CN111252256B - 一种基于电池封装的电动飞机系统 - Google Patents
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Abstract
本发明公开了一种基于电池封装的电动飞机系统,在左、右侧机翼的前、后梁之间设置若干翼肋,与前梁、后梁以及上、下蒙皮构成动力电池模组密闭安装舱,所述动力电池模组密闭安装舱内设置电池模组;在左、右侧机翼上还设置通风引气口、引气主管、引气歧管、引气歧管支管、出气歧管支管,所述引气歧管上设置引气管滞流阀,所述出气歧管支管上设置出气歧管滞流阀,气体通过通风引气口引入后,通过引气主管、引气歧管进入电池模组,再通过引气歧管支管进入电池模组电池块之间,最后通过出气歧管支管从电池模组电池块之间排出。本发明提升了电池模组的通风散热性能。
Description
技术领域
本发明涉及飞机能源系统,具体涉及一种基于电池封装的电动飞机系统。
背景技术
现有2-4座小型通用飞机动力系统均为燃油型,通过航空汽油或煤油的燃烧,将热能转换为机械能给飞机提供动力。传统燃油型飞机的燃烧排放物易造成环境污染,如燃烧排放物二氧化硫会造成酸雨,一氧化氮会破坏地球臭氧层等。随着人们的环境保护意识的提升,各研究单位开始将清洁的电能作为飞机动力能源。此外,电池在飞机爬升与巡航阶段会发热,因此,亟需设计一种飞机电池封装系统,将清洁能源应用在飞机上,同时考虑系统的散热防火等问题。
发明内容
本发明的目的在于提出一种基于电池封装的电动飞机系统。
实现本发明目的的技术解决方案为:一种基于电池封装的电动飞机系统,在左、右侧机翼的前、后梁之间设置若干翼肋,与前梁、后梁以及上、下蒙皮构成动力电池模组密闭安装舱,所述动力电池模组密闭安装舱内设置电池模组;在左、右侧机翼上还设置通风引气口、引气主管、引气歧管、引气歧管支管、出气歧管支管,所述引气歧管上设置引气管滞流阀,所述出气歧管支管上设置出气歧管滞流阀,气体通过通风引气口引入后,通过引气主管、引气歧管进入电池模组,再通过引气歧管支管进入电池模组电池块之间,最后通过出气歧管支管从电池模组电池块之间排出。
进一步的,所述通风引气口设置在机翼前缘下翼面压力区,所述出气歧管支管的排气出口设置在机翼上蒙皮转捩点处。
进一步的,所述通风引气口呈漏斗状。
进一步的,所述电池模组通过安装支架固定在动力电池模组密闭安装舱内。
进一步的,所述动力电池模组密闭安装舱的上蒙皮为可拆卸的盖板形式。
进一步的,所述动力电池模组密闭安装舱舱壁上依次设置隔热石棉层、不锈钢板层和防火漆层。
进一步的,所述左、右侧机翼内分别设置多个动力电池模组密闭安装舱,每个动力电池模组密闭安装舱内设置一个电池模组。
进一步的,所述左、右侧机翼前后、梁之间还设置灭火瓶密闭安装舱,所述灭火瓶密闭安装舱内设置灭火瓶,所述灭火瓶上设置灭火瓶引流管,所述灭火瓶引流管通入动力电池模组密闭安装舱,在灭火瓶引流管上设置灭火瓶滞流阀。
更进一步的,所述左、右侧机翼内分别设置多个动力电池模组密闭安装舱和灭火瓶密闭安装舱,所述动力电池模组密闭安装舱和灭火瓶密闭安装舱间隔设置,每个动力电池模组密闭安装舱内设置一个电池模组,每个灭火瓶密闭安装舱内设置一个灭火瓶。
更进一步的,所述左侧机翼内电池模组和灭火瓶的排布形式与右侧机翼内电池模组和灭火瓶的排布形式对称。
本发明与现有技术相比,其显著优点为:1)对电池模组配套设置灭火瓶,提升了电池模组的防火性能;2)设置通风防火管线,有利于电池模组在飞机爬升与巡航阶段通风散热。
附图说明
图1为电动飞机的外形图。
图2是电动飞机动力电池布置图。
图3是右侧机翼通风防火管线布置图。
图4是右侧I电池模组与右侧I灭火瓶的安装细节图。
图5是机翼剖视图。
图6是电池安装细节图。
图7是电池安装舱细节图。
图8是电池安装舱防火壁板细节图。
