CN107514939B - 火箭复合材料壳体 - Google Patents
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Abstract
本发明属于火箭装置技术领域,并公开了一种火箭复合材料壳体,所述壳体由内至外依次包括内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层是由耐热橡胶制成,外耐热层是由耐热防冲刷材料制成,所述内隔热层和所述外隔热层是由隔热材料制成,所述承载层是由竹片缠绕多层并通过树脂粘结固化而成。通过本发明,采用竹复合材料制成壳体,尤其是对构成承载层的竹片尺寸、含水率、强度、缠绕方式及树脂进行具体设计,使制得的火箭复合材料壳体绿色环保、原材料资源可再生、防震、低摩擦、耐磨、隔热、耐烧蚀、耐冲刷、成本低。
Description
技术领域
本发明属于火箭装置技术领域,更具体地,涉及一种火箭复合材料壳体。
背景技术
火箭是一种燃气推进装置,其以热气流高速向后喷出,利用产生的反作用力向前运动。它自身携带燃烧剂与氧化剂,不依赖空气中的氧助燃,既可在大气中,又可在外层空间飞行。现代火箭可作为快速远距离运输工具,可以用来运载发射卫星和投送武器战斗部。火箭壳体一般是铝合金蒙皮和加强框架铆接而成的硬壳、半硬壳式结构。但铝合金壳体重量大,降低有效载荷量,于是考虑到用质轻高强的复合材料作为火箭壳体。目前常用的火箭复合材料壳体多为玻璃纤维、碳纤维、芳纶纤维缠绕制成,但是上述纤维会消耗有限的矿产资源,且原材料制造生产过程不环保,会对环境造成破坏。并且上述材料成本很高。
发明内容
针对现有技术的以上不足或改进需求,本发明提供了一种火箭复合材料壳体,其中通过利用竹材制成复合材料壳体,使得该火箭壳体资源可再生、绿色环保且成本低廉。
为实现上述目的,按照本发明,提供了一种火箭复合材料壳体,所述壳体由内至外依次包括内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层是由耐热材料制成,所述内隔热层和所述外隔热层是由隔热材料制成,所述承载层是由竹材缠绕多层并通过树脂粘结固化而成,所述外耐热层是由耐热防冲刷材料制成。
对于本发明的上述构思所形成的技术方案,承载层作为火箭复合材料壳体的主要结构,是由竹材缠绕制成,采用竹材作为原材料,绿色环保,资源可再生,不会受到资源限制,成本低;而且竹材质量轻,强度高,韧性好,利用高比强度、比模量的竹材采用缠绕工艺可以将其轴向拉伸强度发挥至最大化,使缠绕出的壳体力学强度高;为保护竹材缠绕而成的承载层不易受高温破坏结构,在其内外表面均设置隔热层,用以降低传导至承载层的温度,设置内衬垫层和耐热防冲刷层用以耐受火箭复合材料壳体内部和外部弹射过程高压、高温气动热冲击。
优选地,所述内衬垫层的耐热材料为耐热橡胶。
优选地,所述的隔热材料是生态陶瓷,所述内衬垫层与所述内隔热层之间、所述内隔热层与所述承载层之间、所述承载层与所述外隔热层之间、所述外隔热层与所述外耐热层之间均是通过胶粘剂粘接。
优选地,所述生态陶瓷为竹陶瓷或木陶瓷。
优选地,所述胶粘剂为环氧树脂胶粘剂。
优选地,所述承载层的树脂为难燃性氨基树脂。
优选地,所述竹材是宽度为5mm-20mm,厚度为0.3mm-2mm,长度为2m-6m的竹丝。
优选地,所述竹丝含水率不高于10%。
优选地,所述竹丝轴向拉伸强度不低于90MPa。
优选地,所述承载层的竹材缠绕方式是环向缠绕和螺旋缠绕的组合。
总体而言,通过本发明所构思的以上技术方案与现有技术相比,通过采用竹复合材料制成壳体,尤其是对构成承载层的竹材尺寸、含水率、强度、缠绕方式及树脂进行具体设计,使制得的火箭复合材料壳体绿色环保、原材料资源可再生、防震、低摩擦、耐磨、隔热、耐烧蚀、耐冲刷、成本低。
附图说明
图1是按照本发明优选实施方式所设计的火箭复合材料壳体的径向截面结构示意图;
在所有附图中,相同的附图标记用来表示相同的元件或结构,其中:
1-内衬垫层,2-内隔热层,3-承载层,4-外隔热层,5-外耐热层。
具体实施方式
为了使本发明的目的、技术方案及优点更加清楚明白,以下结合附图及实施例,对本发明进行进一步详细说明。应当理解,此处所描述的具体实施例仅仅用以解释本发明,并不用于限定本发明。此外,下面所描述的本发明各个实施方式中所涉及到的技术特征只要彼此之间未构成冲突就可以相互组合。
图1是按照本发明优选实施方式所设计的火箭复合材料壳体的径向截面结构示意图。如图1中所示,在一个实施例中,一种火箭复合材料壳体,所述壳体由内至外依次包括内衬垫层1、内隔热层2、承载层3、外隔热层4、外耐热层5,所述承载层3由竹材缠绕多层并通过树脂粘结固化而成,通过缠绕方式可以将竹材的轴向拉伸强度发挥至最大化,从而使缠绕出的承载层3达到承力要求。竹材可以为竹片、竹篾、竹丝、竹帘等,在本实施例中,所述竹材是宽度为5mm-20mm,厚度为0.3mm-2mm,长度为2m-6m的竹丝。该尺寸范围内的竹丝比强度、比模量高,一方面提高缠绕的密实度,从而提高壳体的强度,另一方面便于树脂渗透进入竹材中,增大粘结性能,使缠绕出的承载层力学性能好。竹丝含水率优选为不高于10%、轴向拉伸强度优选为不低于90MPa,以保证每根竹丝均具有高强度,控制其含水率以提高树脂的渗入率,提高粘结性能。在本实施例中,该树脂优选为难燃性氨基树脂,采用难燃性树脂,以增大承载层3的防燃烧性能。因为经过大量试验证明,氨基树脂与竹材的浸润性最好,从而可以使得固化后得到的承载层3粘结强度高。本实施例中优选将竹丝进行环向和螺旋组合缠绕方式,以保证得到的承载层各个方向均具有高强度。所述内衬垫层1用以耐受火箭壳体内部燃料燃烧导致的高温,由耐热材料制成,本实施例中具体为耐热橡胶。所述外耐热层5用以耐受外部弹射过程产生的高压、高温气动热冲击,由耐热防冲刷材料制成,具体可以为耐高温防冲刷涂料、碳纤维复合材料等材料。所述内隔热层2和所述外隔热层4用以隔绝热量向承载层3的传递,从而降低承载层3的温度,保护承载层3不受高温破坏,由隔热材料制成,具体可以为耐高温树脂、生态陶瓷等材料。
在另一实施例中,隔热层优选采用生态陶瓷制成,生态陶瓷的多孔结构具有优异的隔热效果,并且能够充分利用可再生资源,绿色环保。该生态陶瓷优选为竹陶瓷或木陶瓷,所述内衬垫层1与所述内隔热层2之间、所述内隔热层2与所述承载层3之间、所述承载层3与所述外隔热层4之间、所述外隔热层4与所述外耐热层5之间均是通过胶粘剂粘接。该胶粘剂具体为高强度的环氧树脂胶粘剂。
为了满足其他性能,还可以在壳体结构内设置其他功能层,如为达到电磁屏蔽效果,在壳体内还设置电磁屏蔽层。
下面将结合一些具体实施例来更为清楚地解释说明按照本发明的竹缠绕复合管制造工艺及其关键工艺参数设计。
实施例1
一种火箭复合材料壳体,所述壳体由内至外依次为内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层为耐热橡胶,所述内隔热层、外隔热层和外耐热层均是缠绕的碳纤维/环氧树脂复合材料,所述承载层是由竹片螺旋缠绕在所述内隔热层外表面多层并通过酚醛树脂粘结固化而成。具体制备过程如下:
(1)芯模处理:制备火箭壳体形状的芯模,在其表面涂覆脱模剂;
(2)内衬垫层成型:将耐热橡胶缠绕在芯模上,粘接成型,得到内衬垫层;
(3)内隔热层成型:采用碳纤维纱浸渍高温固化环氧树脂在内衬垫层上湿法螺旋缠绕,加热固化成型,得到内隔热层;
(4)承载层成型:将原竹剖分成竹片,尺寸不做限制,将竹片粘接成连续长状,浸渍酚醛树脂湿法螺旋缠绕在内隔热层上,加热固化成型,得到承载层;
(5)外隔热层和外耐热层成型:采用碳纤维纱浸渍高温固化环氧树脂在承载层上湿法螺旋缠绕,加热固化成型,得到外隔热层和外耐热层;
(6)脱模:将制备好的壳体从芯模上脱模,得到火箭壳体。
实施例2
