99％，容重6Kg/m3～15Kg/m3，成分为三聚氰胺，厚度为10mm～200mm，内壳为碳纤维增强塑料；其中泡沫放在外壳与内壳之间的空腔体内，腔体两侧的顶端各设有一个水阀，水阀间距为1m～5m，其与飞机上的储水箱相连接，水阀为电动开关，开关连线位于飞机前舱及后舱内。
所述的高分子树脂为酚醛树脂和三聚氰胺树脂中的一种。
所述的内壳碳纤维抗拉强度大于5000Mpa，弹性模量大于260GPa，伸长率大于2.2。
所述的外壳玻璃纤维为无碱玻璃纤维。
本发明所具有的有益效果是：①突破传统飞机机身底部阻燃性差的限制，当飞机迫降，出现机身底部与地面摩擦使漏油起火等危险时，打开水阀，水流进泡沫中，泡沫吸水并保水，湿态可以阻隔火焰，另外泡沫本身难燃，其阻燃性大大提高，达到不燃；②泡沫的导热系数低及开孔率高，起到隔热吸音的作用，为乘客提供舒适环境；③泡沫容重低，不会增加飞机太多负载；④阻燃方式简单实用且环保经济。
附图说明
图1是一种飞机机身底部阻燃隔热吸音材料结构示意图。
图示中10为机身外壳，20为泡沫，30为机身内壳，40为水阀，50为机身内底板。
具体实施方式
下面结合具体实施例，进一步阐明本发明，应理解这些实施例仅用于说明本发明而不用于限制本发明的范围，在阅读了本发明之后，本领域技术人员对本发明的各种等价形式的修改均落于本申请所附权利要求所限定。
实施例1
一种飞机机身底部阻燃隔热吸音材料结构，其特征在于从外到内依次由外壳、泡沫、内壳及机身内底板组成；所述的外壳为碳纤维或玻璃纤维与树脂胶的高分子复合材料，泡沫为开孔泡沫，孔隙率95％，容重6Kg/m3，成分为三聚氰胺，厚度为10mm，内壳为碳纤维增强塑料；其中泡沫放在外壳与内壳之间的空腔体内，腔体两侧的顶端各设有一个水阀，水阀间距为1m，其与飞机上的储水箱相连接，水阀为电动开关，开关连线位于飞机前舱及后舱内。
所述的高分子树脂为酚醛树脂和三聚氰胺树脂中的一种。
所述的内壳碳纤维抗拉强度大于5000Mpa，弹性模量大于260GPa，伸长率大于2.2。
所述的外壳玻璃纤维为无碱玻璃纤维。
该结构阻燃方式简单：当飞机非正常降落，机身底部先于地面摩擦，造成机体漏油起火时，将水阀自动打开，往腔体内的泡沫注水，吸水的泡沫，将火焰阻隔。
实施例2
一种飞机机身底部阻燃隔热吸音材料结构，其特征在于从外到内依次由外壳、泡沫、内壳及机身内底板组成；所述的外壳为碳纤维或玻璃纤维与树脂胶的高分子复合材料，泡沫为开孔泡沫，孔隙率99％，容重15Kg/m3，成分为三聚氰胺，厚度为200mm，内壳为碳纤维增强塑料；其中泡沫放在外壳与内壳之间的空腔体内，腔体两侧的顶端各设有一个水阀，水阀间距为5m，其与飞机上的储水箱相连接，水阀为电动开关，开关连线位于飞机前舱及后舱内。
所述的高分子树脂为酚醛树脂和三聚氰胺树脂中的一种。
所述的内壳碳纤维抗拉强度大于5000Mpa，弹性模量大于260GPa，伸长率大于2.2。
所述的外壳玻璃纤维为无碱玻璃纤维。
该结构阻燃方式简单：当飞机非正常降落，机身底部先于地面摩擦，造成机体漏油起火时，将水阀自动打开，往腔体内的泡沫注水，吸水的泡沫，将火焰阻隔。
上述仅为本发明的两个具体实施方式，但本发明的设计构思并不局限于此，凡利用此构思对本发明进行非实质性的改动，均应属于侵犯本发明保护的范围的行为。但凡是未脱离本发明技术方案的内容，依据本发明的技术实质对以上实施例所作的任何形式的简单修改、等同变化与改型，仍属于本发明技术方案的保护范围。
Claims (4)
1.一种飞机机身底部阻燃隔热吸音材料结构，其特征在于从外到内依次由外壳、泡沫、内壳及机身内底板组成；所述的外壳为碳纤维或玻璃纤维增强的高分子树脂的复合材料，泡沫为开孔泡沫，孔隙率95％～99％，容重6Kg/m3～15Kg/m3，厚度为10mm～200mm，成分为三聚氰胺，内壳为碳纤维增强塑料；其中泡沫放在外壳与内壳之间的空腔体内，腔体两侧的顶端各设有一个水阀，水阀间距为1m～5m，其与飞机上的储水箱相连接，水阀为电动开关，开关连线位于飞机前舱及后舱内。
2.根据权利要求1所述的材料结构，其特征在于所述的高分子树脂为酚醛树脂和三聚氰胺树脂中的一种。
3.根据权利要求1所述的材料结构，其特征在于所述的内壳碳纤维抗拉强度大于5000Mpa，弹性模量大于260GPa，伸长率大于2.2。
4.根据权利要求1所述的材料结构，其特征在于所述的外壳玻璃纤维为无碱玻璃纤维。
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