图9是排气孔关闭时机翼大迎角扰流图。
图10是排气孔打开时机翼大迎角扰流图。
具体实施方式
下面结合附图和具体实施例,进一步说明本发明方案。
本发明以图1所示小型(二到四座)飞机为例进行介绍。图1所示飞机为单发,下单翼(带翼梢小翼),低平尾,两到四个座位,左右各一个舱门(掀背式)。1为三叶拉力螺旋桨,2为电动机(直流或交流),3为驾驶舱前风挡,4为左侧舱门(掀背式,舱门顶部与机身之间安装有铰链,可朝上打开),5为右侧舱门(掀背式,舱门顶部与机身之间安装有铰链,可朝上打开),6为左侧机翼(双梁、单樯式),7为右侧机翼(双梁、单樯式),8为左侧翼梢小翼,9为右侧翼梢小翼,10为左侧副翼,11为左侧外襟翼,12为左侧内襟翼,13为右侧内襟翼,14为右侧外襟翼,15为右侧副翼,16为低平尾,17为升降舵,18为垂直尾翼,19为方向舵。
本发明小型电动飞机的动力电池分别布置在左、右侧机翼的前后梁之间。如图2所示,在左、右侧各布置三个电池模组,每个电池模组均含有单独的灭火瓶。图中,20为左侧I电池模组,21为左侧II电池模组,22为左侧III电池模组,23为右侧III电池模组,24为右侧II电池模组,25为右侧I电池模组,26为左侧I灭火瓶,27为左侧II灭火瓶,28为左侧III灭火瓶,29为右侧III灭火瓶,30为右侧II灭火瓶,31为右侧I灭火瓶。
为了保证电池系统的通风、防火,在左、右侧机翼内布设通风防火管线。由于左侧机翼与右侧机翼对称,在此以右侧机翼为例,如图3所示,说明飞机动力电池的安装与通风、防火,不对左侧机翼做进一步说明。32为右侧前梁,33为右侧后梁,34为右侧I号翼肋,35为右侧II号翼肋,36为右侧III号翼肋,37为右侧IV号翼肋,38为右侧V号翼肋,39为右侧VI号翼肋,40为右侧VII号翼肋,41为右侧机翼通风引气口(位于右侧机翼前缘下翼面压力区,呈漏斗状),42为引气主管I,43为引气主管II,44为引气歧管I,45为引气歧管II,46为引气歧管III,47为灭火瓶引流管I,48为灭火瓶引流管II,49为灭火瓶引流管III。
飞机动力电池通过位于右侧机翼前缘下翼面压力区呈漏斗状的41通风引气口进行引气,气流进入机翼后左右分流,分别进入42引气主管I,43引气主管II。然后分别通过44引气歧管I,45引气歧管II,46引气歧管III引气分别进入动力电池模组密闭安装舱。灭火瓶里的灭火泡沫分别通过47灭火瓶引流管I,48灭火瓶引流管II,49灭火瓶引流管III引流到动力电池模组密闭安装舱。
每组电池模组与灭火瓶的安装类似,以25右侧I电池模组与31右侧I灭火瓶为例进行说明,如图4所示。50为后排电池,51为电池安装支架,52为引气管滞流阀,53为电池块之间的引气歧管支管,54为电池块之间的出气歧管支管,55为出气歧管滞流阀,56为灭火瓶滞流阀,57为灭火器安装架。
飞机动力电池通过51安装支架分别固定在32前梁、33后梁以及下蒙皮上,每个模组包含两排电池,每排含八至二十四块电池,根据需要进行增减。25右侧I电池模组安装在由32右侧前梁、33右侧后梁、39右侧VI号翼肋、40右侧VII号翼肋以及上下蒙皮组成的密闭空间内。31右侧I灭火瓶安装在由32右侧前梁、33右侧后梁、38右侧V号翼肋,39右侧VI号翼肋以及上下蒙皮组成的密闭空间内。31右侧I灭火瓶通过57灭火器安装架(周向四个)进行固定。
25右侧I电池模组通风是通过43引气主管II进行引气,通过若干53电池块之间的引气歧管支管将气流引入到电池安装舱室,并最后通过若干54电池块之间的出气歧管支管将气流引出,并最总通过上翼面流出,将电池热量带走。43引气主管II上安装有52引气管滞流阀,54电池块之间的出气歧管上安装有55出气歧管滞流阀。