一种火箭复合材料壳体,所述壳体由内至外依次为内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层为耐热橡胶,所述外耐热层是缠绕的高硅氧布/酚醛树脂复合材料,所述内隔热层和所述外隔热层是耐高温树脂,本实施例中具体为酚醛树脂,所述承载层是由宽度为5mm-20mm、厚度为0.3mm-2mm、长度为2m-6m的竹片通过环向缠绕在所述内隔热层外表面多层并通过环氧树脂粘结固化而成。具体制备过程如下:
(1)芯模处理:制备火箭壳体形状的芯模,在其表面涂覆脱模剂;
(2)内衬垫层成型:将耐热橡胶缠绕在芯模上,粘接成型,得到内衬垫层;
(3)内隔热层成型:将酚醛树脂均匀涂敷在内衬垫层表面,加热固化成型,得到内隔热层;
(4)承载层成型:将原竹剖分成宽度为5mm-20mm、厚度为0.3mm-2mm、长度为2m-6m的竹片,粘接成连续长状,浸渍环氧树脂湿法环向缠绕在内隔热层上,加热固化成型,得到承载层;
(5)外隔热层成型:将酚醛树脂均匀涂敷在承载层外表面,加热固化成型,得到外隔热层;
(6)外耐热层成型:采用高硅氧布浸渍酚醛树脂在外隔热层上缠绕,加热固化成型,得到外耐热层;
(7)脱模:将制备好的壳体从芯模上脱模,得到火箭壳体。
实施例3
一种火箭复合材料壳体,所述壳体由内至外依次包括内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层是耐热橡胶,外耐热层是缠绕的碳纤维/环氧树脂复合材料,所述内隔热层和所述外隔热层是粘接的生态陶瓷,具体为木陶瓷,所述承载层是由多个平行排列的竹片织成竹帘后环向缠绕在所述内隔热层外表面多层并通过难燃性氨基树脂粘结固化而成。具体制备过程如下:
(1)芯模处理:制备火箭壳体形状的芯模,在其表面涂覆脱模剂;
(2)内衬垫层成型:将耐热橡胶缠绕在芯模上,粘接成型,得到内衬垫层;
(3)内隔热层成型:将木粉干燥至含水率<10%,粉碎研磨至木粉粒径在30μm以下;将酚醛树脂与木粉混合搅拌均匀,两者质量比为30~70∶70~30,得到混合物;将混合物倒入事先制备好的火箭壳体形状环形石墨模具内,加热固化得到预烧坯体,然后将装有该预烧坯体的环形石墨模具放入裂解炉中在氮气保护下高温烧结,温度为650~1200℃,烧结制度为:升温速率为2-10℃/min,室温-200℃保温1h,200-650℃保温1h,650-800℃保温3-5h,800-1200℃保温2-5h,得到酚醛树脂强化木陶瓷内隔热层,将成型的内隔热层套装在成型的内衬垫层外表面,两者之间通过高强度耐温环氧树脂胶粘剂进行粘接,得到内隔热层;
(4)承载层成型:在内隔热层外表面涂覆高强度耐温环氧树脂胶粘剂,将原竹剖分成宽度为5mm-20mm、厚度为0.3mm-2mm、长度为2m-6m的竹片,将竹片沿其宽度方向平行排列若干个,再在其长度方向缝接为连续长的竹帘,浸渍难燃性氨基树脂在涂覆有环氧树脂胶粘剂的内隔热层上湿法环向缠绕,加热固化成型,得到承载层;
(5)外隔热层成型:制作方法同内隔热层,将成型的木陶瓷外隔热层套装在成型的承载层外表面,两者之间通过高强度耐温环氧树脂胶粘剂进行粘接,得到外隔热层;
(6)外耐热层成型:在外隔热层外表面涂覆高强度耐温环氧树脂胶粘剂,采用碳纤维纱浸渍高温固化环氧树脂在涂覆有环氧树脂胶粘剂的外隔热层上湿法螺旋与环向组合缠绕,加热固化成型,得到外耐热层;
(7)脱模:将制备好的壳体从芯模上脱模,得到火箭壳体。
实施例4
一种火箭复合材料壳体,所述壳体由内至外依次包括内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层为耐热橡胶材料,所述外耐热层是缠绕的碳纤维/环氧树脂复合材料,所述内隔热层和所述外隔热层是粘接的生态陶瓷,具体为竹陶瓷,所述承载层是由宽度为5mm-20mm、厚度为0.3mm-2mm、长度为2m-6m、含水率不高于10%、拉伸强度不低于90MPa的竹片通过环向和螺旋组合缠绕在所述隔热层外表面多层并通过难燃性氨基树脂粘结固化而成,具体制备方法如下:
(1)芯模处理:制备火箭壳体形状的芯模,在其表面涂覆脱模剂;
