CN111022412B - 一种飞机机翼装配用平衡气缸 - Google Patents
一种飞机机翼装配用平衡气缸 Download PDFInfo
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Abstract
本发明涉及航天航空技术领域,且公开了一种飞机机翼装配用平衡气缸,包括缸体和活塞杆,所述缸体和活塞杆活动连接,所述活塞杆的底部设有可以平衡活塞杆所受重力的平衡腔。该飞机机翼装配用平衡气缸,平衡腔的气压与其载荷适配,工作人员施加很小的力就去驱动载荷移动,在多个平衡气缸用于不规则的物体时,通过外力平衡装置对活塞杆的作用力平衡活塞杆的载荷变化,另一方面,当载荷变化大于可承载范围时,锁定角度的变化,进一步提高平衡气缸的安全性,在对机翼的角度进行微调时,无需借助任何吊车,使用人力即可完成,其次,当机翼的角度变化重力重新分布时,辅助工件自动平衡,避免机翼角度变化失控,减少生产事故。
Description
技术领域
本发明涉及航天航空技术领域,具体为一种飞机机翼装配用平衡气缸。
背景技术
由于机翼具有跨度大、体积大、重量大的“三大”特性, 现行的机翼安装方法是从四个方向采用多人牵引,防止机翼冲撞机身,而后拆除所有机翼与机身的连接部件,用吊车起吊加人工微调的方法安装机翼,实际时微调时需要多人观察,并指挥吊车操作人员调整机翼角度,角度调整过于复杂。
进一步的,由于飞机机翼的形状不规则,在调整角度的时候,机翼倾角发生改变,会引起机翼与吊车的各个连接位置的重力分布发生变化,并随着重力分布的变化,机翼调整发生失控,使机翼发生翻转,发生生产事故。
发明内容
针对上述背景技术的不足,本发明提供了一种飞机机翼装配用平衡气缸的技术方案,具有调整简单,过程易控等优点,解决了背景技术提出的问题。
本发明提供如下技术方案:一种飞机机翼装配用平衡气缸,包括缸体和活塞杆,所述缸体和活塞杆活动连接,所述活塞杆的底部设有能够平衡活塞杆所受重力的平衡腔,所述平衡腔连通有气控减压阀,所述气控减压阀连通有可远程控制的先导式压力减压阀,所述平衡腔中设有气压传感器,所述活塞杆和上端载荷之间设有加速度传感器和线速度传感器,所述活塞杆的外侧壁设有平衡活塞杆所受的力的作用使加速度为零的外力平衡装置。
优选的,当所述活塞杆的加速度大于阙值或速度大于阙值时,触发外力平衡装置启动。
优选的,所述外力平衡装置包括壳体、永磁体和线圈,所述壳体与缸体固定连接,所述永磁体与活塞杆固定连接,所述线圈与壳体固定连接,所述线圈的轴线与活塞杆的轴线重合,所述线圈中的电流大小和大小根据活塞杆的加速度大小和方向而调整。
优选的,所述活塞杆的外侧壁设有至少两组永磁体,两个所述永磁体的间距与线圈的宽度相同。
优选的,当所述线圈中电流大于阙值时触发安全运行模式,在所述安全运行模式中所述线圈中的电流随着活塞杆的速度调整,直至所述活塞杆的速度变为零。
本发明具备以下有益效果:
1、该飞机机翼装配用平衡气缸,平衡腔的气压与其载荷适配,工作人员施加很小的力就去驱动载荷移动,在多个平衡气缸用于不规则的物体时,物体的角度变化会使不同的平衡气缸载荷发生变化时,通过外力平衡装置对活塞杆的作用力平衡活塞杆的载荷变化,避免活塞杆的载荷急剧变化,使角度变化相对平稳,避免载荷变化失控发生事故,另一方面,当载荷变化大于可承载范围时,锁定角度的变化,进一步提高平衡气缸的安全性。
附图说明
图1为该飞机机翼装配用平衡气缸结构示意图;
图2为该飞机机翼装配用平衡气缸的控制示意图;
图3为该飞机机翼装配用平衡气缸的控制流程图。
图中:1、缸体;2、活塞杆;3、平衡腔;4、外力平衡装置;41、壳体;42、永磁体;43、线圈;5、气控减压阀;6、先导式压力减压阀。
具体实施方式
下面将结合本发明实施例中的附图,对本发明实施例中的技术方案进行清楚、完整地描述,显然,所描述的实施例仅仅是本发明一部分实施例,而不是全部的实施例。基于本发明中的实施例,本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例,都属于本发明保护的范围。
请参阅图1-3,一种飞机机翼装配用平衡气缸,包括缸体1和活塞杆2,缸体1和活塞杆2活动连接,活塞杆2的底部设有能够平衡活塞杆2所受重力的平衡腔3,平衡腔3中气压和载荷对活塞杆2的压力相同,平衡活塞杆2的受力,在使用很小的力的情况下就能够推动活塞杆2移动,平衡腔3连通有气控减压阀5,气控减压阀5为大流量、大排放量高精密的减压阀,快速维持平衡腔3内气压的平衡,气控减压阀5连通有可远程控制的先导式压力减压阀6,先导式压力减压阀6平衡腔3中设有气压传感器,气压传感器用于检测平衡腔3内气压是否与设定相同,活塞杆2和上端载荷之间设有加速度传感器和线速度传感器,气压传感器、加速度传感器、线速度传感器外力平衡装置4和先导式压力减压阀6均与控制器连接,活塞杆2的外侧壁设有平衡活塞杆2所受的力的作用使加速度为零的外力平衡装置4,由于加速度调整时滞后的,而手动推动活塞杆2的力量是变化的,处于不断变化中,因此手可以推动活塞杆2,而当因为重力失衡施加在活塞杆2上的力是一次性的,将外力平衡装置4将其加速度变为零,使活塞杆2受力再次平衡,避免活塞杆2的受力过快变化,操作人员施加一点外力就可以活塞杆2恢复平衡。