当由于电池短路或其他故障导致的电池过热或火灾产生时,驾驶员先通过指令将52引气管滞流阀与55出气歧管滞流阀关断,掐断进气与出气口,将电池安装舱室封闭。同时打开31右侧I灭火瓶(含泡沫或二氧化碳,压力2-5MPa)的56灭火瓶滞流阀,将灭火介质导入到电池安装舱进行灭火。
图5为机翼剖视图(右侧I电池模组站位,A-A剖面),58为机翼上蒙皮,59为机翼下蒙皮,60为右侧副翼,61为右侧副翼铰链轴,62为右侧机翼后缘纵樯,63为通风引气排风口(靠近机翼后缘),64为前排电池。
图6为电池安装图(右侧I电池模组站位,A-A剖面),65为上蒙皮盖板,电池拆装检查与更换时,将65上蒙皮盖板与机翼32前梁、33后梁上缘条相连接的螺栓拧出,在将64前排电池、50后排电池取出。其中65为前排电池安装架I,51为前排电池安装架II,66为后排电池安装架I,67为后排电池安装架II。
图7为右侧I电池模组即68电池安装舱剖视图。为了达到防火要求,舱壁需进行特殊处理。如图8所示,在69复合材料(或铝合金)舱壁上分别粘结70隔热石棉层、71不锈钢板层、72防火漆层进行隔热防火处理,保护69复合材料(或铝合金)舱壁免受高温侵袭。
本发明创新性地设计出一种电动飞机动力电池的封装方案,该封装方案可以直接将飞行中机翼前缘冷空气引入进电池安装舱对电池进行通风冷却,同时将排气出口设计在机翼上蒙皮靠近转捩点(层流与湍流转变)位置,排气的同时增加了机翼上蒙皮气流的动能,提升了机翼在大迎角时的升力,如图9与图10对比,涡流区明显向后缘移动。同时,该方案将电池分为左、右机翼各三个模组进行安装,且每个模组单独配置灭火瓶,每个电池模组采用独立的防火隔舱,防止了由于电池故障或火灾引发飞机灾难性后果,提升了飞机动力电池的安全可靠度。关于电池模组和灭火瓶的数量及排布形式等,可以根据实际情况调整。
Claims (5)
1.一种基于电池封装的电动飞机系统,其特征在于,在左、右侧机翼的前、后梁之间设置若干翼肋,与前梁、后梁以及上、下蒙皮构成动力电池模组密闭安装舱,所述动力电池模组密闭安装舱内设置电池模组;在左、右侧机翼上还设置通风引气口、引气主管、引气歧管、引气歧管支管、出气歧管支管,所述引气歧管上设置引气管滞流阀,所述出气歧管支管上设置出气歧管滞流阀,气体通过通风引气口引入后,通过引气主管、引气歧管进入电池模组,再通过引气歧管支管进入电池模组电池块之间,最后通过出气歧管支管从电池模组电池块之间排出;
所述左、右侧机翼内分别设置多个动力电池模组密闭安装舱,每个动力电池模组密闭安装舱内设置一个电池模组;
所述左、右侧机翼前后、梁之间还设置灭火瓶密闭安装舱,所述灭火瓶密闭安装舱内设置灭火瓶,所述灭火瓶上设置灭火瓶引流管,所述灭火瓶引流管通入动力电池模组密闭安装舱,在灭火瓶引流管上设置灭火瓶滞流阀;
所述左、右侧机翼内分别设置多个动力电池模组密闭安装舱和灭火瓶密闭安装舱,所述动力电池模组密闭安装舱和灭火瓶密闭安装舱间隔设置,每个动力电池模组密闭安装舱内设置一个电池模组,每个灭火瓶密闭安装舱内设置一个灭火瓶;
所述通风引气口设置在机翼前缘下翼面压力区,所述出气歧管支管的排气出口设置在机翼上蒙皮转捩点处;所述通风引气口呈漏斗状。
2.根据权利要求1所述的基于电池封装的电动飞机系统,其特征在于,所述电池模组通过安装支架固定在动力电池模组密闭安装舱内。
3.根据权利要求1所述的基于电池封装的电动飞机系统,其特征在于,所述动力电池模组密闭安装舱的上蒙皮为可拆卸的盖板形式。
4.根据权利要求1所述的基于电池封装的电动飞机系统,其特征在于,所述动力电池模组密闭安装舱舱壁上依次设置隔热石棉层、不锈钢板层和防火漆层。
5.根据权利要求1所述的基于电池封装的电动飞机系统,其特征在于,所述左侧机翼内电池模组和灭火瓶的排布形式与右侧机翼内电池模组和灭火瓶的排布形式对称。
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