(2)内衬垫层成型:将耐热橡胶缠绕在芯模上,粘接成型,得到内衬垫层;
(3)内隔热层成型:将竹粉干燥至含水率<8%,粉碎研磨至竹粉粒径在30μm以下;将酚醛树脂与竹粉混合搅拌均匀,两者质量比为30~70∶70~30,得到混合物;将混合物倒入事先制备好的火箭壳体形状环形石墨模具内,加热固化得到预烧坯体,然后将装有该预烧坯体的模具放入裂解炉中在氮气保护下高温烧结,温度为650~1200℃,烧结制度为:升温速率为2-10℃/min,室温-200℃保温1h,200-650℃保温1-2h,650-800℃保温1-5h,800-1200℃保温1-5h,得到酚醛树脂强化竹陶瓷内隔热层,将成型的内隔热层套装在成型的内衬垫层外表面,两者之间通过高强度耐温环氧树脂胶粘剂进行粘接,得到内隔热层;
(4)承载层成型:在内隔热层外表面涂覆高强度耐温环氧树脂胶粘剂,将原竹剖分成宽度为5mm-20mm、厚度为0.3mm-2mm、长度为2m-6m的竹片,经过脱脂处理后干燥至含水率不高于10%,选取拉伸强度不低于90MPa的竹片粘接成连续长状,浸渍难燃性氨基树脂在涂覆有环氧树脂胶粘剂的内隔热层上湿法环向和螺旋组合缠绕,加热固化成型,得到承载层;
(5)外隔热层成型:制作方法同内隔热层,将成型的竹陶瓷外隔热层套装在成型的承载层外表面,两者之间通过高强度耐温环氧树脂胶粘剂进行粘接,得到外隔热层;
(6)外耐热层成型:在外隔热层外表面涂覆高强度耐温环氧树脂胶粘剂,采用碳纤维纱浸渍高温固化环氧树脂在涂覆有环氧树脂胶粘剂的外隔热层上湿法螺旋与环向组合缠绕,加热固化成型,得到外耐热层;
(7)脱模:将制备好的壳体从芯模上脱模,得到火箭壳体。
本领域的技术人员容易理解,以上所述仅为本发明的较佳实施例而已,并不用以限制本发明,凡在本发明的精神和原则之内所作的任何修改、等同替换和改进等,均应包含在本发明的保护范围之内。
Claims (5)
1.一种火箭复合材料壳体,其特征在于,所述壳体由内至外依次包括内衬垫层、内隔热层、承载层、外隔热层、外耐热层,所述内衬垫层是由耐热材料制成,所述内隔热层和所述外隔热层是由隔热材料制成,所述承载层是由竹材缠绕多层并通过树脂粘结固化而成,所述外耐热层是由耐热防冲刷材料制成;
所述竹材是宽度为5mm-20mm,厚度为0.3mm-2mm,长度为2m-6m的竹丝;所述竹丝含水率不高于10%;所述竹丝轴向拉伸强度不低于90MPa;所述承载层的竹材缠绕方式是环向缠绕和螺旋缠绕的组合;
所述的隔热材料为生态陶瓷,所述生态陶瓷为竹陶瓷或木陶瓷;
其中木陶瓷隔热层的成型方法为:将木粉干燥至含水率<10%,粉碎研磨至木粉粒径在30μm以下;将酚醛树脂与木粉混合搅拌均匀,两者质量比为30~70:70~30,得到混合物;将混合物倒入事先制备好的火箭壳体形状环形石墨模具内,加热固化得到预烧坯体,然后将装有该预烧坯体的环形石墨模具放入裂解炉中在氮气保护下高温烧结,温度为650~1200℃;
竹陶瓷隔热层的成型方法为:将竹粉干燥至含水率<8%,粉碎研磨至竹粉粒径在30μm以下;将酚醛树脂与竹粉混合搅拌均匀,两者质量比为30~70:70~30,得到混合物;将混合物倒入事先制备好的火箭壳体形状环形石墨模具内,加热固化得到预烧坯体,然后将装有该预烧坯体的模具放入裂解炉中在氮气保护下高温烧结,温度为650~1200℃。
2.如权利要求1所述的火箭复合材料壳体,其特征在于,所述内衬垫层的耐热材料为耐热橡胶。
3.如权利要求1所述的火箭复合材料壳体,其特征在于,所述内衬垫层与所述内隔热层之间、所述内隔热层与所述承载层之间、所述承载层与所述外隔热层之间、所述外隔热层与所述外耐热层之间均是通过胶粘剂粘接。
4.如权利要求3所述的火箭复合材料壳体,其特征在于,所述胶粘剂为环氧树脂胶粘剂。
5.如权利要求1所述的火箭复合材料壳体,其特征在于,所述承载层的树脂为难燃性氨基树脂。
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