其中,当活塞杆2的加速度大于阙值1或速度大于阙值2时,触发外力平衡装置4启动当活塞杆2受力过大或速度过大,极易失衡的时候才启动外力平衡装置4平衡力的作用,在加速度小于阙值1和速度小于阙值2时,外力平衡装置4不启动,人力的作用即可使活塞杆2移动。
其中,外力平衡装置4包括壳体41、永磁体42和线圈43,壳体41与缸体1固定连接,壳体41位于缸体1的上端面,永磁体42与活塞杆2固定连接,线圈43与壳体41固定连接,线圈43与控制器连接,控制器控制线圈43的电流方向和大小,进而控制线圈43内部的磁场大小和方向,线圈43的轴线与活塞杆2的轴线重合,线圈43中的电流大小和大小根据活塞杆2的加速度大小和方向而调整,控制器根据加速度大小和方向确定需要平衡的力的大小和方向,进而控制线圈43中的电流大小和方向。
其中,活塞杆2的外侧壁设有至少两组永磁体42,两个永磁体42的间距与线圈43的宽度相同,线圈43的磁场依次作用在永磁体42上,在满足活塞杆2移动的同时,减少永磁体42所需要的体积。
其中,当线圈43中电流大于阙值3时触发安全运行模式,在安全运行模式中线圈43中的电流随着活塞杆2的速度调整,直至活塞杆2的速度变为零,避免调整需要的平衡力大于线圈43和永磁体42之间最大的作用力。
本发明的工作原理及工作流程:
该飞机机翼装配用平衡气缸,调整先导式压力减压阀6控制平衡腔3内的压力大小,使其与活塞杆2的载荷适配,此时较小的外力即可以使活塞杆2移动,匀速或缓慢使活塞杆2移动,当载荷发生变化时,活塞杆2的加速度逐渐变大,当活塞杆2的加速度过大或速度过大时,外力平衡装置4启动,平衡活塞杆2的作用力,由于载荷变化刚开始很小,外力平衡装置4对活塞杆2的作用力足以平衡额外变化的力,避免载荷变化失控,当载荷进一步变化到失控范围时,即外力平衡装置4可提供的平衡力达到阙值时,外力平衡装置4提供的作用于用于制止物体角度进一步变化,控制载荷继续变大。
需要说明的是,在本文中,诸如第一和第二等之类的关系术语仅仅用来将一个实体或者操作与另一个实体或操作区分开来,而不一定要求或者暗示这些实体或操作之间存在任何这种实际的关系或者顺序。而且,术语“包括”、“包含”或者其任何其他变体意在涵盖非排他性的包含,从而使得包括一系列要素的过程、方法、物品或者设备不仅包括那些要素,而且还包括没有明确列出的其他要素,或者是还包括为这种过程、方法、物品或者设备所固有的要素。
尽管已经示出和描述了本发明的实施例,对于本领域的普通技术人员而言,可以理解在不脱离本发明的原理和精神的情况下可以对这些实施例进行多种变化、修改、替换和变型,本发明的范围由所附权利要求及其等同物限定。
Claims (4)
1.一种飞机机翼装配用平衡气缸,包括缸体(1)和活塞杆(2),所述缸体(1)和活塞杆(2)活动连接,其特征在于:所述活塞杆(2)的底部设有能够平衡活塞杆(2)所受重力的平衡腔(3),所述平衡腔(3)连通有气控减压阀(5),所述气控减压阀(5)连通有可远程控制的先导式压力减压阀(6),所述平衡腔(3)中设有气压传感器,所述活塞杆(2)和上端载荷之间设有加速度传感器和线速度传感器,所述活塞杆(2)的外侧壁设有平衡活塞杆(2)所受的力的作用使加速度为零的外力平衡装置(4),所述外力平衡装置(4)包括壳体(41)、永磁体(42)和线圈(43),所述壳体(41)与缸体(1)固定连接,所述永磁体(42)与活塞杆(2)固定连接,所述线圈(43)与壳体(41)固定连接,所述线圈(43)的轴线与活塞杆(2)的轴线重合,所述线圈(43)中的电流大小和大小根据活塞杆(2)的加速度大小和方向而调整。
2.根据权利要求1所述的一种飞机机翼装配用平衡气缸,其特征在于:当所述活塞杆(2)的加速度大于阙值1或速度大于阙值2时,触发外力平衡装置(4)启动。
3.根据权利要求1所述的一种飞机机翼装配用平衡气缸,其特征在于:所述活塞杆(2)的外侧壁设有至少两组永磁体(42),两个所述永磁体(42)的间距与线圈(43)的宽度相同。
4.根据权利要求1所述的一种飞机机翼装配用平衡气缸,其特征在于:当所述线圈(43)中电流大于阙值3时触发安全运行模式,在所述安全运行模式中所述线圈(43)中的电流随着活塞杆(2)的速度调整,直至所述活塞杆(2)的速度变为零。
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